Heat Treater's Guide: Practices and Procedures for Nonferrous Alloys

Heat Treater's Guide Practices and Procedures for Nonferrous Alloys Harry Chandler, Editor Veronica Flint, Manager of Bo...

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Heat Treater's Guide Practices and Procedures for Nonferrous Alloys Harry Chandler, Editor Veronica Flint, Manager of Book Acquisitions Grace M. Davidson, Manager of Book Production Randall L. Boring, Production Project Coordinator Cheryl L. Powers, Production Project Coordinator Alexandru Popaz Pauna, Production Project Coordinator

AS~

c:z The Materials Information Society

Copyright© 1996 by ASM International® AII rights reserved

No part of this book may be reproduced, stored in a retrieval system, or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the written permission of the copyright owner. First Printing, November 1996 Second Printing, February 1999 Third Printing, March 2006

Great care is taken in the compilation and production of this Volume, but it should be made clear that NO WARRANTIES, EXPRESS OR IMPLIED, INCLUDING, WITHOUTLIMITATlON, WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE, ARE GIVEN IN CONNECTION WITH THIS PUBLICATION. Although this information is believed to be accurate by ASM. ASM cannot guarantee that favorable results will be obtained from the use of this publication alone. This publication is intended for use by persons having technical skill, at their sole discretion and risk. Since the conditions of product or material use are outside of ASM's control, ASM assumes no liability or obligation in connection with any use of this information. No claim of any kind, whether as to products or information in this publication, and whether or not based on negligence, shall be greater in amount than the purchase price of this product or publication in respect of which damages are claimed. THE REMEDY HEREBY PROVIDED SHALL BE THE EXCLUSIVE AND SOLE REMEDY OF BUYER, AND IN NO EVENT SHALL EITHER PARTY BE LIABLE FOR SPECIAL, INDlRECf OR CONSEQUENTIAL DAMAGES WHETHER OR NOT CAUSED BY OR RESULTING FROM THE NEGLIGENCE OF SUCH PARTY. As with any material, evaluation of the material under enduse conditions prior to specification is essential. Therefore, specific testing under actual conditions is recommended. Nothing contained in this book shall be construed as a grant of any right of manufacture, sale, use, or reproduction, in connection with any method, process, apparatus, product, composition, or system, whether or not covered by letters patent, copyright, or trademark, and nothing contained in this book shall be construed as a defense against any alleged infringement of letters patent, copyright, or trademark, or as a defense against liability for such infringement Comments, criticisms, and suggestions are invited, and should be forwarded to ASM International.

Library of Congress Cataloging Card Number: 96-85651 ISBN: 0-87170-565-6 SAN: 204-7586

ASM International® Materials Park, OH 44073-0002

Printed in the United States of America

Table of Contents Introduction. . . . . . . . . . . . . . . . . . . . . . . .. Diffusion Process. . . . . . . . . . . . . . . .. Annealing Cold-Worked Metals ..... Homogenization of Castings. . . . . . .. Precipitation Hardening Treatments . . . . . . . . . . . . . . . . . .. Developing Two-Phase Structures. . ..

1 1 1 4 5 6

Superalloys . . . . . . . . . . . . . . . . . . . . . . . . . .. 9 Heat Treating Superalloys. . . . . . . . . . . .. 11 Characteristics " 11 Heat Treating Practice " 12 Nickel-Base Alloys " 17 Astroloy . . . . . . . . . . . . . . . . . . . . . .. 17 D-979 '" 19 IN 100 19 IN 102 25 Incoloy 901 " 26 Inconel 706 " 29 Inconel X 750 .. . .. . .. . 30 Incone1751 33 Hastelloy B " 33 Hastelloy B-2 " 33 Hastelloy C " 35 Hastelloy C-4. . . . . . . . . . . . . . . . . .. 36 Hastelloy C-276 " 37 Hastelloy N " 37 Hastelloy S '" 37 Hastelloy W " 38 Hastelloy X . . . . . . . . . . . . . . . . . . .. 38 Haynes 214 39 Haynes 230 " 40 Nimonic 86 . . . . . . . . . . . . .. 40 Custom Age 625 PLUS " 40 Haynes 242 " 40 Incone1702 " 41 Incone1718 " 41 Inconel721 59 Inconel 722 " 59 C-263 59 Pyromet 31 " 59 Nimonic 80A . . . . . . . . . . . . . . . . . .. 60 Nimonic 90 " 62 Pyromet 860 " 62 Refractory 26 " 63 Rene 41 63 Rene 95 68 Rene 100 69 Udimet 500 " 69 Udimet 520 " 70 Udimet 700 " 70 Udimet 710 " 74 UnitempAF2-lDA 74 Waspaloy " 76 Nimonic PE16 " 81 Nimonic PK33 " 81 Inconel 600 " 81 Inconel 601 " 88 Inconel 604 . . . . . . . . . . . . . . . . . . .. 88 Incone1617 " 88

Inconel 625 88 Nimonic 75 97 RA-333 97 NA-224 97 Cobalt-Base Alloys 98 S-816 98 Stellite 6B 98 Haynes 25; L-605 99 Haynes 188 . . . . . . . . . . . . . . . . . . . . 102 MP35N 105 MP159 106 Air-Resist 213 106 Elgiloy. . . . . . . . . . . . . . . . . . . . . . . . 106 V-36 107 UMCo-50 107 Iron-Base Alloys 108 A-286 .. '" 108 W-545 112 V-57 112 Incoloy 800 112 Incoloy 801 114 Incoloy 802 115 Incoloy 807 115 Incoloy 825 115 Incoloy 903 117 Incoloy 907 117 Incoloy 909 117 Incoloy 925 118 16-25-6 118 17-14 CuMo 119 19-9DL 119 N-155 119 RA-330 120 Discaloy. . . . . . . . . . . . . . . . . . . . . . . 120 Haynes 556 121 Pyromet CTX-l. 122 PyrometCTX-3 122 Nickel. 123 Heat Treating Nickel . . . . . . . . . . . . . . . . 125 Nickel 200 126 Nicke1201 126 Monel 400 127 Monel R-405 127 Monel K-500 127 Aluminum Alloys 129 Heat Treating Aluminum Alloys 131 Strengthening by Heat Treatment 135 Hardening of Cast Alloys . . . . . . . . . 140 Stress Relief 140 Effects of Reheating . . . . . . . . . . . . . 140 Annealing . . . . . . . . . . . . . . . . . . . . . 141 Grain Growth 142 Dimensional Changes during Heat Treatment. 142 Quality Assurance 142 Temper Designations for Heat-Treatable AluminumAlloys 144 Properties of Wrought Aluminum and Wrought Aluminum Alloys. . . .. 146 V

1050 1060 1100 1145 1199 1350 2011 2014, Alclad 2014 2017 2024, Alclad 2024. . . . . . . . . . . . . .. 2048 2124 2218 2219, Alclad 2219 2319 2618 3003, Alclad 3003 3004, Alclad 3004 3105 4032 4043 '" 5005 5050 5052 5056, Alclad 5056 5083 5086, Alclad 5086 5154 5182 5252 5254 5356 5454 5456 5457 5652 5657 6005 6009 6010 6061, Alclad 6061. . . . . . . . . . . . . . . 6063 6066 6070 6101 6151 6201 , 6205 6262 6351 6463 7005 7039 7049 7050 7072 7075, A1clad7075 7175 7178, Alclad 7178 7475

149 150 151 153 153 154 155 155 159 159 169 171 173 174 178 179 180 182 184 184 185 185 186 187 188 189 191 191 192 193 193 194 194 195 197 198 198 200 200 201 201 206 208 208 209 210 211 211 212 213 214 214 215 217 218 221 221 238 239 241

Aluminum Casting Alloys. . . . . . . . . . .. 201.0 204.0 206.0, A206.0 208.0 238.0 242.0 295.0 296.0 308.0 319.0 332.0 336.0 339.0 354.0 355.0, C355.0 356.0, A356.0 357.0, A357.0 359.0 360.0, A360.0 . . . . . . . . . . . . . . . . .. 380.0, A380.0 383.0 384.0, A384.0 390.0, A390.0 . . . . . . . . . . . . . . . . .. 413.0, M13.0 443.0, A443.0, B443.0, C443.0 514.0 518.0 520.0 535.0, A535.0, B535.0 712.0 713.0 771.0 850.0 Heat Treating Aluminum-Lithium Alloys Weldalite 049 . . . . . . . . . . . . . . . . .. 2090 2091 8090 CP276 Heat Treating Aluminum PIM Parts . . . . Heat Treatable Grades . . . . . . . . . .. Applications . . . . . . . . . . . . . . . . . .. Heat Treating Technology Copper Alloys . . . . . . . . . . . . . . . . . . . . . . . Heat Treating Copper Alloys. . . . . . . . .. Homogenizing . . . . . . . . . . . . . . . .. Annealing. . . . . . . . . . . . . . . . . . . .. Stress Relieving . . . . . . . . . . . . . . . . Hardening. . . . . . . . . . . . . . . . . . . . . Copper-Beryllium Alloys Copper-Chromium Alloys Copper-Zirconium Alloys. . . . . . . . . Miscellaneous PrecipitationHardening Alloys ... . . . . . . . . . Spinodal-Hardening Alloys Copper-Aluminum (Aluminum Bronze) Alloys Copper Casting Alloys Wrought Coppers and Copper Alloys . . . CIOIOO and C10200 CI0300 CI0400, C10500, ClO700 CI0800 CllOOO(99.95Cu-0.040) C11l00 (99.95Cu-0.040-0.01Cd)

244 244 245 246 248 248 249 250 251 251 252 252 252 253 253 255 257 259 259 260 261 261 262 262 263 264 264 265 265 266 266 267 267 268 269 269 271 274 276 279 280 280 280 280 283 285 285 285 286 287 288 290 290 291 291 291 292 295 295 298 298 300 300 306

C1l300, C1l400, C1l500, C1l600 (99.96Cu + Ag - 0040) , C12500,CI2700,C12800,CI2900, C13000 C14300, C14310 (99.90Cu-O.lCd; 99.8Cu-0.2Cd) , Cl4500 (99.5Cu-0.Te) , Cl4700 (99.6Cu-OA5) , Cl5000 (99.85Cu-0.15Zr) C15100 (99.9Cu-0.1Zr) , C15500 (99.75Cu-0.llMg0.06P) Cl5710 (99.8Cu-0.2Ah03) , C15720 (99.6Cu-0.4Ah03) , C15735 (99.3Cu-0.7Ah03) Cl6200 (99Cu-1Cd) C17000 (98Cu-1.7Be-0.3Co) , Cl7200, C17300 , C17410 (99.2Cu-0.3Be-0.5Co) , C17500 (97Cu-0.50Be-2.5Co) , C17600 , Cl8100 (99Cu-0.8Cr-0.16Zr0.04Mg) , C18200, C18400, C18500 (99Cu-1Cr) C18700 (99Cu-1Pb) , Cl9200 (98.97Cu-1.0Fe-0.03P) .. , Cl9210 (99.87Cu-0.lFe-0.03P) .. , C19400 (Cu-2.35Fe-0.03P0.12Zn) , Cl9500 (97Cu-1.5Fe-0.1P0.8Co-0.6Sn) , C19700 (99.15Cu-0.6Fe-0.2P0.05Mg) , C21000 (95Cu-5Zn) , C22000 (90Cu-IOZn) , C22600 (87.5Cu-12.5Zn) , C23000 (85Cu-15Zn) , C24000 (80Cu-20Zn) , C26000(70Cu-30Zn) C26800, C27000 (65Cu-35Zn) , C28000 (60Cu-40Zn) C31400 (89Cu-9.lZn-1.9Pb) , C31600 (89Cu-8.1Zn-1.9Pb1Ni) , C33000 (66Cu-33.5Zn-0.5Pb) , C33200 (66Cu-32AZn-1.6Pb) , C33500 (65Cu-34.5Zn-0.5Pb) , C34000 (65Cu-34Zn-1Pb) C342PO(62Cu-36.2Zn-2Pb) , C35300 (62Cu-36.2Zn-1.8Pb) C34900 (62Cu-37.5Zn-0.3Pb) , C35000 (65.5Cu-36AZn-l.lPb) C35600 (62Cu-35.5Zn-2.5Pb) , C36000 (61.5Cu-35.5Zn-3Pb) , C36500,C36600,C36700,C36800 (60Cu-39AZn-0.6Pb) , C37000 (60Cu-39Zn-lPb) , C37700 (60Cu-38Zn-2Pb) C38500 (57Cu-40Zn-3Pb) C40500 (95Cu-4Zn-1Sn) , C40800 (95Cu-2Sn-3Zn) C41100 (91Cu-8.5Zn-0.5Sn) C41500 (91Cu-7.2Zn-1.8Sn) , C41900 (90.5Cu-4.35Zn5.l5Sn) , C42200 (87.5Cu-ll.4Zn-l.lSn)

vi

306 308 309 309 309 310 312 312 313 313 314 314 314 316 320 321 323 323 324 325 325 326 326 328 328 328 330 331 332 334 334 339 341 343 343 343 344 344 345 345 345 346 347 347 347 349 349 349 350 351 351 351 352 353 353

C42500 (88.5Cu-9.5Zn-2Sn) C43000 (87Cu-IO.8Zn-2.2Sn) C43400 (85Cu-14.3Zn-0.7Sn) C44300,C44400,C44500 (71Cu-28Zn-lSn) C46400,C46500,C46600,C46700 (60Cu-39.2Zn-0.8Sn) C48200 (60.5Cu-38Zn-0.8Sn0.7Pb) C48500 (60Cu-37.5Zn-1.8Pb0.7Sn) C50500 (98.7Cu-1.3Sn) C51000 (94.8Cu-5Sn-0.2P) C51100 (95.6Cu-4.2Sn-0.2P) C52100 (92Cu-8Sn) C52400 (90Cu-IOSn) C54400 (88Cu-4Pb-4Sn-4Zn) C60600 (95Cu-5Al) C60800 (95Cu-5Al) C61000 (92Cu-8Al) C61300 (90Cu-7AI-0.3Sn) C61400 (91Cu-7AI-2Fe) C61500 (90Cu-8AI-2Ni) C62300 (87Cu-IOAI-3Fe) C62400 (86Cu-llAI-3Fe) C62500 (82.7Cu-4.3Fe-13Al) C63800 (95Cu-2.8AI-1.8SiOAOCo)

C65100 (98.5Cu-1.5Si) C65400 (95ACu-3.0Si-1.5SnO.lCr) C65500 (97Cu-3Si) C68800 (73.5Cu-22.7Zn-3AAlOACo)

,

C69000 (73.3Cu-22.7Zn-3AAl0.6Ni) , C69400 (81.5Cu-14.5Zn-4Si) C70400 (92ACu-5.5Ni-1.5Fe0.6Mn) C70600 (90Cu-IONi) C71000 (80Cu-20Ni) C71500 (70Cu-30Ni) C71900 (67.2Cu-30Ni-2.8Cr) C72200 (83Cu-16.5Ni-0.5Cr) C72500 (88.2Cu-9.5Ni-2.3Sn) C74500 (65Cu-25Zn-IONi) C75200 (65Cu-18Ni-17Zn) C75400 (65Cu-20Zn-15Ni) C75700 (65Cu-23Zn-12Ni) C77000 (55Cu-27Zn-18Ni) C78200 (65Cu-25Zn-8Ni-2Pb) Copper Casting Alloys C81300 C81400 , C81500 , C81800 (97Cu-1.5Co-IAgOABe) C82000 (97Cu-2.5Co-0.5Be) C82200 (98Cu-1.5Ni-0.5Be) C82400 (98Cu-1.7Be-0.3Co) C82500 (97.2Cu-2Be-0.5Co0.25Si) C82600 (97Cu-2ABe-0.5Co) C82800 (96.6Cu-2.6Be-0.5Co0.3Si) C83300

353 354 . 354 354 356 358 359 359 360 361 361 362 363 363 363 364 364 365 '366 367 368 368 369 370 370 370 371 372 372 373 373 375 376 377 378 378 378 379 380 381 381 382 393 383 383 383 384 384 385 386 386 387 388 389

C86100, C86200 (64Cu-24Zn3Fe-5Al~~n) .. . . . . . . . . . . .. 389 C86300 (64Cu-26Zn-3Fe3AI-4~n) . . . . . . . . . . . . . . . . .. 390 C86400 (59Cu-0.75Sn-0.75Pb-37Zn1.25Fe-0.75AI-0.5~n) 390 C86500 (58Cu-39Zn-1.3Fe-lAlO.5~n) 390 C86700 391 C86800 391 C87300 (formerly C87200). . . . . .. 392 C87600 392 C8761O 392 C87500, C87800 (82Cu~Si14Zn) 393 C87900 393 C92200 (88Cu-6Sn-l.SPb4.5Zn) 393 C92300 (87Cu-8Sn-1Pb-4Zn) . . . .. 394 C92500 (87Cu-llSn-1Pb-1Ni) .... 394 C92600 (87Cu-lOSn-1Pb-2Zn). . .. 395 C92700 (88Cu-lOSn-2Pb) 395 C92900 (84Cu-lOSn-2.5Pb3.5Ni) 395 C93200 (83Cu-7Sn-7Pb-3Zn) 395 C93400 396 C93500 (85Cu-5Sn-9Pb-1Zn). . . .. 396 C93700 (80Cu-lOSn-lOPb) 396 C93800 (78Cu-7Sn-15Pb) 397 C95200 (88Cu-3Fe-9Al) . . . . . . . .. 398 0.... I>...~

50

Hardnes~

\

a: J:

Fig. 4 Effect of annealing temperature on hardness and electrical resistivity of nickel. The metal has been cold worked at 25°C (77 OF) almost to fracture. Annealing time, 1 h

Annealing temperature, of 750 390 1110 1470 60

80

Q)

c:

"E 60

'"

\

J:

40

Resistivit;-

I

20 0

LIVE GRAPH Click here to view

'0;

40

~

«i

.~

1\

lI)

i

't;

's

30

ereep,h Haynes HastelJoyX 188

Waterquench. Aircool Furnacecool 10650°C (1200oF)andthenaircool

8 7 6

148 97 48

lnconel 617

302 15 9

Table 9 Typical heat treatments for precipitation-strengthened cast superalloys Alloy

Heal treatmenl (temperature/duration In bJ.,,,.-1------1

~ 1500

~

Nl-15Co-1OCr-5. 5Al- •• 7T1-3Mo-o. 95V(NOMINAL) ACTUAL COMPOSITION FOR TWO "LEVELS OFNv MEDIUM l'lv(2••9)1 Nl-13.3Co-l0.UCr5.5Al-•• 29T1-3. 55Mo-0. B6V mGH NV(2.65): Nl-13.3Co-l0.12Cr-5.6Al.. 69'1'1-3. G1Mo-0. 97V ALL ALLOYS MADE FROM SAME MASTER HEAT. ADDIT.IONS OF AlIoTl MADE DURING CASTING TO ACHIEVE DESIRED LEVEL OF ELECTRON VACANCY CONCENTRATION Rv COARSE GRAIN ALLOYS PREPARED BY . NORMAL INVESTMENT CASTING PlIOOEDUREll; FINE GRAIN ALLOYS PREPARED BY MOLD DlNOCULATION 'rE;T SPECIMEN 1/. IN DIA x 11/. IN GAGE LENGTH EXPOSED WITHOUT STRESS FOR TIMES AND TEMPERATURES INDICATED ~GHNV _ ~ MEDIUMNv

;:::.:::-.e- P7

I~

...

1400

(

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'

1300 1

... w

--

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~

(r

w

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I-

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/

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...........

-

-

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---- -- -

I

FINE

~.>O~E "FINE

20

Alloy 5 PMandCE

...... ~

I

100

1000 TIME - HR

10,000

IN 100 (Modified): Time-temperature-precipitation diagram. Start of sigma phase. PM modified versions of IN 100 (Alloy 3) and AF-2IDA (Alloy 5) vs. conventional wrought. IN 100 Nb-modified (PM), composition: Ni - 11.9% Cr - 17.7% Co - 3.3% Mo - 5.2% AI- 4.2% Ti - 1.4% Nb - 0.24% B - 0.06% Zr - 0.09% C. IN 100 Nb-modified (CE), composition: Ni -12.1% Cr-17.4% Co - 3.2% Mo - 5.3% AI4.4%Ti - 1.5% Nb - 0.028% B - 0.06% Zr - 0.08% C. AF-2-1 DA NbC-modified (PM), composition: Ni -12.1%Cr-10.0%Co- 5.7% W -2.9% Mo-4.8%AI-3.1% Ti-1.5% Nb-1.5% Ta-0.018% B-0.08% Zr - 0.09% C. AF-2-1DA Nb-C-modified (CE), composition: Ni12.0% Cr - 10.3% Co - 5.5% W - 2.9% Mo - 4.7% AI- 2.9% Tl - 1.4% Nb - 1.6% Ta - 0.020% B - 0.11% Zr - 0.09% C. PM, powder metallurgy; CE, cast and extruded. Treatment: Both PM and CE materials were given identical heat treatments, which consisted of a partial gamma prime solution treatment at temperatures 20 °C (70 OF) below the gamma prime solvus for 2 h, followed by cooling in air, a carbide-stabilizing heat treatment at 980 °C (1795 OF) for 8 h, followed by an air cool, and a gamma prime precipitation cycle of 760 °C (1400 OF) for 8 h. To observe the formation of sigma phase the heattreated specimens were exposed to temperatures from 708 to 980 °C (1300 to 1795 OF) for various times in argon

Next Page

Nickel-Base Superalloys /25

IN 100: Time-temperature-transformation diagram. Shows start of sigma phase formation. Composition: Ni - 0.18% C -14.26% Co10.26% Cr - 2.97% Mo - 5.35% Ti - 5.60% AI - 0.30% Fe - 0.92% V - 0.012% B - 0.05% Zr

1800

1----------;

/700

1------------11700'F/20,oOO P.S.I. 2056.1 HOURS

t

1600

I--------,L----l------------I------------l

/500

1------..,..

0::

L

!5'" ~

'" ::e

ISOOOF/60,OOO P.S.1. 769.3

HOURS

Q.

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I-

1400 6 -

_

100 1550·'/70.000 P.S.!. 1827.1 HOURS

1000

Compilation of phaaes found in IN-IOO

Phases present

TIC (J

M23C6 M6C M6C'

Ascast

4.30A Strong N.D.(a)

1O.67A Veryweak II.OIA Veryweak 1O.92A Very weak

/0.000 TIME (HOURS I -

As-cast + 1800°F/13,OOO psi, 1592.7b

As-east + 1700°F/20,OOO psl 2056.1b

As-east + 1500°F/50,OOO psl, 769.3b

As-east + 1350°F/70,OOO psi, 1827.1b

4.31A Weaktomoderate weak c=4.62A a=8.84A da=O.S2 Very weak 1O.71A Strong N.D.

4.31A Moderate c=4.60A a=8.8SA da=O.S2 Weak 1O.71A Strong N.D.

4.31A Strong c=4.59A a=8.8SA da=O.52 Moderate strong 1O.71A Moderate strong 11.06A Very weak 1O.98A Weak

4.31A Strong c=4.S8A a=8.83A da=O.S2 Moderate 1O.68A Moderate

?(b)

?

(a)Not detected. (b)Presenceor absencequestionable.

IN 102 Chemical Composition. IN 102 (UNS N06102) (nominal). 15.00 Cr, 67.00Ni, 2.90 Mo, 3.00 W, 2.90 Nb, 0.50Ti, 0.50 AI, 7.00 Fe, 0.06 C, 0.0005 B, 0.02 Mg, 0.03 Zr

Similar Alloys (U.S. and/or Foreign). UNS N06102

Characteristics A nickel-base, precipitation-hardening alloy

Previous Page 26/ Heat Treater's Guide: Nonferrous Alloys

Incoloy 901 and more practical. For parts formed from sheet or strip, rapid air cooling usually is adequate. Rapid cooling from solid treating or annealing temperatures does not suppress the aging treatment for some alloys, such as Astroloy. They become harder and stronger

Chemical Composition.lncoloy 901 (UNS N09901) (nominal). 12.50 Cr, 42.50 Ni, 6.00 Mo, 2.70 Ti, 36.20 Fe, 0.10 C max

Similar Alloys (U.S. and/or Foreign). UNS N09901


Incoloy 901: Effectof grain size on the high-cycle fatigue properties at 455°C (850 OF)

Recommended Heat Treating Practice

455°C(850 oF) Fatigue strength (10'cycles)

Stress Relieving. Full annealing is recommended, because intermediate Incoloy901

temperatures cause aging

Annealing. Treatment is at 1095 °C (2000 OF). Holding time is 2 h per inch of section. Minimum hardness is obtained by cooling rapidly from the annealing temperatures to prevent precipitation ofhardening phases; water quenching is preferred; and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching is adequate

Fatigue ratio (FS!UTS)(a)

gralnsize

MPa

ksl

AS1M2 AS1M5 AS1M12

315 439 624

64

46

0.32 0.42 0.55

91

(a) FSIlITS. fatiguestrengthto ultimatetensilestrength

Incoloy 901: Effectof stabilization on typical properties Elongation in

Thsted at 20 °C (70 oF) No intennediateaging(a): HeatA HeatB Withintennediateaging(b): HeatA HeatB Thsted at 650°C (1200 oF) No intermediate aging(a): HeatA HeatB Withintermediate aging(b): HeatA HeatB

Yield strength

Ullimate tensile strength MPa ksi

MPa

ksi

(2 In.), %

Reduction in area, %

1050 1080

152 157

790 790

115 114

12 17

13 16

1040 1040

151 151

730 710

106 103

12 12

15 13

SOmm

Creep-rupture Iire,h

1.0

76 118

1.5

11 7

45 54

(a) Heat treatment:1120°C (2050 "P) for 2 h. waterquench;745°C (1375 oF) for 24 h, air cool.(b) Heat treatment: 1120°C (2050 "P) for 24 h, waterquench;815°C (1500 oF), 4 h; air cool;745°C (1375 "F), 24 h; air cool

Incoloy 901 : Tensile properties at 540°C (1000 OF) at various locations in disk forgings in two heat-treated conditions Conditlon

'lestlocation

Yield strength ksi MPa

Ultimate tensile strength

Elongalion in SO Reduction in

MPa

ksi

mm (2 In.), %

area,%

1095°C (2000"F) for2 h, waterquench+790°C (1455"F) for2 h, water quench+ 730°C (1345 OF)for 24 h. aircool

Rim-radial-top Rim-tangent-middle Web-radial-top Web-tangent-middle Bore-radial-top Bore-tangent-middle

772 772 781 772 782 772

112.0 112.0 113.2 112.0 113.4 112.0

1037 1048 1049 1041 1045 1027

150.4 152.0 152.1 151.0 151.6 149.0

13 12 13 14 13 14

18 18 21 21 20 22

1010°C (1850oF) for 2 h. waterquench+ 730°C (1345 oF) for20 h, water quench+650 °C (1200 oF) for 20 h, aircool

Rim-radial-top Rim-tangent-middle Web-radial-top Web-tangent-middle Bore-radial-top Bore-tangent-middle

832 910 853 876 855 876

120.6 132.0 123.7 127.0 124.0 127.0

1066 1117 1091 1089 1069 1105

154.6 162.0 158.2 158.0 155.0 160.2

14 17 20 19

27 38 39 39 30 38

17 17


210

30

Temperature, ·F 570 750

390

1110

930

Incoloy 901: Effects of temperature and grain size on tensile properties of forgings in the solution-treated, stabilized, and aged condition. AC, air cooled

1290

1500 0955 ·C/1 h/AC + 720 ·C/4 h/AC + 650 ·C/12 h/AC 1400 ~-- .980 ·C/1 h/AC + 720 ·C/4 h/AC + 650 ·C/12 h/AC l> 1095 ·C/1 h/AC + 720 ·C/4 h/AC + 650 ·C/12 h/AC 1300

ASTM grain size 12 5

-----1200

LIVE GRAPH

2

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I----f---=::::::p.""""'::--+---+------I----+-----i 180

1200 I-----""'......=-------II--::...,=------I----t-""""'~__t---__t---___j

::a;

~

~ 160 Vi

~

00

Vi 1100 I----+----+-----"I'-o;o----"'I3 - ,. ~( )3

(

r-,~ ~ t'

1350 ---_. - - f--

r--... I"-

1300 Solu Ion reete

9P

-~O~~F:tt:

L""R

~ ~-3

~ ~ ~~ ~ N OF IOOHSK

170011' 48HA'i

1850': 3.4HR'i

Inconel 718: Precipitation phases. Composition: Fe - 53% Ni - 0.05% C - 1.0% Ti - 0.7% AI 19.0% Cr - 3.0% Mo - 5.3% Nb+Ta - 0.006% B 0.03% Zr - 0.2% Mn - 0.3% Si. Treatment: 1230 °C (2250 OF) for 2 h, ice brine quench + 705°C (1300 OF) for 100 h, water quench, aged at temperatures and times indicated

Nickel-Base Superalloys I 49

Inconel718: Time-temperature diagram. Composition: Ni - 0.06% C -18.86% Cr - 2.99% Mo - 0.93% Ti - 0.57% AI- 5.25% Nb -17.48% Fe. Treatment: Solution treated at 980°C (1795 OF) for 1 h, aged in air at 760 to 1095°C (1400 to 2000 OF) at 40°C (100 OF) intervals for 5000 h, and at 1149 °C (2100 OF) for 2000 h Very Abundant

h

NiSCb

\

\

\

\

\ \ \

I---- Sigma

·1

g Abundant

:a

...e

\ \

MC

.---L-------.

d

Gl U

I:l

\

I

)'_. I I

0

0

Gl

-

.-------.~.------_."

\

Medium

l-

:l

..c:

.

ll. 0

~

•

Rare

I

Very Rare

l

i IS00

-

I

I I I I I 1400

1700 1600 1800 Temperature, of

1600

1900

2000

2100

Inconel718: CCT diagram. Note: cooling rate °C/h, and resultant hardness, HV. Composition: Ni -17.4% Cr-18.7% Fe - 5.16% Nb2.96% Mo - 0.99% Ti - 0.48% AI - 0.06% C - 0.07% Mn - 0.10% Si -

0.9

0.4

e,

-

K

1,)

-

.110',

------

NF NF

NF

NF

NF

-

I1000 0.1

0.5

1.0

10

50

100

500

1000

TIME, HOURS

Inconel718: Time-temperature-precipitation diagram for Ni 3Nb compared to Eiselstein data. Composition: Fe - 53.8% Ni -18.0% Cr - 3;00% Mo - 5.24% Nb+Ta- 1.00% Ti - 0.59% AI- 0.05% C - 0.003% S - 0.004% B. Treatment: Solution treated at 1065 °C (1950 OF) for 4 h, air cooled 2000


~

1800

.... :>

1600

f-

...

-,

1400

I

,",

NO FILM

lL

.. ... .

,

I

6

~~ 20

8 10

A9in9 Time -

-- -

!

iI

I

~I-

40

60

100

200

400

Hours

Inconel718: Time-temperature-precipitation diagram. Occurrence of grain boundary carbide film and needles. Nominal composition: Ni - 19% Cr - 18% Fe - 5% Nb - 3% Mo - 0.15% Si - 0.10% Cu - 0.20% Mn - 1.0% Ti - 0.4% AI- 0.04% C - 0.007% S. Treatment: Solution annealed at 1040 °C (1900 OF), aged at various times and temperatures indicated

LIVE GRAPH

1700

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I....

1600

~t} II

0

~

1500

I Hour

:>

..

~.

~

01

~'

10 Hours

Q.

E ~

,

l'

NO FILM

..:

\.

1400

c:

'0

I\.

......

:

220

;e

-1'>-718

/;

180

",",' .....

-

r-, ~ As solution treated

N.

r-.V

II I 650 675 700 725 750 Temperature of 20-h aging, °C

~

~

t-h~c-+-- - 1 - - -

Annealmg temperature

I

I

--1---1250 'C(2280 OF) 1200 °C(2190 OF) ---"1---1150 °C12100 'FI -:::~:::::==I=== 1100 °c (201 0 ° F) 1050 °C11920 OF) OL---c-'=---+.:----.:..::~...=..:..:.=.c:__--! 20 30 40 10 50 o Amount 01 cold work, %


pyromet 860 Chemical Composition. Pyromet 860 (nominal). 13.00 4.00 Cr, 6.00 Mo, 3.00 Ti, 1.00 AI, 28.90 Fe, 0.05 C, 0.01 B

o,

44.00 Ni,

Recommended Heat Treating Practice Solution Treating. Treat at 1095 °C (2000 "F) for 2 h; water quench

Characteristics

High Temperature Aging. Treat at 830°C (1525 OF) for 2 h; air cool

A nickel-base, precipitation-hardening alloy

Low Temperature Aging. Treat at 760°C (1400 OF) for 24 h; air cool


Refractory 26 Chemical Composition. Refractory 26 (nominal). 18.00 Cr, 38.00 Ni, 20.00 Co, 3.20 Mo, 2.60 Ti, 0.20 AI, 16.00 Fe, 0,03 C, 0.015 B


Rene 41 Chemical Composition. Rene 41 (UNS N07041) (nominal). 19.00 Cr, 55.00 Ni, 11.00 Co, 10.00 Mo, 3.10 Ti, 1.50 AI, ood-~'-.ld-HHf+f+HH-H-H-H-H~

::;,

] (lJ

a.

E QI

-;;950 Kl~o--~>-----------m,..."..ffl97mH ~

850 t-(Jt--,fItHo-H-r+fIhl-r+f-f-:f-h.....'-H'-H'-H'-H'-He..,o..-j

o

1000

h

10000

Udimet 700 Chemical Composition. Udimet 700 (nominal). 18.00 Cr, 55.00 Ni, 14.80 Co, 3.00 Mo, 1.50 W, 5.00 Ti, 2.50 AI, 0.D7C, 0.01 B


Recommended Heat Treating Practice Alternative solution treating and aging procedures are available.

Solution Treating. lD lD

Treatment is at 1175 °C (2150 OF) for 4 h; cooling is in air Treatment is at 1080 °C (1975 OF) for 4 h; cooling is in air

Aging. lD lD

Treatment is at 845°C (1555 OF) for 24 h; cooling is in air Treatment is at 760°C (1400 OF) for 16 h; cooling is in air

Stress Relieving. Full annealing is recommended because intermediate temperatures cause aging Annealing. Treatment is at 1135 °C (2075 OF); holding time is 4 h per inch of section. Minimum hardness is obtained by rapid cooling from the annealing temperature, to prevent precipitation of hardening phases. Water quenching is preferred, and usually is necessary for heavy sections, but air cooling is preferred for heavy sections of Udirnet 700, because water quenching causes cracking. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts

formed from strip and sheet, rapid air cooling usually is adequate. Rapid cooling from the annealing or solution treating temperature does not suppress the aging reaction of some alloys, such as Astroloy, they become harder and stronger

Udimet 700: Microstructure. Fully heat-treated, showing cubical r'. 6800x

Nickel-Sase Superalloys /71

Udimet 700: Time-temperature diagram. Gamma prime particle size vs. temperature and time. From 760 to 1095 °C (1400 to 2000 OF). Volume fraction of gamma prime from 38 to 14%. Composition: Ni - 14.5% Cr - 17.5% Co - 5.1% Mo - 3.7% Ti - 4.1% AI- 0.015% B - 0.08% C. Treatment: Specimens were annealed above the gamma prime solvus temperature at 1175 °C (2150 OF) for 4 h, followed by a fast air cool


2000°F 19S0 oF 1900 0F 18S0 oF 1800 0F 17S0 oF 1700 0F 16S0 oF 1600 0F lHooF IS000F USooF

1000

500

14'10 22'10 27'10 30'10 33,"0 35'10 36'10 38'10 38'10 38'10 38'10 38'10

UOooF 38'10

5

10

TIME (HOURS)

SO

100

500

Udimet 700: Time-temperature-oxidation diagram. Isoreactivity plots for constant amount of subscale damage. Note: complete reversal of behavior at 1040 °C (1900 OF) and absence of internal oxidation atthis temperature. Composition: Ni -15.0% Cr- 0.15% Fe -19.0% Co - 5.15% Mo· 3.49% Ti - 4.45% AI - 0.10% Si - 0.10% Mn - 0.028% B • 0.06% C. Treatment: 0.5-in. diam rod, solution annealed at 1177 °C (2150 OF) for 4 h, aged at 1080 °C (1975 OF) for 4 h + at 845°C (1550 OF) for 24 h and at 870°C (1600 OF) for 16 h

LIVE GRAPH

Click here to view 2200

2000

1.0A.D. ______

~----========1800

c~-~

1.0 A.D.

................

A.D.-ALLOY DEPLETION MIl/SIDE X.O. INTERNAL OXI DATION MILISIDE 1600

\0

T1M~

HOURS

100

----1000

72/ Heat Treater's Guide: Nonferrous Alloys

Udimet 700: Time-temperature-oxidation diagram. Simplified summary of the four main stages of oxidation. Composition: Ni - 15.0% Cr - 0.15% Fe - 19.0% Co - 5.15% Mo - 3.49% Ti - 4.45% AI - 0.10% Si - 0.10% Mn - 0.028% B - 0.06% C. Treatment: 0.5-in. diam rod. solution annealed at 1175 °C (2150 OF) for4 h, aged at 1080 °C (1975 OF) for4 h + 845°C (1550 OF) for 24 hand at 870 °C (1600 oF)for16 h


CrZ03+ Ni Crz04 + Ni0

2000

--- --- -

A1z03+ Ti N

LEGEND: (1) = linear growth rate (2) and (3) = parabolic growth rate (4) where weight gain reaches a constant value in some 1000 min Numerator = the scale constituents present Denominator = the products of internal oxidation

=

CD 1800

1600'---------L-----....I---.l....----.L.--....:....----' 10,000 10 1000 100 MINUTES

Udimet 700: Time-temperature diagram. Minor phase concentration as a function of aging temperature. Nominal composition: Ni 0.08% C - 15.0% Cr - 18.5% Co - 5.2% Mo - 3.5% Ti - 4.3% AI- 0.030% B. Treatment: Bar stock specimens were solution treated at 1175 °C (2150 OF) for 6 h, aged at 760 to 1150 °C (1400 to 2100 OF) for varying times Very Abundant

r - -.........- - , . - - - - - , , . - - - . - - , - - - - - , - - - - r - - , - - - - - - ,

Abundant d

o

~...

~

Medium

o

o ~ ..;

:k~c~\

Rare

/

Very Rare

\

°

I

\

Sigma

I>~\ 0, \

\

Me

'\

I I MgB2 \\ rrr::__. \, I --+.__.__ 8-L._ _ I I 1400

\ I 1500

1600

1700

1800 Temperature, of

/

1900

l

2000

2100

Udimet 700: Microstructures. (a) Solution annealed at 1175 °C (2150 OF) for 4 to 6 h and then aged 5000 h at 760°C (1400 OF). Replica electron micrograph shows large particle of MC at grain-boundary intersection and t' in grains of y matrix. 4500x. (b) Solution annealed as for (a) and aged for 5000 h at 815°C (1500 OF). Replica electron micrograph shows acicular sigma, carbide (M23C6) at grain boundary, and t' within grains of the y' matrix. 4700x

(a)

(b)


Udimet 710 Chemical Composition. Udimet710 (nominal). 18.00 Cr. 55.00 Ni. 14.80 Co. 3.00 Mo. 1.50 W. 5.00 rt, 2.50 AI. 0.07 C. 1.50 Ta. 0.Ql5 B. O.lOZr

Characteristics

Udimet710: Time-temperature-precipitation diagram. Showing sigma phase formation. U-710 composition: Ni - 0.06% C17.7% Cr - 15.1% Co - 3.0% Mo - 1.4% W - 4.8% Tl - 2.4% AI0.02%8

A nickel-base. precipitation-hardening alloy

o

cs free

(0) Udimet 520

•

(3

prone

N v = 2.40

..

Unitemp AF2-1 DA ChemicalComposition. UnitempAF2-1 DA (nominal). 12.00 Cr. 59.00 Ni. 10.00 Co. 3.00 Mo. 6.00 W. 3.00 Ti. 4.60 AI, Massive GB particles Specimen identification ~ GB and ITB particles • GB, ITB and TB particles

o

o

GB = Grain boundary ITB Incoherent twin boundary TB Coherent twin boundary

= =

Nickel-Base Superalloys I 85

Inconel 600: Time-temperature diagram. Scanning electron microscope evaluation of heat treated specimens. Composition: Ni - 15.6% Cr - 8.1% Fe - 0.2% Ti - 0.03% Mo - 0.03% N - 0.03% Cu - 0.16% AI - 0.040% C - 0.27% Si - 0.13% Mn. Grain size: ASTM 6-7. Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF). Etchant: 10% Br-Ch 30H

Inconel 600: Time-temperature diagram. Intercrystalline corrosion susceptibility. Test conditions: 45 h boiling in solution of 21 g Fe2(S04)3 + 100 mL H2S04 + 400 mL H20, followed by bend test and SEM. Composition: Ni - 15.6% Cr - 8.1% Fe - 0.2% Ti 0.03% Mo - 0.03% N - 0.03% Cu - 0.16% AI- 0.040% C - 0.27% Si - 0.13% Mn. Grain size: ASTM 6-7. Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF)

1000 1000 900

.

4 ..

0

fj< ~- 700

i . ..

600

j

3

2

900

1'\ V 800

,.

.lII 1'\ V .lII 1'\ ,,,,",

. "'

a.lll 1'\

1"...

0

0

i

~cu

~

'\ .J

cu

E-o 600

...

~

"lil

... ~

..

=

6.l11 1'\ I'"

"lil

500

700

::l

9 .. ~

IS ..

... II'

..

"lilcu

1'\

E-o

'Il II'

"lilcu

500

= 350

121'~'\

51''''

400

"

"'"

,.,

400

0,1

10

100

Heat treatment time, h

1000

t---+----{

10000 350'---~--~---~--...J.~-~~-~_ 0,1 1000 10000

LEGEND:

o No precipitate ~ Fine GB particles () Massive GB particles e GB and ITB particles • GB, ITB and TB particles

GB ITB TB

= Grain boundary = Incoherent twin boundary = Coherent twin boundary LIVE GRAPH Click here to view

LEGEND:

o No attack ~

GB etching GB fissuring II GB cracking • Disintegration

e

GB = Grain boundary ITB Incoherent twin boundary TB Coherent twin boundary

= =


1000

Inconel 600: Time-temperature diagram. Transmission electron microscope evaluation of heat treated specimens. Composition: Ni - 15.6% Cr - 8.1% Fe - 0.2% Ti - 0.03% Mo - 0.03% N - 0.03% Cu 0.16% AI - 0.040% C - 0.27% Si - 0.13% Mn. Grain size: ASTM 6-7. Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF). Carbon-extraction replicas of Br-methanol etched transverse cross sections of tube specimens

4~ 00

00

t"\ ...V

... 1"\1.1

3 ....

2~

8 ....

....

.,1"\

1'\

,~

6.

.....

400

350

13....

'"

"\

16 .t1111 "\

,,,. '\

I 'I

100

5

0,1

.... .,

1'\

"

10

1000

10000

Heat treatment time, h

LEGEND:

e> Very fine GB particles ()

Coarse or dendritic GB particles No precipitate except globular MC x or M(C, N) particles Q GB and ITB particles

o

GB ITB TB

= Grain boundary = Incoherent twin

boundary

= Coherent twin boundary

2200 ,--------r--------r-------r-----.....,.. 1200

Inconel 600: Time-temperature-carbideprecipitation diagram. Nominal composition: Ni - 0.08% C - 0.5% Mn - 8% Fe 0.25% Cu - 15.5% Cr. Treatment: Solution treated at 1150 °C (2100 OF) for 30 min, before exposure to precipitation temperatures

2100 ~_-----11100

2000 1900 ~

woo u

1800

°

0

Ql

1700 900

I-< ~

u

1600

Ql

P-

eQl f-4

III I-
t-

el

...a:

4.

2 ~ 1200

"

t-

C(

a: ~

:I ~ 1200

I(

109.8

133.1 1132.211( A 1133.91

el

z

G C(

124.5 X 1124.51

10

20

30

40

50

60 70 80 AGING TIME - HOURS

90

100

110

120

130


Inconel625: Time-temperature-aging diagram. Contours of equal yield strength (ksi). Composition: 60.96% Ni - 0.02% C - 0.12% Mn - 0.31% Si - 21.94% Cr - 3.82% Fe - 8.94% Mo - 3.47% Nb+Ta - 0.21% AI- 0.20% Ti - 0.06% Co - 0.001% B. Treatment: Hot-rolled, aged as shown

x- OBSERVED YIELD

STRENGTH ICALCULATED YIELD STRENGTH1 ll. - CALCULATED MAXIMUM YIELD STRENGTH


_.-------X~6-----II 98.6

__

... ". 1300 tal II:

••

...="

~ ~1128.11

~

tal

~

~

:::: =

--"ljjjI05i6.UO~IJx~I~06~.9!:======:;;:;~~~~====:::::::: 1110.71 X 109.8 X

1200

1"~·761 II...

\!)

z

l

129.0 X 12~.8 127.0 130.7 130

120

111~X==-

iii c(

20

30

40

so

60

70

lI.

1133.91

_

124.~ X 1124.51

--.:~~~

114.2

10

133.1 X 1132.21

80

110

100

110

120

130

AGING TIME - HOURS

Inconel 625: Time-temperature-precipitation diagram. Lower gamma double prime limit determined by hardness measurements. Nominal composition: Ni - 0.06% C - 3% Fe - 21.5% Cr - 9% Mo - 4% Nb. Treatment: Solution annealed, then aged 2000

LIVE GRAPH

-- ---

~---~ ,. Cb(C.NI ce IC.N) Rare

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1800

1100 (M6C 2

1000

/

I

, I

fa
~

~... \/A-286

250

~":-.

T-;--;---c:=\:+------+-----f-------+-------1

.;., Haynes 188\

\ / ". ~'" ••••.~::-........ •• _ :..

.....-Incoloy MA 956

/'

.. _

7.3

N-155

o'--

-l..-

650

750

--'-

---I.

850

""""-,-'"

950

.l--

1050

---J

0

1150

Temperature. 'C

Haynes 188: Microstructure. Solution annealed at 1175 °C (2145 OF) and aged 3400 hat 650°C (1200 OF). Structure is MsC and M23Cs particles in a fcc matrix. Electrolytic: HCI and H20 2. 500x

Haynes 188: Microstructure. Solution annealed at 1175 °C (2145 OF) and aged 6244 h at 870°C (1600 OF). Structure is M23Cs, Laves phase, and probably MsC in a fcc matrix. Electrolytic: HCI and HP2' 500x

Cobalt-Base Superalloys /105

Haynes 188: Oxidation resistance. (a) In dry air for Haynes 188 versus Hastelloy X and L-605 alloys showing continuous penetration from original thickness. (b) Static values at 1100 °C (2010 OF) in air with 5% water vapor

Temperature, 'F

1600 ~ 75 :Q! 84 [ 50

.g, 38 ~

~

1700

1800

I I L-605........

~ 0 870

"......

- --

25 ......... 13

...v I 925

2100 3.0 ~ ...l 2.5 ~ /1 /Ha~elloyX 2.0 'E 1.5

1900

980

2000

J,.V

I

g

Ha~es 188

I 1035

1095

1,0 .~

0.5

~

o

~

1150

Temperature, 'C

(e)

320

0.50

180

0.25 N

Incoloy MA 956

E

..§

Cl

E

g -0.25

c:

0>

c:: 'N

c:: 'N

El200 In

650

c::

:;::l

'Vi c:: Q)

V)

V)

600

1100

550

1000 1.0 10.0 Time atTemperature, h

100.0

Iron-Base Superalloys /113

Incoloy 800: Intercrystalline corrosion susceptibility. Test conditions: 45 h boiling in solution of 250 mL H2S04 + 100 g CuS04 + 750 mL H20, followed by bend test and SEM evaluation. Composition: Fe - 31.1% Ni - 21.4% Cr - 0.90% Mn - 0.28% Si 0.037% C - 0.02% N - 0.01% P - 0.007% S - 0.5% AI - 0.3% Ti. Grain size: ASTM 7-8. Treatment: Mill annealed specimens . aged at 400 to 800°C (750 to 1470 OF)

Incoloy 800: Transmission electron microscope evaluation of heat treated specimens. Composition: Fe - 31.1% Ni 21.4% Cr - 0.90% Mn - 0.28% Si - 0.037% C - 0.02% N - 0.01% P - 0.007% S - 0.5% AI- 0.3% Ti. Grain size: ASTM 7-8.Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF). Carbon-extraction replicas of Sr-methanol etched transverse cross sections of tube specimens 1000

1000

900 900 000 000

0

0

~

0 700

.8-

4 ..

II

31 L,J

1il

~

...

Eo

.>
:

600

800

Heat-treating temperature, °C


LIVE GRAPH

LIVE GRAPH

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Click here to view

Monel R·405 Chemical Composition (nominal). 66.00 Ni, 0.8 C, 0.90 Mn, 1.35 Fe, 0.15 Si, 31.5 Cu, 0.04 S

Characteristics Free machining version of alloy 400. Sulfide inclusions act as chip breakers in machining. Applications include meter and meter valve parts, fasteners, and screw machine products. Alloy is not stress relieved or stress equalized

Recommended Heat Treating Practice Soft Annealing. R-405 is annealed in continuous and batch furnaces. Temperatures, times at temperature, and cooling methods vary by type of furnace: • In continuous furnaces, parts are annealed at 870 to 980°C (1600 to 1795 "F) for 30 sec to 15 min, and cooled in air or water • In batch furnaces, parts are annealed at 760 to 815 °C (1400 to 1500 "F) for 1 to 3 h, and water quenched

Monel K·500 Chemical Composition (nominal). 65.00 Ni, 0.15 C, 0.60 Mn, 1.00 Fe, 0.15 Si, 29.5 Cu, 0.50 Ti, 2.80 Al

Characteristics A precipitation-hardenable, nickel-copper alloy that combines corrosion resistance of alloy 400 with greater strength and hardness. Also has low permeability and is nonmagnetic under -100°C (-150 OF). Applications: Pump shafts, oil well tools and instruments, doctor blades and scrapers, springs, valve trim, fasteners, and marine propeller shafts

Recommended Heat Treating Practice Solution Heat Treating. Alloy is treated at 980 °C (1795 "F) for 30 min to 1 h, and water quenched Age Hardening Treatment. Parts are heated to 595°C (1100 oF), held for 16 h; furnace cooled to 540°C (1000 "F), held 6 h; furnace cooled to 480°C (900 "F), held 8 h; and air cooled

Aluminum Alloys

Heat Treating Aluminum Alloys Not all aluminum alloys are heat treatable. Generally, only the precipitation hardenable wrought and cast alloys are heat treated (to increase strength and hardness). The strength of the nonheat treatable alloys is upgraded primarily via cold work. Heating and cooling do little to increase their strength. Both types of alloys are annealed (to reduce strength and to increase ductility). Typical practices are summarized in the graphics that follow: • Fig. I, an aluminum-copper phase diagram. identifies temperature ranges for annealing, precipitation hardening, and solution treating • Table l(a) provides information on typical solution and precipitation heat treatments for commercial mill products with copper alloying, namely:

1. 2. 3. 4.

Aluminum-copper alloys without magnesium alloying Aluminum-copper-magnesiumalloys Aluminum-copper-magnesium-silicon alloys Aluminum-copper-lithiumalloys

• Table I (b) provides typical solution and precipitation heat treatments for magnesium-silicon alloys (6xxx series) • Table 1(c) provides typical solution and precipitation heat treatments for zinc-magnesium alloys from 7xxx series • Table 2 provides soak times and maximum quench delays for the solution treatment of wrought alloys • Table 3 provides typical heat treatments for sand and permanent mold alloy die castings

Tablela Typical solution and precipitation heat treatments for commercial heat-treatable aluminum alloy mill products with copper alloying

Alloy

Product form

Solutionheallrealment(.) Thmper Melllliempemlure(h) OF -c designation

1're

0,,_

E ~

570 660 750 1.0 0.8 I - - -

1000

1000

!;l-

la)

~

0

0.016 0.020 0,025 0.032 0.040

Ma>imum quencb de"}',. Aklad Nonclad

6.4 8.0 10.0 12.8 20.0

4.4 5.5 6.8 8.8 11.0

1.2 1.0

- 0.8

~

c:

- 0.6 ~ - 0.4 iii

- 0.2 0

400 450 500 550 600 Temperature, °C LIVE

GRAPH

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last corner of the load is immersed in the water quench tank." Recommended maximum quench-delay times are listed in Table 2. However, exceeding the maximum delay time is permitted if temperature measurements of the load prove that all parts are above 415°C (775 "F) when quenched. The C-curves used in quench-factor analysis can also assist in determining a maximum allowable delay. Water-immersion quenching normally is controlled in practice by stipulating maximum quench-delay time and maximum water temperature. The first requirement controls the cooling rate during transfer and, for high-strength alloys, often is based on the criterion of complete immersion before the metal cools below 415°C (775 OF). This speciftcationof 415°C (775 OF) is based on a critical temperature for alloy 7075, which has one of the more severe C-curves (Fig. 4). Therefore, the criterion for complete immersion of other alloys might be based on a temperature lower than the 415°C (775 OF) specification, depending on the characteristics of the particular C-curve. The second requirement controls the cooling rate during immersion. MlL-H-6088 speciftes that for water-immersion quenching, except quenching of forgings and castings, the temperature of the water shall not exceed 38°C (110 "F) upon completion of quenching. This requirement controls both the temperature of the quench water prior to immersion and the ratio of the combined mass of load and rack to the volume of water. However, to ensure adequate quenching effectiveness, it is necessary also

that the cooling fluid flow past all surfaces of each part during the first few seconds after immersion. Before parts enter the furnace, their placement in racks or baskets should be compatible with this requirement. During the first few seconds of quenching, agitation of the parts or the water should be sufficient to prevent local increases in temperature due to the formation of steam pockets. Spray Quenching. For spray quenching, the quench rate is controlled by the velocity of the water and by volume of water per unit area per unit time of impingement of the water on the workpiece. Rate of travel of the workpiece through the sprays is an important variable. Forming and Straightening after Quenching. Immediately after being quenched, most aluminum alloys are nearly as ductile as they are in the annealed condition. Consequently, it is often advantageous to form or straighten parts in this temper. Moreover, at the mill level, controlled mechanical deformation is the most common method of reducing residual quenching stresses. Because precipitation hardening will occur at room temperature, forming or straightening usually follows as soon after quenching as possible. In addition, maximum effectiveness in stress relief is obtained by working the metal immediately after quenching.

Age Hardening After solution treatment and quenching, hardening is achieved either at room temperature (natural aging) or with a precipitation heat treatment (artificial aging). In some alloys, sufficient precipitation occurs in a few days at room temperature to yield stable products with properties that are adequate for many applications. These alloys sometimes are precipitation heat treated to provide increased strength and hardness in wrought or cast products. Other alloys with slow precipitation reactions at room temperature are always precipitation heat treated before being used. In some alloys, notably those of the 2xxx series, cold working of freshly quenched material greatly increases its response to later precipitation heat treatment. Mills take advantage of this phenomenon by applying a controlled amount ofrolling (sheet and plate) or stretching (extrusion, bar, and plate) to produce higher mechanical properties. However, if the higher properties are used in design, reheat treatment must be avoided.

Aluminum /139

Fig. 4 Time-temperature-property curves at 95% of maximum tensile stress for various alloys . 1110

600


- --

500

930

~ ~ -:::. :: :. ~.~-~-~-~_:-:--;-

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759

400

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570

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200 A: 7075 100 r--- B: 2017 c. 6061 D: 6063

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100

10

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32

103

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Yield strength. ksi

50

65

60 I

70

707~.T6

I

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Fig. 5 Comparison of distribution of yield strength in heattreated 7075-T6 clad sheet product with distribution in a single sheet. A is 95% probability that not more than 1% of all material will fall below this value; B is 95% probability that not more than 10% of all material will fall below this value. (A and B refer only to curve representing 4290 routine mill tests.)

75

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475

500

525

Yield strength, MPa

Natural Aging. The more highly alloyed members of the 6xxxwrought series, the copper-containing alloys of the Txxx group, and all of the 2xxx alloys are almost always solution heat treated and quenched. For some of these alloys-particularly the 2xxxalloys-the precipitation hardening that results from natural aging alone produces useful tempers (1'3 and T4 types) that are characterized by high ratios of tensile to yield strength and high fracture toughness and resistance to fatigue. For the alloys that are used in these tempers, the relatively high supersaturation of atoms and vacancies retained by rapid quenching causes rapid formation of GP zones, and strength increases rapidly, attaining nearly maximum stable values in four or five days. Tensile-property specifications for products in 1'3- and T4type tempers are based on a nominal natural aging time of four days. In alloys for which 1'3- or T4-type tempers are standard, the changes that occur on further natural aging are of relatively minor magnitude, and products of these combinations of alloy and temper are regarded as essentially stable after about one week. In contrast to the relatively stable condition reached in a few days by 2xxx alloys that are used in 1'3- or T4-type tempers, the 6xxx alloys and to an even greater degree the 7xxx alloys are considerably less stable at room temperature and continue to exhibit significant changes in mechanical properties for many years.

Temperature control and uniformity present essentially the same problems in precipitation heat treating as they do in solution heat treating. Good temperature control and uniformity throughout the furnace and load are required for all precipitation heat treating. Recommended temperatures are generally those that are least critical and that can be used with practical time cycles. Except for 7xxx alloys in TIx tempers, these temperatures generally allow some latitude and should have a high probability of meeting property specification requirements. Furnace radiation effects seldom are troublesome except in those few furnaces that are used for both solution and precipitation heat treating. Generally, such situations should be avoided, because the high heat capacity needed for the higher temperatures may be difficult to control at normal aging temperatures. Soak time in precipitation heat treating is not difficult to control; the specified times carry rather broad tolerances. Heavier loads with parts racked closer together, and even nested, are not abnormal. The principal hazard is undersoaking due to gross excesses in loading practices. Some regions of the load may reach soak temperature long after soak time has been called. Placement of load thermocouples is critical, and limiting the size and spacing of a load may be necessary for aging to the TI3 and TI6 tempers. Soak time is not as critical for peak-aged (T6 and TB) tempers.

140 I Heat Treater's Guide: Nonferrous Alloys

Hardening of Cast Alloys In general, the principles and procedures for heat treating wrought and cast alloys are similar. The major differences between solution-treating conditions for castings and those for wrought products are found in soak times and quenching media. Solution of the relatively large microconstituents present in castings requires longer soaking periods than those used for wrought products (fable 3). When heat treatment of castings must be repeated, solution times become similar to those for wrought products, because gross solution and homogenization have been completed and are irreversible under normal conditions. Reduction of stresses and distortion from quenching is also important, because castings generally are complex shapes with variations in section thickness. Quenchants. Quenching of castings is often in boiling water or a milder medium to reduce quenching stresses in complex shapes. A commercially important variety is a mixture of polyalkylene glycol and water, which has no detrimental effect on properties for thicknesses under ap-

proximately 3.2 mm (0.125 in.). Quenchant additions can be made for the following purposes: • To promote stable vapor film boiling by the deposition of compounds on the surface of parts as they are submerged in the quench solution • To suppress variations in heat flux by increasing vapor ftlm boiling stability through chemically decreased quench solution surface tension • To moderate quench rate for a given water temperature Tempers. Cast products of heat-treatable alloys have the highest combinations of strength, ductility, and toughness when produced in T6-type tempers. Developing T6-type tempers in cast products requires the same sequence of operations employed in developing tempers of the same type in wrought products-solution heat treating, quenching, and precipitation heat treating. Premium-quality casting specifications such as MlL-A-21180 can require different strengths and ductility levels in the same casting.

Stress Relief Immediately after being quenched, most aluminum alloys are nearly as ductile as they are in the annealed condition. Consequently, it is often advantageous to stress relieve parts by working the metal immediately after quenching. Numerous attempts also have been made to develop a thermal treatment that will remove, or appreciably reduce, quenching stresses. Normal precipitation heat-treating temperatures are generally too low to provide appreciable stress relief. Exposure to higher temperatures (at which stresses are relieved more effectively) results in lower properties. However, such treatments are sometimes utilized when even moderate reduction of residual stress levels is important enough so that some sacrifice in mechanical properties can be accepted. The T7 temper for castings is a typical example of this kind of treatment. Mechanical Stress Relief. Deformation consists of stretching (bar, extrusions, and plate) or compressing (forgings) the product sufficiently to achieve a small but controlled amount (l to 3%) of plastic deformation. If the benefits of mechanical stress relieving are needed, the user should refrain from reheat treating. Specific combinations of the supplemental digits are used to denote the tempers produced when mechanical deformation is used primarily to relieve residual stresses induced during the quenching operation. For products stress relieved by stretching, the digits 51 follow the basic Tx designation (f451, for example). For products stress relieved by compressive deformation, the supplementary digits are 52. An additional digit is added to designations for extrusions: an added zero specifies that the product has not been straightened after final stretching; an added one indicates that straightening may have been performed after fmal stretching.

Effect of Precipitation Heat Treating on Residual Stress. The stresses developed during quenching from solution heat treatment are reduced during subsequent precipitation heat treatment. The degree of relaxation of stresses is highly dependent upon the time and temperature of the precipitation treatment and the alloy composition. In general, the precipitation treatments used to obtain the T6 tempers provide only modest reduction in stresses, ranging from about 10 to 35%. To achieve a substantial lowering of quenching stresses by thermal stress relaxation, highertemperature treatments of the T7 type are required. These treatments are used when the lower strengths resulting from overaging are acceptable. Other thermal stress-relief treatments, known as subzero treatment and cold stabilization, involve cycling ofparts above and below room temperature. The temperatures chosen are those that can be readily obtained with boiling water and mixtures of dry ice and alcohol-namely, 100 and-73°C (212 and-loo °F)-and the number of cycles ranges from one to five. The maximum reduction in residual stress that can be effected by these techniques is about 25%. The maximum effect can be obtained only if the subzero step is performed first, and immediately after quenching from the solution-treating temperature while yield strength is low. No benefit is gained from more than one cycle. A 25% reduction in residual stress is sometimes sufficient to permit fabrication of a part that could not be made without this reduction. However, if a general reduction is needed, as much as 83% relief of residual stress is possible by increasing the severity of the uphill quench-that is, more closely approximating the reverse of the cooling-rate differential during the original quench.

Effects of Reheating The precipitation characteristics of aluminum alloys must be considered frequently during evaluation of the effects ofreheating on mechanical properties and corrosion resistance. Such evaluations are necessary for determining standard practices for manufacturing operations, such as hot forming and straightening, adhesive bonding, and paint and dry-film lubricant curing, and for evaluation the effects of both short-term and long-term exposure in elevated temperatures in service.

The stage of precipitation that exists in an alloy at the time ofreheating plays a significant role in the effects of reheating. Consequently, it is extremely dangerous to reheat material in a solution heat-treated temper without first carefully testing the effects of such reheating. In one such test, 2024-T4 sheet was found to be very susceptible to intergranular corrosion when subjected to a 15-min drying operation at 150°C (300 OF) during the first 8 h after quenching; no susceptibility was evident when the same drying operation was performed more than 16 h after quenching.

Aluminum /141

Annealing Annealing treatments are of several types that differ in objective. Annealing times and temperatures depend on alloy type as well as on initial structure and temper. Full Annealing. The softest, most ductile, and most workable condition of both nonheat-treatable and heat-treatable wrought alloys is produced by full annealing to the temper designated "0." For both heat-treatable and non-heat-treatable aluminum alloys, reduction or elimination of the strengthening effects of cold working is accomplished by heating at a temperature from about 260 to about 440°C (500 to 825 "F). The rate of softening is strongly temperature-dependent; the time required to soften a given material by a given amount can vary from hours at low temperatures to seconds at high temperatures. If the purpose of annealing is merely to remove the effects of strain hardening, heating to about 345°C (650 oF) will usually suffice. If it is necessary to remove the hardening effects of a heat treatment or of cooling from hot-working temperatures, a treatment designed to produce a coarse,

widely spaced precipitate is employed. This usually consists of soaking at 415 to 440°C (775 to 825 "F) followed by slow cooling (28 °CIh, or 50 °FIh, max) to about 260°C (500 oF). The high diffusion rates that exist during soaking and slow cooling permit maximum coalescence of precipitate particles and result in minimum hardness. In annealing, it is important to ensure that the proper temperature is reached in all portions of the load; it is common to specify a soaking period of at least 1 h. The maximum annealing temperature is moderately critical;

Table 4b Typical full annealingtreatments for some common wrought aluminumalloys These treatments, which anneal the material to the 0 temper, are typical for various sizes and methods of manufacture and may not exactly describe optimum treatments for specific items. Metaltempemture Alloy

Table 4a Typical annealingtreatments for aluminum alloymill products Alloy

1060 1100 1145 1235 1345 1350 2014 2017 2024 2117 2219 3003 3004 3005 3105 5005 5050 5052 5056 5083 5086 5154 5254 5454 5456 5457 5652 6005 6053 6061 6063 6066 7072 7075 7175 7178 7475 Brazing Sheet: Nos. 11& 12 Nos. 23&24

MetaJ tempemture OF

Approximate timeat Iempemture bours

deslgoalion

Thmper

650 650 650 650 650 650 775(b) 775(b) 775(b) 775(b) 775(b) 775 650 775 650 650 650 650 650 650 650 650 650 650 650 650 650 775(b) 775(b) 775(b) 775(b) 775(b) 650 775(c) 775(c) 775(c) 775(c)

(a) (a) (a) (a) (a) (a) (b)(c) (b)(c) (b)(c) (b)(c) (b)(c) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (b)(c) (b)(c) (b)(c) (b)(c) (b)(c) (a) (b)(c) (b)(c) (b)(c) (b)(c)

0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0

650 650

(a) (a)

0 0

(a)TImein the furnaceneednot be longerthan necessarytobring allpartsofload to annealingtemperature.Rateof coolingis unimportant.(b)These treatmentsare intendedto removeeffectsof solutionheattreatmentandincludecoolingat rateof about50 OF perhourfromtheannealingtemperature to 500 oF-The rate of subsequentcooling is unimportant. Treatmentat 650 OF, followed by uncontrolledcooling,may be usedto removetheeffectsof cold work,or topartiallyremovethe effectsof heattreatment.(c)ThIstreatmentisintendedto removetheeffectsofsolutionheatlreatment and includescoolingat an uncontrolledrateto 400 OF or less, followedbyreheatingto 450 OF for 4 h. Treatmentat 650 OF, followedby uncontrolledcooling,may be usedto removetheeffectsof cold work, or to partiallyremovethe effectsof heattreatment.

1060 1100 1350 2014 2017 2024 2036 2117 2124 2219 3003 3004 3105 5005 5050 5052 5056 5083 5086 5154 5182 5254 5454 5456 5457 5652 6005 6009 6010 6053 6061 6063 6066 7001 7005 7049 7050 7075 7079 7178 7475 Brazing sheet No. Hand 12 No.21 and22 No.23 and24

OC

OF

Appromnate tbneat Iempemture, b

345 345 345 415(b) 415(b) 415(b) 385(b) 415(b) 415(b) 415(b) 415 345 345 345 345 345 345 345 345 345 345 345 345 345 345 345 415(b) 415(b) 415(b) 415(b) 415(b) 415(b) 415(b) 415(c) 345(d) 415(c) 415(c) 415(c) 415(c) 415(c) 415(c)

650 650 650 775(b) 775(b) 775(b) 725(b) 775(b) 775(b) 775(b) 775 650 650 650 650 650 650 650 650 650 650 650 650 650 650 650 775(b) 775(b) 775(b) 775(b) 775(b) 775(b) 775(b) 775(c) 650(d) 775(c) 775(c) 775(c) 775(c) 775(c) 775(c)

(a) (a) (a) 2-3 2-3 2-3 2-3 2-3 2-3 2-3 (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3

345 345 345

650 650 650

(a) (a) (a)

(a) 'lime in the furnaceneed not be longerthan necessaryto bring alI parts of the load to annealing temperature. Coolingrate isunimportant. (b)These treatments areintendedtoremovetheeffectsof solutiontreatmentand includecoolingat a rate of aboUl300C/h (50°FIb)from the annealingtemperatureto 260 "C (500 oF). Rate of subsequentcooling is unimportant. Treatmentat 345°C (650 oF), followedby uncontrolled cooling,may be used toremove the effectsof cold work or to partly removetheeffectsof heat treatment. (c)Thesetreatmentsareintendedto removetheeffectsof solution treatmentand includecoolingat an uncontrolledrateto205°C (400 oF) or less,followedbyreheatingto 230°C (450 oF) for 4 h. Treatmentat 345 "C(650 oF), followedby uncontrolledcooling, maybe usedtoremovethe effectsof cold workor to partlyremovetheeffectsof heattreatment. (d) Coolingrate to205 DC (400 OF) or belowis less than orequal to 30 0C/h (50 °FIb)


it is advisable not to exceed 415°C (775°F), because of oxidation and grain growth. The heating rate can be critical, especially for alloy 3003, which usually requires rapid heating for prevention of grain growth. Relatively slow cooling, in still air or in the furnace, is recommended for all alloys to minimize distortion. Typical annealing conditions used for some alloys in common use are listed in Tables 4a and b. Partial Annealing. Annealing of cold-worked non-heat-treatable wrought alloys to obtain intermediate mechanical properties (H2-type tempers) is referred to as partial annealing or recovery annealing. Bendability and formability of an alloy annealed to an H2-type temper generally are significantly higher than those of the same alloy in which an equal strength level is developed by a final cold-working operation (HI-type temper). Treatments to produce H2-type tempers require close control of temperature to achieve uniform and consistent mechanical properties. Stress-Relief Annealing. For cold-worked wrought alloys, annealing merely to remove the effects of strain hardening is referred to as stress-relief annealing. Such treatments employ temperatures up to about 345°C (650 "F), or up to 400 ± 8°C (750 ± 15 "F) for 3003 alloy, and cooling to room temperature. No appreciable holding time is required. Such treatment may result in simple recovery, partial recrystallization, or full recrystallization. Age hardening may follow stress-relief annealing of heat-treatable alloys, however, because a concentration of soluble alloying

elements sufficient to cause natural aging remains in solid solution after such treatments. Controlled-Atmosphere Annealing and Stabilizing. Aluminum alloys that contain even very small amounts of magnesium will form a surface magnesium oxide unless the atmosphere in the annealing furnace is free ofmoisture and oxygen. Examples include alloy 3004, which is used for cooking utensils, and alloys of the 5xxx series. Another problem that control of the annealing atmosphere helps to overcome or avoid is oil staining by oil-base roll lubricants that do not burn off at lower annealing temperatures. If the oxygen content of the furnace atmosphere is kept very low during such annealing, the oil will not oxidize and stain the work. Temperature control for full and partial annealing is somewhat more critical than for stress-relief annealing; the temperatures and times specified are selected to produce recrystallization and, in the case of heat-treatable alloys, a precipitate of maximum size; for this the cooling rate must be closely controlled. Annealing of castings for 2 to 4 h at temperatures 315 to 345°C (600 to 650 OF) provides the most complete relief of residual stresses and precipitation of the phases formed by the excess solute retained in solid solution in the as-cast condition. Such annealing treatments provide maximum dimensional stability for service at elevated temperatures. The annealed temper is designated "0."

Grain Growth Many aluminum alloys in common use are subject to grain growth during solution treatment or annealing. This phenomenon can occur during or after recrystallization of material that has been subjected to a small critical amount of prior cold work. It is usually manifested by surface roughening during subsequent fabrication operations and frequently results in rejections for appearance or functional reasons. Less frequently, some deterioration of mechanical properties is encountered, and this is undesirable regardless of surface-roughening effects. When a grain-growth problem is discovered, it is too late to change the condition of the parts in question, but several methods are available for preventing recurrence of the difficulty. The simplest of these is relieving

the causative stress by interjecting a stress-relief anneal into the manufacturing sequence immediately prior to the solution-treating or full-annealing cycle in which the grain growth occurred. This approach is usually successful and practical. Another possibility is to adjust the amount of stress present in the part immediately prior to the critical heat treatment so that the stress level is outside the critical range. This may be done by adding a cold-working operation before forming, such as prestretching of blanks, or by forming in multiple stages with a stress-relief anneal before each stage. A third method that is sometimes successful consists of increasing the heating rate during the critical heat treatment by reducing the size of furnace loads or by changing from an air furnace to a salt bath.

Dimensional Changes during Heat Treatment Distortion as a result of creep during solution heat treatment should be avoided by proper loading of parts in baskets, racks, or fixtures, or by provision of adequate support for long pieces of plate, rod, bar, and extrusions heat treated in horizontal roller hearth furnaces. Sheet is provided with air-pressure support in continuous heat-treating furnaces to avoid scratching, gouging, and distortion. If parts are to be solution heat treated in fixtures or racks made of materials (such as steel) with coeffi-

cients of thermal expansion lower than that of the aluminum being treated, allowance should be made for this differential expansion to ensure that expansion of the aluminum is not restricted. Straightening immediately after solution heat treating may be preferable to fixturing, Solution of phases formed by major alloying elements causes volumetric expansion or contraction, depending on the alloy system, and this may have to be taken into account in heat treatment of long pieces.

Quality Assurance Tensile Tests. In general, the relatively constant relationships among various properties allow the use of tensile properties alone as acceptance criteria. The minimum guaranteed strength is ordinarily that value above which it has been statistically predicted with 95% probability that 99% or

more of the material will pass. The inherent variability within lots and among specimens from a given piece is shown in Fig. 5. Hardness. Tests are less valuable for acceptance and rejection of heat-treated aluminum alloys than they are for steel. Nevertheless, hard-

Aluminum /143 ness tests have some utility for process control. Typical hardness values for various alloys and tempers are given in Table 5. Figure 6 shows the general relationship between longitudinal tensile strength and hardness for aluminum alloys. Electrical Conductivity. For control of the corrosion and stress-corrosion characteristics of certain tempers, notably the 1'73 and 1'76 types, the material must meet combination criteria of yield strength plus electrical conductivity. Low tensile strengths may be accompanied by high levels of electrical conductivity, so electrical conductivity is sometimes used as a quality-assurance diagnostic tool. However, because the correlation between strength and electrical conductivity is strongly a function of chemical composition and fabricating practice, use of electrical conductivity is not recommended except for rough screening, which must be followed by hardness testing, and then by tensile testing if the hardness tests indicate that the heat treatment was suspect. Fracture Toughness Indices. Fracture toughness is rarely, if ever, a design consideration in the 1000,3000,4000,5000, and 6000 series alloys. The fracture toughness of these alloys is sufficiently high that thicknesses beyond those commonly produced would be required to obtain a valid test.

Fracture toughness quality control and material procurement minimums are appropriate for controlled-toughness, high-strength alloys. The alloys and tempers currently identified as controlled-toughness, highstrength products include: AnDy

Condltlon

Product rorm

2048 2124 2419 7049 7050 7150 7175 7475

T8 13.T8 T8 T7 T7 T6 T6,T7 T6,T7

Sheetandplate Sheetandplate Sheet,plate,extrusions, andforgings Plate,forgings, andextrusions Sheet,plate,forgings, andextrusions Sheetandplate Sheet,plate,forgings,andextrusions Sheetand plate

The fracture toughness of these alloys and tempers range in measured Klc values from about 20 MPa'.lnl (18 ksi"ln.) upward. Controlled-toughness alloys are often derivatives of conventional alloys.For example, 7475 alloy is a derivative of 7075 with maximum compositional limits on some elements that were found to decrease toughness.

Table 5 Typical acceptable hardness values for wrought aluminum alloys Acceptable hardness does not guarantee acceptable properties; acceptance should be based on acceptable hardness plus written evidence of compliance with specified heat-treating procedures. Hardness values higher than the listed maximums are acceptable provided that the material is positively identified as the correct alloy. Hardness Alloy lindtemper

2014-13,-T4,-T42 2014-T6,-T62,-T65 2014-T61 2024-13 2024-136 2024-T4,-T42(d) 2024-T6,-T62 2024-TSI 2024-TS6 6053-T6 6061-T4(d) 6061-T6 6063-T5 6063-T6 6151-T6 7075-T6,-T65

7079-T6,-T65 7178-T6

Product rorm(o)

HRB

HRE

All

65-70 80-90 81-90

87-95 103-110 104-110 100-109 97-106 91-100 93-102 100-110 97-106 91-100 93-102 99-106 99-106 99-106 105-110 79-87 60-75 70-81

Sheet{b) All others All

Notclad(c) Clad, ~1.60 mm(0.063in.) Clad,>1.60mm(0.063in.) All

Notclad Clad, ~1.60 mm (0.063in.) Clad,>1.60mm (0.063in.) All

Notclad Clad All All

Sheet Extrusions;bar Notclad,0.41 mm (0.016in.) Notclad,~.51 mm (OmOin.) Clad

69-83 52-71 52-71 76-90 69-83 52-71 52-71 74.5-83.5 74.5-83.5 83-90

HR15T

111-118 109-116 109-116

82.5-87.5 80-84.5

111-118 109-116 109-116

85-90 82.5-87.5 80-84.5 84-88 84-88

88-100 82-103

87.5-90 74.5-78.5 64-75 67-78 75-84 78-84

89-97

62.5-70

85-94

85-97 84-96 55-70 70-85 91-102 106-114

78-90 76-90 76-90 73-90 81-93 85 min

102-110 104-110 104-110 102-110 102-110 104-114 105min

87.5-92 88min

102min

86 min

47-72

All All All

Notclad(e) Clad: ~.91 mm (O.036 in.) >0.91s 1.27mm (>0.036s 0.050in.) >1.27~ 1.57mm (>0.050~ 0.062 in.) >1.57s 1.78mm (>0.062~0.070 in.) >1.78mm (0.070in.) All(e) Notclad(t) Clad: ~.91 mm (0.036in.) >0.91 s 1.57mm (>0.036~ 0.062in.) >1.57mm (0.062in.)

HRH

87.5-92 86-90

85 min 88min

(a)Minimumhardnessvaluesshownforcladproductsarevalidforthicknesses up to and including2.31mm(0.091in.);forheavier-gage material,claddingshouldbe locallyremovedforhardnesstestingor test should be perfonnedon edge of sheet. (b) 126to 158HB (lO mm bal, 500kg load).(c) 100to 130HB (10mm ball,500kg load).(d)Alloys2024-T4,2024-T42 and6061-T4shouldnot be rejectedfor lowhardnessuntil theyhaveremainedatroom temperature for at least three daysfollowingsolutiontreatment. (e) 136to 164HB (10 mmball,500kg load).(t) 136HBmin(lOmmball, 500kgload)


600

Fig. 6 Tensile strength versus hardness for various aluminum alloysandtempers

85

550

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500

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60 400

c:

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55 350

50 45 70 80 Hardness. HRB

90

100

Temper Designations for Heat-Treatable Aluminum Alloys Basictemperdesignations for heat-treated conditions include the codes 0, W, and T. Other basic temper designations are F (as fabricated) and H (strain hardened). • 0, annealed. Applies to wrought products that are annealed to obtain lowest strength temper and to cast products that are annealed to improve ductility and dimensional stability. The 0 may be followed by a digit other than zero. • W, solution heat treated. An unstable temper applicable to any alloy that naturally ages (spontaneously ages at room temperature) after solution heat treatment. This designation is specific only when the period of natural aging is indicated-for example, W 1;2 h. (See discussion of the Tx51, Tx52, and Tx54 tempers, in the section below on subdivision of the T temper.) • T, heat treated to produce stable tempers other than O. Applies to products that are thermally treated, with or without supplementary strain hardening, to produce stable tempers. The T is always followed by one or more digits.

MajorSubdivisions of T Temper. In T-type designations, the T is followed by a number from I to 10; each number denotes a specific sequence of basic treatments: • TI, cooled from an elevated-temperature shaping process and naturally aged to a substantially stable condition. Applies to products that are not cold worked after an elevated-temperature shaping process such as casting or extrusion, and for which mechanical properties have been stabilized by room-temperature aging. If the products are flattened or straightened after cooling from the shaping process, the effects of the cold work imparted by flattening or straightening are not recognized in specified property limits. • TI, cooled from an elevated-temperature shaping process, cold worked, and naturally aged to a substantially stable condition. Applies to products that are cold worked specifically to improve strength after cooling from a hot-working process such as rolling or extrusion, and for which mechanical properties have been stabilized by room-temperature aging. The effects of cold work, including any cold work imparted by flattening or straightening, are recognized in specified property limits.

• TI, solution heat treated, cold worked, and naturally aged to a substantially stable condition. Applies to products that are cold worked specifically to improve strength after solution heat treatment, and for which mechanical properties have been stabilized by room-temperature aging. The effects of cold work, including any cold work imparted by flattening or straightening, are recognized in specified property limits. • T4, solution heat treated and naturally aged to a substantially stable condition. Applies to products that are not cold worked after solution heat treatment, and for which mechanical properties have been stabilized by room-temperature aging. If the products are flattened or straightened, the effects of the cold work imparted by flattening or straightening are not recognized in specified property limits. • T5, cooled from an elevated-temperature shaping process and artificially aged. Applies to products that are not cold worked after an elevated-temperature shaping process such as casting or extrusion, and for which mechanical properties or dimensional stability, or both, have been substantially improved by precipitation heat treatment. If the products are flattened or straightened after cooling from the shaping process, the effects of the cold work imparted by flattening or straightening are not recognized in specified property limits. • T6, solution heat treated and artificially aged. Applies to products that are not cold worked after solution heat treatment, and for which mechanical properties or dimensional stability, or both, have been substantially improved by precipitation heat treatment. If the products are flattened or straightened, the effects of the cold work imparted by flattening or straightening are not recognized in specified property limits. • 11, solution heat treated and stabilized. Applies to products that have been precipitation heat treated to the extent that they are overaged. Stabilization heat treatment carries the mechanical properties beyond the point of maximum strength to provide some special characteristic, such as enhanced resistance to stress-corrosion cracking or to exfoliation corrosion. • T8, solution heat treated, cold worked, and artificially aged. Applies to products that are cold worked specifically to improve strength after solution heat treatment, and for which mechanical properties or dimensional stability, or both, have been substantially improved by precipitation heat treatment. The effects of cold work, including any cold work

Aluminum /145 imparted by flattening or straightening, are recognized in specified property limits. • 1'9, solution heat treated, artificially aged, and cold worked. Applies to products that are cold worked specifically to improve strength after they have been precipitation heat treated. • TlO, cooled from an elevated-temperature shaping process, cold worked, and artificially aged. Applies to products that are cold worked specifically to improve strength after cooling from a hot-working process such as rolling or extrusion, and for which mechanical properties or dimensional stability, or both, have been substantially improved by precipitation heat treatment. The effects of cold work, including any cold work imparted by flattening or straightening, are recognized in specified property limits.

Other Subdivisions T Temper Codes for Stress-Relieved Products. When it is desirable to identify a variation of one of the ten major T tempers described above, additional digits, the first (x) of which cannot be zero, may be added to the designation. The following specific sets of additional digits have been assigned to stress-relieved wrought products:

• Tx51, stress relieved by stretching. Applies to the following products when stretched to the indicated amounts after solution heat treatment or after cooling from an elevated-temperature shaping process: Tx51 applies directly to plate and to rolled or cold finished rod and bar. These products receive no further straightening after stretching. Tx51 also applies to extruded rod, bar, shapes, and tubing, and to drawn tubing, when designated as follows: Product Corm

Plate Rod, bar.shapes.extrudedtube Drawntube

Permanent set, %

1.5-3 1-3 0.5-3

• Tx5lO. Products that receive no further straightening after stretching • Tx511. Products that may receive minor straightening after stretching to comply with standard tolerances • Tx52. Stress relieved by compressing. Applies to products that are stress relieved by compressing after solution heat treatment, or after cooling from a hot-working process to produce a permanent set of 1 to 5% • Tx54. Stress relieved by combining stretching and compressing. Applies to die forgings that are stress relieved by restriking cold in the finish die. (These same digits-and 51, 52, and 54-may be added to the designation W to indicate unstable solution heat-treated and stress-relieved tempers) Temper designations T42 and T62 apply to wrought products heat treated from the 0 or the F temper to demonstrate response from the heat treatment described below. Temper designations T42 and T62 also may be applied to wrought products heat treated from any temper by the user when such heat treatment results in the mechanical properties applicable to these tempers. • T42. Solution heat treated from the 0 or the F temper to demonstrate response to heat treatment and naturally aged to a substantially stable condition • T62. Solution heat treated from the 0 or the F temper to demonstrate response to heat treatment and artificially aged

Subdivision of the 0 Temper. In temper designations for annealed products, a digit following the 0 indicates special characteristics. For example, 01 denotes that a product has been heat treated according to a time/temperature schedule approximately the same as that used for solution heat treatment, and then air cooled to room temperature, to accentuate ultrasonic response and provide dimensional stability; this designation applies to products that are to be machined prior to solution heat treatment by the user.

Properties of Wrought Aluminum and Wrought Aluminum Alloys Aluminum mill products have been subjected to plastic deformation by hot- and cold-working mill processes (such as rolling, extruding, and drawing, either singly or in combination), so as to transform cast ingot into the desired product form, Microstructural changes associated with the working and with any accompanying thermal treatments are used to control certain properties and characteristics of the worked, or wrought, product or alloy.

Typical mill products include plate or sheet (which is subsequently formed or machined into products such as aircraft or building components), household foil, and extruded shapes such as storm window frames. A vast difference in the mechanical and physical properties of mill products can be obtained through the control of the chemistry, processing, and thermal treatment. Examples of corrosion and fabrication properties that are available, per alloy and temper, are found in the Table that follows.

Comparative characteristics and applications Weldabilil}'(Q Resistance spotand

Resistance tocorrosion St.....General(a)

crackiDg(b)

Workabitity (cold)(e)

Machlnability(e)

A A A A ,A A A A A A A A A A A A A A A A A A A A A A A A A A D(c) D(c) D

A A A A A A A A A A A A A A A A A A A A A A A A A A A A A A D D B

A A A B B A A A B B A A A B C A A A B B A A A B B A A A B B C B D

E E

D(c) D

C C

C D

corrosion

Alloy temper 10500 Hl2 HI4 HI6 Hl8 10600 HI2 HI4 HI6 HI8 11000 HI2 HI4 HI6 HI8 11450 HI2 HI4 Hl6 HI8 11990 HI2 HI4 HI6 HI8 13500 H12,H1l1 H14,H24 HI6,H26 HI8 2011TI T4, T451 T8 20140 TI,T4,T451 T6, T651,T651O. T6511

D D D E E D D D E E D D D E E

D D D E E

D D

D E E D D D A A A D B

B

Gas

An:

seam

ability(l)

Solderabilil}'(g)

A A A A A A A A A A A A A A A A A A A A A A A A A A A A A A D D D D D D

A A A A A A A A A A A A A A A A A A A A A A A A A A A A A A D D D D B B

B A A A A B A A A A B A A A A B A A A A B A A A A B A A A A D D D B B B

A A A A A A A A A A A A A A A A A A A A A A A A A A A A A A D D D D D D

A A A A A A A A A A A A A A A A A A A A A A A A A A A A A A C C C C C C

Braze-

Some lypicaI applications ofalloys Chemicalequipment, railroadtankcars

Chemicalequipment, railroadtankcars

Sheet-metalwork,spunhollowware, fin stock

Foil.fin stock

Electrolytic capacitorfoil,chemical equipment,railroadtankcars

Electricalconductors

Screw-machine products

Truckframes, aircraftstructures

(a) Ratings A through E are relative ratings in decreasing order of merit, based on exposures to sodium chloride solution by intermittent spraying or immersion. Alloys with A and B ratings can be used in industrialand seacoast atmosphereswithout protection. Alloyswith C. D, and Eratings generallyshould be protected at least on faying surfaces. (b) Stress-corrosioncracking ratings are based on service experience and on laboratorytests of specimens exposed to the 3.5% sodium chloride alternate immersion test. A = No known instance of failure in service or in laboratory tests. B = No known instance of failure in service;limited failures in laboratory tests of short transversespecimens. C = Service failures with sustained tension stress acting in short transverse direction relative to grain structure: limited failures in laboratory tests of long transverse specimens.D = Limited service failures with sustained longitudinal or long transverse stress. (c) In relatively thick sections the rating would be E. (d) This rating may be different for material held at elevated temperaturefor long periods. (e) Ratings A through D for workability (cold), and A through E for machinabilityare relative ratings in decreasingorder of merit. (f) Ratings A through D for weldabilityand brazeabilityare relative ratings defined as follows:A = Generally weldableby all commercial proceduresand methods. B = Weldablewith special techniquesor for specificapplications;requirespreliminarytrials or testing to develop welding procedure and weld performance.C = Limited weldabilitybecause of crack sensitivityor loss in resistance to corrosion and mechanicalproperties.D = No commonlyused welding methods have been developed. (g) Ratings A through D and NA for solderabilityare relative ratings defined as follows:A = Excellent.B =Good. C = Fair. D = Poor.NA = Not applicable (continued)

Wrought Aluminum and Aluminum Alloys /147 Comparative characteristics andapplications (continued) WeldabilitylO Resistance spoland

Resistance 10 corrosion

StressGenerat(a)

cmcking(b)

Workability (cold)(e)

D(c) D(c) D 0

C C B B

C D C D

C D D D

B C C

D(c) D(c) 0 D 0 A A A A A A A A A A A A A A A A A C B A A A A A A A A A A A A A A A A A A A A(d) A(d) A(d) A(d) A(d) B(d) B(d)

C C B B C A A A A A A A A A A A A A A A A A B A A A A A A A A A A A A A A A A A A A A B(d) B(d) B(d) B(d) C(d) Oed) D(d)

corrosion

Alloy temper 20240 T4, TI, TI51, TI51O,TI511 TI61 T6 T861, T81,T851,T851O, T8511 172 2036T4 2124T851 2218T61 172 22190 TIl, TI51, TI51O,TI511 TI7 T81, T851,T851O, T8511 T87 2618T61 30030 HI2 H14 HI6 HI8 H25 30040 H32 H34 H36 H38 31050 H12 H14 H16 H18 H25 4032T6 4043 50050 HI2 HI4 HI6 HI8 H32 H34 H36 H38 50500 H32 H34 H36 H38 50520 H32 H34 H36 H38 50560 HIll H12,H32 HI4,H34 HI8,H38 H192 H392

B D

C D D D A A B C C B A B B C C A B B C C B NA A A B C C B C C A A B C C A B B C C A A B B C D D

Machinability(e)

Gas

Arc

seam

abilily(1)

Solderability(g)

D B B B B B C B

D C 0 D D

D B C C C

D B B B B

D D D D D

C C C C C

Truckwheels,screw-machine products,aircraftstructures

D

B C

0 D

D D A A A A D A A A A A A B B B B B B B B B B B D NA A A A A A A A A A A A A A A A A A A A C C C C C C C

C A A A A A C A A A A A A A A A A A A A A A A A B NA A A A A A A A A A A A A A A A A A A A A A A A A A A

C C C

Military supersonic aircraft

B

B B C B B A A A A B B A A A A A B A A A A B A A A A A C NA B A A A A A A A A B A A A A B A A A A B A A A A A A

B B B B B E E D D 0 0 0 D C C C E E D D D D B C E E 0 0 D E D D D E D 0 C C D D C C C D D D C C B

B

Braze-

D D D D D D D A A A A A A B B B B B B B B B B B 0 NA B B B

Auto-bodypanelsheet

NA

B B B

NA A A A A A A B B B B B B B B B B B NA NA B B B B B B B B

B

B

B B B B B C C C C C 0 D D D D D D

C C C C C D D D D D 0 0 0 0 0 0 D

B B

Some typical applications oralloys

Jet engineimpellers andrings Strucmralusesathigh temperatures (to 315°C, or 600 "P) high-strength weldments

Aircraftengines Cookingutensils, chemicalequipment, pressurevessels,sheet-metalwork, builder's hardware,storage tanks

Sheet-metalwork,storagetanks

Residential siding,mobilehomes, rain-carryinggoods,sheet-metal work

Pistons Weldingelectrode Appliances, utensils,architectura1, electricalconductors

Builders'hardware, refrigerator trim, coiled tubes

Sheet-metal work,hydraulictube, appliances

Cablesheathing, rivetsfor magnesium, screenwire, zippers

(a) Ratings A through E are relative ratings in decreasing order of merit, based on exposures to sodium chloride solution by intermittentspraying or immersion. Alloys with A and B ratings can be used in industrialand seacoast atmosphereswithout protection.Alloys with C, D, and E ratings generally should be protected at least on faying surfaces. (b) Stress-corrosioncracking ratings are based on service experience and on laboratory tests of specimens exposed to the 3.5% sodium chloride alternate immersion test. A =No known instance of failure in service or in laboratory tests. B =No known instance of failure in service; limited failures in laboratory tests of short transversespecimens. C =Service failures with sustained tension stress acting in short transverse direction relative to grain structure: limited failures in laboratory tests of long transverse specimens. 0 =Limited service failures with sustained longitudinal or long transverse stress. (c) In relatively thick sections the rating would be E. (d) This rating may be different for material held at elevated temperaturefor long periods. (e) Ratings A through D for workability (cold), and A through E for machinabilityare relative ratings in decreasing order of merit. (f) Ratings A through 0 for weldabilityand brazeability are relative ratings defined as follows: A =Generally weldableby all commercial proceduresand methods. B =Weldablewith special techniquesor for specific applications;requires preliminarytrials or testing to develop welding procedureand weld performance.C =Limited weldablllty because of crack sensitivity or loss in resistance to corrosion and mechanicalproperties.D =No commonly used welding methods have been developed. (g) Ratings A through 0 and NA for solderabilityare relative ratings defined as follows: A =Excellent. B =Good. C =Fair. D =Poor.NA =Not applicable (continued)

148 I Heat Treater's Guide: Nonferrous Alloys Comparative characteristics andapplications (continued) Resistance tocorrosion StressWorkabitity (co!d)(e)

Machinability(e)

Gas

An:

seam

abillly(f)

A(d) A(d) B(d) A(d) A(d) B(d) B(d) B(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A A A A(d) A(d) A(d) A(d) A(d) A A A A A B(d) B(d) B(d) A A A A A A A A A A A

B C C A B B C C B A B B C C A D B B C A B B C C NA A B B B B C C A A B B C C A B B

D D D D D C C C D D D C C C D B D C C D D C C C B D D C D D D D E D D C C C D D D D C

C C C C C C C C C C C C C C C C A A A C C C C C NA C C C C C C C A A A A A A A A A A A

A A A A A A A A A A A A A A A A A A A A A A A A NA A A A A A A A A A A A A A A A A A A

B A A B A A A A A B A A A A B A A A A B A A A A NA B A A A B A A B B A A A A A A A A A

D D D D D D D D D D D D D D D D C C C D D D D D NA D D D D D D D B C C C C C B B B B A

D D D D D D D D D D D D D D D D D D D D D D D D NA

A A A B A A A A A A A B B B B A A

A B A B C B B B C C B C

C C D C C D D C C C D C B C C C D

A A A A A A A A A A D D D A A A A

A A A A A A A A A A B B B A A A A

A A B A A A A A A A B B B A A A A

A A A A A A A A A A D D D B B A A

B B B B B B B B B B

corroslon

Alloy temper 50830 H32l,H1l6 H11l 50860 H32,H116 H34 H36 H38 H11l 51540 H32 H34 H36 H38 51820 HI9 5252H24 H25 H28 52540 H32 H34 H36 H38 5356 54540 H32 H34 HlII 54560 H11l H321,HlI5 54570 56520 H32 H34 H36 H38 5657H241 H25 H26 H28 6005T5 6009T4 6010T4 60610 T4,T45l, T451O, T4511 T6, T65l, T652,T651O, T6511 6063T1 T4 T5,T52 T6 T83,T831,T832 60660 T4,T451O, T4511 T6, T651O, T65l1 6070T4,T4511 T6 61OIT6,T63 T6I,T64

General(a)

rracking(b)

A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A A A A A A(d) A(d) A(d) A(d) A(d) A A A A A A(d) A(d) A(d) A A A A A A A A A A B A A B B B A A A A A C

C C B B A A

Weldabillty(l) Resislance spoland

C

C

C

B C C B

Braze-

Solderabillly(g)

Some lyplcalappUralions oralloys Unfired,weldedpressurevessels, marine,auto aircraftcryogenics,TV towers,drillingrigs, transportation equipment,missilecomponents

Weldedstructures, storagetanks, pressurevessels,salt-waterservice

Automobilebodysheet,canends Automotiveandappliancetrim

Hydrogenperoxideandchemical storagevessels

Welding electrode Weldedstructures, pressurevessels, marineservice

NA

NA B D D D D D

High-strength weldedstructures, storagetanks,pressurevessels, marineapplications Hydrogenperoxideandchemical storagevessels

Anodizedautoandappliance trim NA

NA

NA NA NA

Heavy-dutystructuresrequiringgoodcorrosionresistanceapplications, truckandmarine,railroad cars,furniture, pipelines Automobilebodysheet Automobilebodysheet Heavy-dutystructuresrequiringgood corrosionresistance,truckand marine,railroadcars,furniture,pipelines Piperailing,furniture, architectural extrusions

Forgingsandextrusionsfor welded structures Heavy-dutyweldedstructures, pipelines High-strength busconductors

(a) Ratings A through E are relative ratings in decreasing order of merit, based on exposures to sodium chloride solution by intermittentspraying or immersion. Alloys with A and B ratings can he used in industrialand seacoast atmosphereswithout protection.Alloys with C, D, and E ratings generallyshould be protectedat least on faying surfaces. (b) Stress-corrosioncracking ratings are based on service experience and on laboratory tests of specimens exposed to the 3.5% sodium chloride alternate immersion test. A =No known instance of failure in service or in laboratory tests. B =No known instance of failure in service; limited failures in laboratory tests of short transversespecimens. C =Service failures with sustained tension stress acting in short transverse direction relative to grain structure; limited failures in laboratory tests of long transverse specimens.D =Limited service failures with sustained longitudinal or long transverse stress. (c) In relatively thick sections the rating would he E. (d) This rating may he different for material held at elevated temperaturefor long periods. (e) Ratings A through D for workability (cold), and A through E for machinabilityare relative ratings in decreasing order of merit. (f) Ratings A through D for weldabilityand brazeabilityare relative ratings defined as follows:A =Generally weldableby all commercialprocedures and methods.B =Weldablewith special techniquesor for specific applications;requirespreliminarytrials or testing to develop welding procedureand weld performance.C =Limited weldabllitybecause of crack sensitivity or loss in resistance to corrosion and mechanicalproperties. D =No commonlyused welding methodshave been developed. (g) Ratings A through D and NA for solderabilityare relative ratings defined as follows: A =Excellent. B =Good. C =Fair. D =Poor. NA =Not applicable (continued)

Wrought Aluminum and Aluminum Alloys /149 Comparative characteristics and applications (continued) Weldability(f)

Resista_to corrosion Stress-

corrosion

Alloy temper

Generalla)

cracking(b)

Workabilily (cold)(e)

Machin-

ability(e)

Gas

Resistance spotand

Braze-

seam

ability(!)

Arc

Solde" ability(g)

6151T6.T652

B

6201T81 6262T6,T651,T6510.T6511 1'9 6351.T5.T6

A B B B

A A A A

6463T1 T5 T6 7005T53

A A A

A A A

B

B

7049T73.T7351. T7352 T76.T7651 7050T74.T7451.T7452 T76.T761 7072 70750 T6,T651.T652.T651O, T6511 T73.T7351 7175.T74.T7452 71780 T6,T651.T651O. T6511 7475T6,T651 T73.T7351.T7352 T76,T765l

C C C C A

B B B B

C(c) C C C(c) C C C

A C B B

C C B B

C C D C

B B

B B

D C C A

C C D D D D A

C

B B B B

D D

D D D

B B B

D D D D

B B B B

NA NA

A A A A

A A A A

A A A A

A A A A

A A A

A A A

A A A

A A A

NA

B

B

B

B

B

D D D D A D D D D D D D D D

C C C C A C C C C C C C C C

B B B B



A B B B B B B B B B

B

Some typical appticatlons oralloys Moderate-strength, intricate forgings formachineand autoparts High-strength electric conductor wire Screw-machineproducts Heavy-duty structures requiring goodcorrosion resistance. truckandtractorextrusions Extruded architectural and trim sections Heavy-duty structures requiring goodcorrosion resistance. trucks.trailers, dumpbodies Aircraft andolherstructures Aircraftandolherstructures Finstock,cladding alloy Aircraftandotherstructures Aircraft andolherstructures. forgings Aircraftandolherstructures Aircraftandotherstructures

(a)RatingsAIhrough E arerelativeratingsindecreasing orderof merit.basedon exposures to sodiumchloridesolutionby intermittent spraying or immersion. AlloyswithA and B ratingscan be usedin industrial andseacoastatmospheres withoutprotection. AlloyswilhC. D. and E ratingsgenerally shouldbeprotectedat least on fayingsurfaces. (b) Stress-corrosion crackingratingsarebasedon service experience andon laboratory testsof specimens exposedto the3.5%sodiumchloridealternate inunersion test.A = No knowninstanceof failurein serviceor in laboratory tests.B = No knowninstance of failureinservice; limitedfailures inlaboratory testsof shorttransverse specimens. C=Servicefailures wilhsustained tensionstressactinginshorttransverse directionrelativetograinstructure; lintitedfailures in laboratory testsof longtransverse specimens. D = Limitedservicefailures withsustainedlongitudinal or longtransverse stress.(c)In relatively thicksectionstheratingwould be E. (d)Thisratingmay be different forrnaterial heldatelevatedtemperature forlongperiods.(e)RatingsAIhrough Dforworkability (cold),andAIhrough Eformachinability arerelativeratingsindecreasing orderofrnerit.(f) Ratings A IhroughD for weldability andbrazeability arerelativeratingsdefmedas follows: A= Generally weldableby allcommercial procedures andmelhods. B= Weldable wilhspeclaltechniques or forspecific applications; requires preliminary trialsor testingto developweldingprocedure andweldperformance. C = Limitedweldability becauseofcracksensitivity orlossin resistance tocorrosion andmechanical properties. D = No commonly usedweldingmethodshavebeendeveloped. (g) RatingsA Ihrough D andNAforsolderability arerelativeratingsdefinedas follows: A= Excellent. B = Good.C = Fair.D = Poor. NA= Notapplicable

1050 Chemical Composition. Composition Limits. 99.50 Al min, 0.25 Si max, 0.05 Cu max, 0.05 Mn max, 0.05 Mg max, 0.05 V max, 0.03 others max (each)

Aluminum content: 99.5 Al min

Specifications (U.S. and/or Foreign). ASTM. B491; UNS. A91050;

Typical Uses. Extruded coiled tubing for equipment and containers for food, chemical, and brewing industries; collapsible tubing

(Canada) CSA 9950; (France) NF A5; (United Kingdom) B5 IB; (Germany) DIN A199.5

Available Product Forms. Extruded pyrotechnic powder

Characteristics

Recommended Heat Treating Practice Annealing. Temperature 345°C (650 oF)

1050 Aluminum: Typical mechanical properties 'Iemper

0 H14 H16 HI8

1enslJe strength MPa ksl 76 110 131 159

11 16 19 23

Yield strength MPa ksl 28

103 124 145

4 15 18 21

Elongation,

....

39 10 8 7

Shearstrength MPa ksl 62 69 76 83

9 10 11 12


1060 Chemical Composition. Composition Limits. 99.60 AI min, 0.25 Si max, 0.35 Fe max, 0.05 Cu max, 0.03 Mn max, 0.03 Mg max, 0.05 Zn max, 0.05 V max, 0.03 Ti max, 0.03 others max (each) Specifications (U.S. and/or Foreign). AMS. Sheet and plate: 4000; ASME. (See adjoining Table); ASTM. (See adjoining Table); SAE. J454; UNS. A91060

ASME and ASTMspecifications Specification number

Mill fonn and condition

ASME

AS1M

Sheetand plate Wire, rod, and bar (rolledor coldfinished) Wire, rod. bar.shapes.and tube (extruded) Pipe (gas and oil transmission) Tube (condenser) Tube (condenserwithintegralfins) Tube (drawn) Tube (drawn.seamless) Tube (extruded, seamless)

SB209

B209 B211 B221 B345 B234 B404 B483 B210 B241

SB221 SB234

SB210 SB241

Available Product Forms. Sheet, plate, drawn tubing, extruded tubing, heat exchanger tubing. Available tempers: H12, H14, HI6, HI8

Characteristics Aluminum content: 99.60 Al min

Typical Uses. Chemical equipment and railroad tank cars. Has very good resistance to corrosion and good formability. For more information on resistance to corrosion, cold formability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Application" in introduction to this chapter

Recommended Heat Treating Practice Annealing. Temperature is 345 °C (650 OF). Time in furnace need not be longer than necessary to bring all parts of load to annealing temperature. Rate of cooling is not important .

1060 Aluminum: Typical mechanical properties Thnsilestrength MPa ksi

Elongatlon(a),

Hardness,

Thmper

MPa

ksi

%

HB(b)

0 H12 HI4 H16 H18

69 83 97 110 131

28 76 90 103 124

4 11 13 15 18

43 16 12 8 6

19 23 26 30 35

10 12 14 16 19

Yieldstrength

Shear strength MPa ksi

48 55 62 69 76

7 8 9 10 11

Fatigue Iimll(c) MPa ksi

21 28 34 45 45

3 4 5 6.5 6.5

(a) 1.6 rom (0.0625 in.) thick specimens.(b)500 kg load: 10 romdiam ball. (c)AI5 x 108 cycles; RR Moore type test

1060 Aluminum: Tensile-property limits Thnsileslrength Minimum Thmper

Maximum

MPa

ksi

MPa

ksi

55 75 83 110

8.0 11.0 12.0 16.0

95 110

115

14.0 16.0 17.0

75 70 62

11.0 10.0 9.0

58 70 83 110 58

8.5 10.0 12.0 16.0 8.5

58 58

8.5 8.5

95 95(b)

14.0 14.O(b)

83

12.0

Sheet and plate

o HI2 H14

HI8 H112 0.250-0.499 in. thick 0.500-1.000 in. thick 1.001-3.000in. thick Drawn lube (0.010-0.500 in. wall thickness)

o HI2 H14

HI8 H112 Extruded tube

o H112 Beat-exchanger tube (0.010-0.200 in. wall thickness) H14

(a) In 50 rom (2 in.) or 4d, where d is diameter of reduced section of tensile test specimen.Where a range of values appears in this column, specified minimum elongation varies with thickness of the mill product. (b) Applicableonly 10tube25.410 114.3 rom (1.000104.500 in.) diam by 1.27104.29 rom(0.050 100.169 in.) wall thickness

Wrought Aluminum and Aluminum Alloys /151

1100 Chemical Composition. Composition Limits. 99.00 Al min, 1.00 Si max + Fe, 0.05 to 0.20 Cu, 0.05 Mn max, 0.10 Zn max, 0.05 others max (each), 0.15 others max (total). 0.0008 Be max (for welding electrode and filler rod only)

Characteristics A 99.00 Al (min)-0.12 Cu grade. Typically used where requirements call for combination of good formability and high resistance to corrosion, but where high strength is not necessary. For example: Food and chemical handling and storage equipment, sheet metal work, drawn or spun hollowware, welded assemblies, heat exchangers, lithoplate, nameplates, and light reflectors.

Specifications (U.S. and/or Foreign). AMS. (See adjoining Table); ASME. (See adjoining Table); ASTM. (See adjoining Table); SAE. J454; UNS. A9l100; Government. (See adjoining Table); (Canada) CSA 990C; (France) N A45; ISO. A199.0 Cu

For additional information on resistance to corrosion, cold formability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Available Product Forms. Sheet; plate; wire, rod, and bar (rolled or cold finished); wire. rod, bar, shapes and tubing (extruded); tubing (extruded, seamless; extruded coiled; drawn; seamless; and welded); rivet wire and rod; spray gun wire; forgings and forging stock; impacts; and foil

Recommended Heat Treating Practice Annealing. Temperature is 345°C (650 OF). Time in furnace need not be any longer than necessary to bring all parts of load to annealing temperature. Rate of cooling is not important

1100-0 sheet, cold rolled and annealed. Recrystallized, equiaxed grains and insoluble particles of FeAla (black). Size and distribution of Fe-Al, in the worked structure were unaffected by annealing. 0.5% HF. 500x

1100 Aluminum: Microstructures. 1100-H18 sheet, cold rolled. Note metal flow around insoluble particles of FeAla (black). Particles are remnants of scriptlike constituents in the ingot that have been fragmented by working. 0.5% HF. 500x

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2014 Aluminum: Microstructure. 2014-T61 closed-die forging. Blister on surface is associated with hydrogen porosity.As-polished. 50x

Previous Page


2017 Chemical Composition. Composition Limits. 0.20 to 0.80 st, 0.70 Fe max, 3.50 to 4.5 Cu, 0.40 to 0.80 Mg, 0.40 to 1.00 Mn, 0.10 Cr max, 0.15 Ti max, 0.25 Zn max, 0.05 other (each), 0.15 others (total), bal Al Specifications (U.S. and/or Foreign). ASTM. B 211 and B 316; SAE. J454; ANSI. H38.4 and H38.12; UNS. A92017; Government. QQ-A222/5, QQ-A-430, MIL-R-430; (France) A-U46; (Germany) AICuMgl and 3.1325; (Great Britain) LI8 and 150A; (Canada) CM41; (Austria) AICuMg1. 150: AICuMgSi Available Product Forms. Forgings, extrusions, bar, rod wire, shapes, rivets

Characteristics First alloy developed in AI-Cu-Mg series is now in limited use

Typical Uses. Chiefly for rivets. Used in components for general engineering purposes, structural applications in construction and transportation, screw machine products, and fittings. Alloy is age hardenable with medium strength and ductility, good machinability, and formability, and fair resistance to atmosphere corrosion. Welding is not recommended unless heat treatment after welding is practical. Service temperature is below 100°C (212 OF). For more information, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Solution Heat Treating. Rolled or cold finished wire, rod, and bar are treated to obtain T4 and T42 tempers at 500 to 510 °C (930 to 950 "F),

Material should be quenched as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature, and cooled in some manner so that it remains below 38°C (100 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water is effective for some materials. Nominal treatment temperatures should be attained as rapidly as possible and maintained with ±6 °C (±1O "F) during time at temperature

Natural Aging. Occurs at room temperature Annealing. A heat-treated anneal is obtained at 415°C (775 OF); a cold work anneal is obtained at 340 to 350 °C (645 to 660 OF)

2017 Aluminum: Typicaltensile properties of 2017 (T4 and T451 tempers) at various temperatures lOst temperalure(a) OF -c

-196 -80 -28 24 100 150 205 260 315 370

- - -_"':=-

400

550 448 440 427 393 275 110 62 40 30

80 65 64 62 57 40 16 9 6 4.3

Yieldstrength (0.2% oft'se!) MPa ksi

365 290 283 275 270 207 90 52 35 24

53 42 41 40 39 30 13 7.5 5 3.5

Elongationin SOmm (2in.l,%

28 24 23 22 18 15 35 45 65 70

(a)Tested afterholding10000h attemperature

600,....--------------------, 500

-320 -112 -18 75 212 300 400 50 600 700

Thnsile strength MPa ksl

2017 Aluminum: Time temperature-property diagram. Curves at 95% of maximum tensile stress for various alloys. A =7075. B =2017. C =6061. D =6063

LIVE GRAPH

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I-

200

100

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10

100

_='

1000

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2024, Alclad 2024 Chemical Composition. Composition Limits (2024). 0.50 Si max, 0.50 Fe max, 3.8 to 4.9 Cu, 0.30 to 0.90 Mn, 1.2 to 6.8 Mg, 0.10 Cr max, 0.25 Zn max, 0.15 Ti max, 0.05 other max (each), 0.15 other max (total), bal AI Composition Limits (Alclad 2024). 1230 c1adding-99.30 Al min, 0.70 Si max + Fe, 0.10 Cu max, 0.05 Mn max, 0.05 Mg max, 0.10 Zn max, 0.05 V max, 0.03 Ti max, 0.03 other max (each)

Specifications (U.S. and/or Foreign). AMS. (See adjoining Table); ASME. Rolled or drawn coil, rod, and bar: SB 211. Extrusions: SB 221; ASTM. (See adjoining Table); SAE. J 454; UNS. A92024; Government. (See adjoining Table); (Austria) Onom AICuMg2; (Canada) CSA CE42; (France) NFA-U4G1; (Italy) UNI P-AICu4.5MgMn, Alclad 2024, P-AICu4.5MgMn place; (Spain) UNE L-314; (Germany) DIN AICuMg2 Available Product Forms. (See adjoining Table)

160 I Heat Treater's Guide: Nonferrous Alloys Precipitation Heat Treating (Artificial Aging). Approximate metal temperatureof 190°C (375°F) is maintained in treating flat sheet; coiled sheet; plate; rolled or cold finished wire, rod, and bar; extruded rod, bar, shapes, and tubing to the T6, T62, T81, T86, T851, T861, T851O, and T8511 tempers. Nominal temperatures should be attained as rapidly as possible and maintained within ±6 °C (±1O "F) of nominal during time at temperature. Times at temperature listed are approximate. Specific times are based on time required for load to reach temperature. Times given here are based on rapid heating, with soak time measured from time load reaches a temperature within 6 °C (10 OF) of applicable temperature.

Characteristics An AI-Cu-Mg alloy Typical Uses. Applications include aircraft structures, rivets, hardware, truck wheels, screw machine products, and other structural applications. For information on resistance to corrosion, machinability, brazeability, and weldability per alloy and temper, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Solution Heat Treating. Treatments also apply to Alclad flat sheet and coiled sheet in T3, T4, T42, and TI61 tempers

Times at temperature can vary with product:

Treatment temperatures are 495°C (920 OF) for flat sheet to obtain TI, T4, T42, and T461 tempers; for coiled sheet to obtain T4 and T42 tempers; for plate to obtain T42, T351, and TI61 tempers; for cold or cold finished coil, rod, and bar to obtain T4, T42, TI51, and TI61 tempers; for extruded rod, bar, shapes, and tubing to obtain TI, T42, TI51O, and TI51 tempers; for drawn tubing to obtain TI and T42 tempers.

Temper

Product

1'861 T62 1'81 172 T62 T62 T6and1'851 1'861 1'851 1'86 T81. T8510, 1'8511

Aatsheet

Coiledsheet Plate

Material should be quenched as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature and cooled in some manner so that it remains below 38°C (100 OF) during quenching cycle. Use of high-velocity, high-volume.jets of cold water is effective for some materials. Nominal treatment temperature should be attained as rapidly as possible and maintained at ±6 °C (±10°F) during time at temperature.

Rolledor coldfinishedwJre, rod,andbar Extrudedrod,wire,shapes,andtubes

nmesat Temperature (hl

8 9 12 16 9 9 12 8 12 8 12

Special considerations include: • In treating flat sheet and plate, to the T81, T86 and T861 tempers, cold working is necessary and subsequent to solution treatment, and prior to any precipitation treatment.to obtain desired properties. • In treating plate, rolled, or cold finished wire, rod, and bar to T851; and extruded rod, wire, shapes or tubing to T8l, T8510, and T8511, the parts are stress relieved by stretching to produce a specified amount of permanent set, subsequent to solution treatment and prior to any precipitation treatment.

Special considerations include: • In treating flat sheet to TI and TI61 tempers and treating rolled or cold finished wire, rod, and bar to TI6 temper, and treating plate to TI61 temper ... cold working subsequent to solution-treatment and prior to precipitation treatment is necessary to obtain properties provided by these tempers • In treating plate and rolled or cold finished wire rod and bar to TI51 temper, parts are stress relieved by stretching to produce a specified amount of set subsequent to solution treatment and prior to precipitation treatment

Annealing. This alloy is annealed at 415°C (775 OF)

2024 Aluminum. Type and depth of attack on 2024-T4 sheet versus quench factor 0.20

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Bare 2024 Sheetandplate

WIre,rod,andbar (roUed orcoldfinished)

WIre,rod,bar,shapes,andtube(extruded)

Tube (extruded, seamless) Tube(drawn,seamless)

Thbe(hydraulic) Rivet wireandrod Foil Alclad2024 Sheetandplate

AMS

30 ~in

Specification number AS1M Government

\WCek 21~onlhs1 20

1 ~ay

100 0.1

10 Elapsed time after quenching, h

4033 4035 4037 4097 4098 4099 4103 4104 4105 4106 4192 4193 4112 4119 4120 4152 4164 4165 4087 4088 4086

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2048 Aluminum. Creep-rupturecurves for 2048-T851 plate, longitudinalorientation 1000 ,-----,----.-,--,--,------,---,----,,-,,

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100

100

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Previous Page

2061 Heat Treater's Guide: Nonferrous Alloys

6063 Chemical Composition. Composition Limits. 0.20 to 0.60 Si, 0.35 Fe max, 0.10 Cu max, 0.10 Mn max, 0.45 to 0.90 Mg, 0.10 Cr max, 0.10 Zn max, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), balAl Specifications (U.S. and/or Foreign). AMS. Extruded wire, rod, bar, shapes, and tubing: 4156; ASME. Extruded wire, rod, bar, shapes, and tubing: SB221. Pipe: SB241; ASTM. (See adjoining Table); SAE. J454; UNSA96063

Available Product Forms. Extruded wire, rod, bar, shapes, and tubing; drawn tubing. Tempers include TI, T4, T5, T52, T6, T83, T831, T832

General Considerations. Temperatures given here are nominal and should be attained as rapidly as possible and maintained with ±6 °C (±l0 OF) of nominal during time at temperature. Times at temperature are approximate. Specific times are based on time required for load to reach temperature. Times given here are based on rapid heating, with soak times measured from time load reaches within 6 °C (10 "F) of applicable temperature

Annealing. Treat at 415°C (775 "F); hold 2 to 3 h at temperature; cool at 28°C (50 oF) per hour from 415°C (775 oF) to 260 °C (500 oF)

Characteristics Major alloying elements: 0.7Mg-0.4Si

Typical Uses. Pipe, railing, furniture, architectural extrusions, truck and

6063 Aluminum: Typical tensile properties at various temperatures

trailer flooring, doors, windows, irrigation pipe. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Solution Heat Treating. Extruded rod, bar, shapes, and tubing may be treated to TI temper by quenching directly from the extrusion press with suitable control of extrusion temperature. T42 temper is obtained by treating product at 520°C (965 "F), Drawn tubing is treated to T4 and T42 tempers at 520°C (965 OF). Sheet and plate are solution treated at 570 °C (1060 OF). T4 temper is obtained with natural aging of two weeks

General Considerations. Unless otherwise indicated, product should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature and maintained at temperature below 38°C (100 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective in treating some materials. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±1OOF) of nominal during time at temperature Precipitation Heat Treating (Artificial Aging). Extruded rod, bar, shapes, and tubing are treated to T5 temper at 205°C (400 OF) for I h. Alternate treatment: 3 h at 180°C (355 "F). Same products are treated to T6 and T62 tempers by treating at 175°C (345 OF) for 8 h. Alternate treatment: 6 h at 180°C (355 "F), In treating drawn tubing to T83, T831, and T832 tempers, cold working after solution treatment is necessary to get desired properties. Nominal treatment temperatures for these alloys and T62 are 175°C (345 "F) for 8 h. Alternative for treating to T83, T831, and T832 tempers: quench directly from extrusion press if it has suitable temperature control

-c

Temperature OF

YIeldstrength (0.2c;{, offset) ksI MPa

'Iensile strength(a) ksI MPa

Elongation, c;{,

Tl temper(b) -320 -112 -18 75 212 300 400 500 600 700

-196 -80 -28 24 100 150 205 260 315 370

234 179 165 152 152 145 62 31 23 16

34 26 24 22 22 21 9 4.5 3.2 2.3

110 103

103 45 24 17 14

16 15 14 13 14 15 6.5 3.5 2.5 2

255 200 193 186 165 138 62 31 23 16

37 29 28 27 24 20 9 4.5 3.2 2.3

165 152 152 145 138 124 45 24 17 14

24 22 22 21 20 18 6.5 3.5 2.5 2

324 262 248 241 214 145 62 31 23 16

47 38 36 35 31 21 9 4.5 3.3 2.3

248 228 221 214 193 133 45 24 17 14

36 33 32 31 28 20 6.5 3.5 2.5 2

97 90

97

44 36 34 33 18 20

40 75 80 105

TStemper -196 -80 -28 24 100 150 205

-320 -112 -18 75 212 300 400 500 600 700

260 315 370

28 24 23 22 18 20

40 75 80 105

T6temper -320 -121 -18 75 212 300 400 500

-196 -80 -28 24 100 150 205 260 315 370

600 700

24 20 19 18 15 20

40 75 80 105

(a) Lowest strength for exposures up to 10 000 h at temperature, no load; testloading applied at 35 MPalmin (5 ksilmin) to yield strength and then at strain rate of 5%/min to fracture. (b) Tl temper fonnerlyT42

6063 Aluminum: Typical mechanical properties 'Thmper

0 Tl(c) T4 T5 T6 T83 T831 T832

Tensilestrength MPa ksi

YIeldstrength MPa ksI

90 152 172 186 241 255 207 290

48 90 90 145 214 241 186 269

13 22 25 27 35 37 30 42

7 13 13 21 31 35 27 39

(a) 500 kg load: 10 rnm diam ball. (b) At 5 X 108 cycles: R.R. Moore type test. (c) Formerly T42 temper

Elongation, c;{,

20 22 12 12 9 10 12

Hanlness(a), HB

Shear strength MPa ksI

Fatigue streogth!b) MPa ksI

25 42

69 97

10 14

55 62

8 9

60 73 82 70 95

117 152 152 124 186

17 22 22 18 27

69 69

10 10


6063 Aluminum. 6063-T5 extrusion. Transverse section. Grains at surface of extrusion have recrystallized because of more working and heating. Grains in the interior of the extrusion are unrecrystalIized. Tucker's reagent. Actual size

6063 Aluminum: Time-temperature property diagram. Composition: AI-0.60% Mg-0.30% Si-0.02% Mn-0.16% Fe-O.Q1 % Zn-0.02% Ti. Treatment: Solution heat-treated at 540°C (1000 OF) for 1 to 1.5 h, down quenched to various temperatures into molten salt, held at temperature for varying times, water quenched, and aged. Maximum quenched and aged yield strength 25.9 ksi (178 MPa) Iso-yield curve is 90% of quenched and aged yield strength

I

800 (4211

90% of T6 YS


400 (:Ill4'

~

100

1000

Time of Isothermal Hold, s

6063 Aluminum: Time-temperature-property diagram. Curves at 95% of maximum tensile stress for various alloys. A= 7075; B = 2017; C = 6061; D = 6063

600

---..-- :----- ---

500 400


A

U

0.300

I-

200 100 0

1

100

10

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1000

2081 Heat Treater's Guide: Nonferrous Alloys ASTMspecifications Mill form andoondltlon

WIre. rod.bar.shapes.WId tube(extruded) Tube(extruded, seamless); pipe Tube(extruded, coiled) 'Iube (drawn) Tubejdrawn,seamless) Pipe(gasWId oilttansmission) Structural pipeWId nibe(extruded)

ASTMNo.

B221 B241 B491 B483 B2LO B345 B429

6066 Chemical Composition. Composition Limits. 0.90 to 1.80 Si, 0.50 Fe max, 0.70 to 1.20 Cu, 0.60 to 1.10 Mn, 0.80 to 1.40 Mg, 0.40 Cr max. 0.25 Zn max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Extruded wire, rod, bar, shapes, and tubing: B 221; SAB. J454; UNS. A96066; Government. Extruded wire, rod, bar, shapes, and tubing: QQ-A-200/1O. Forgings: QQ-A-367; (United Kingdom) BS H11 Available Product Forms. Extruded wire, rod, bar, shapes, and tubing; die forgings. Available tempers: T4, T6, T450, T4511, T651O, T65l1

Characteristics Major alloying elements: 1.4Si-l.1Mg-1.0Cu-0.8Mn Typical Uses. Forgings and extrusions for welded structures. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Precipitation Heat Treating (Artificial Aging). Extruded rod, bar, shapes, and tubing; drawn tubing, and die forgings are treated to T6, T62, T651O,T6511 tempers at 175°C (345 oF) for 8 h. Parts scheduled for T6510 and T6511 tempers are stress relieved by stretching to produce specified amount of permanent set prior to precipitation heat treatment General Considerations. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±10 OF) of nominal during time at temperature. Time at temperature is approximate. Specific times are based on time needed for load to reach temperature. Times are based on rapid heating, with soak time measured from time load reaches temperature within 6 °C (10 "F) of applicable temperature Annealing. Temperature of 415°C (775 "F) is held for 2 to 3 h 6066 Aluminum: Tensile properties

Recommended Heat Treating Practice Solution Heat Treating. Extruded rod, bar, shapes, and tubing; drawn tubing; and die forgings are treated at 530°C (985 OF) to T4, T42, T451O, and T4511 tempers. Product in T4510 and T45ll tempers are stress relieved by stretching to produce specified amount of permanent set prior to precipitation heat treatment General Considerations. Product should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature and maintained at a temperature below 38°C (l00 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water is effective for some materials. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±IO OF) during time at temperature

Thmper

'Iypleal properties 0 T4.T451 T6.T651 Property limits (extrusions) 0 T4. T4510.T4511 T42 T6.T6510.T6511 T62 Property limits (die forgings) T6

Thnslle strength ksl MPH

YIeld strength (0.2% olrsel) MPH ksl

150 360 395

22 52 57

83 207 359

12 30 52

18 18 12

200 max 275 min 275 min 345 min 345 min


125max l70min 165min 310min 290 min


16min 14min 14min 8 min 8 min

345 min

50 min

310min

45 min

FJongatlon(H), %

(a) In 50 mrn(2 in.) or 4d. where d is diameterof reducedsectionof tensiletestspecimen

6070 Chemical Composition. Composition Limits. 1.00 to 1.70 Si, 0.50 Fe max, 0.15 toO.4OCu,0.40 to 1.00Mn, 0.50 to 1.20Mg, 0.10Crmax, 0.25 Zn max, 0.15 Ti max, 0.5 others max (each), 0.15 others max (tota!),bal AI

Specifications (U.S. and/or Foreign). ASTM. Gas and oil transmission pipe: B 345; SAB. J454; Government. Extruded rod, bar, shapes, and tubing: MIL-A-46104. Impacts: MlL-A-12545

Wrought Aluminum and Aluminum Alloys 1209

Available Product Forms. Extruded rod, bar, shapes, and tubing. Tempers include T4, T6, and T4511

Characteristics Major alloying elements: 1.45Si-0.8Mg-0.7Mn-0.3Cu

Typical Uses. Heavy duty welded structures, pipelines, extruded structural parts for autos. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Solution Heat Treating. Extruded bar, rod, shapes, and tubing are treated to T4 and T42 tempers at 545°C (1015 "F), With suitable control of extrusion temperatures, product may be directly quenched from extrusion press.

General Considerations. Material should be quenched as rapidly as possible from solution treating temperature and with minimum delay after removal from furnace. When quenching is by total immersion in' water, unless otherwise indicated, water should be at room temperature and maintained at a temperature below 38°C (100 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water is effective for some materials. Temperatures given here are nominal and should be attained as rapidly as possible within ±6 °C (±IO "F) during time at temperature Precipitation Heat Treating (Artificial Aging). Product is treated to T6 temper at a metal temperature of 160°C (320 "F) for 18 h. Time at temperature is approximate. Specific times depend on time required for load to reach temperature. Times are based on rapid heating, with soak time measured from time load reaches temperature within 6 °C (10 "F) of applicable temperature Annealing. Temperature for T4 temper is 545°C (1015 "F)

6101 Chemical Composition. Composition Limits. 0.30 to 0.70 si, 0.50 Fe max, 0.10 Cu max, 0.03 Mn max, 0.35 to 0.80 Mg, 0.03 Cr max, 0.10 Zn max, 0.06 B max, 0.03 others max (each), 0.10 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Bus conductor: B 317; SAE. J454; UNS. A96101; (Austria) Onorm E-AlMgSi; (France) NF A-G5IL; (Italy) UNI P-AlSiO; (Switzerland) USM AI-Mg-Si; (United Kingdom) BS 9IE; (Germany) E-AlMgSiO.5; Werkstoff-Nr-3.3207 Available Product Forms. Extruded rod, bar, tubing, pipe, and structural shapes. Available tempers: T4, T6, T61, T63, T64, T65

Characteristics

6101 Aluminum: Typical tensile properties of 6101-T6 at various temperatures Tempemture -196 -80 -28 24 100 150 205 260 315 370

OF

-320 -112 -18 75 212 300 400 500 600 700

296 248 234 221 193 145 69 33 24 17

43 36 34 32 28 21 10 4.8 3 2.5

Recommended Heat Treating Practice Solution Heat Treating. Heat to 510 °C (950 "F); hold at temperature for 1 h Precipitation Heat Treating (Artificial Aging). Heat to 175°C (345 OF); hold at temperature for 6 to 8 h

(0.2% off.. l)(o) MPo ksI

228 207 200 193 172 131 48 23 16 12

33 30 29 28 25 19 7 3.3 2.3 1.8

6101 Aluminum: Property limits for 6101 extrusions Eleelrleal

Temper

Yield strength Teosil's1reogth(o) MPo ksl

For information on corrosion resistance, cold workability, machinability, braze ability , and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)

Major alloying elements: 0.6Mg-0.55Si

·C

Typical Uses. High strength bus bars, electrical conductors, and heat sinks.

Tensile slrength(o) MPo ksl

YIeld s1reogth(o) MPo ksi

oondU
Wrought Aluminum and Aluminum Alloys /219 LIVE GRAPH LIVE GRAPH LIVE GRAPH Click here to view

• Extruded rod, bar, and shapes are treated to 176510 and 176511 tempers in a two-stage treatment: 3 to 6 h at 120°C (250 OF), followed by 12 to 15 h at 165°C (330 oF) • All extruded rod, bar, and shapes are stress relieved by stretching to produce a specified amount of permanent set subsequent to solution treatment and prior to precipitation treatment • Die forgings are heated to 174 temper and hand forgings to 17452 temper in a multistage treatment: 8 h at 105°C (225 "F), followed by 8 hat 120°C (250 oF), then 4 to 10 hat 175°C (345 OF). Hand forgings are stress relieved by 1 to 5% cold reduction subsequent solution treating and prior to precipitation treatment General Considerations.

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7050 Aluminum. Aging characteristics at room temperature, at 0 °C (32 OF), and at -18°C (0 OF)

7050 600

v . .V 500

--

~

• Nominal metal temperatures should be reached as soon as possible and maintained at ±6 °C (±10 OF) during time at temperature • Time at temperature depends on time for load to reach temperature. Times given are based on rapid heating, with soaking time measured from time load reaches temperature within 6 °C (10 OF) of applicable temperature

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7050 Aluminum: Plane-strain fracture toughness Thmperand orientation

500

MPa.,r,n

70

Average

Minimum

MPa.,r,n

ksIVlIL

ksiVlIL ~

Plate 173651 L-T T-L S-L Extrusions 17651X L-T T-L S-L 17351X L-T T-L S-L

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45.1 31.9 26.4

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7050 Aluminum. Actual versus predicted yield strengths for 7050 extrusions

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1 day

Elapsed lime after quenching, h

7050 Aluminum. Effect of aging temperature on yield strength of 7050-T736

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2219 Aluminum. Rotating beam fatigue data of 7039 plate compared with fatigue characteristics of 2014 and 2219. Data for 7039 are

based on least-of-four results in the longitudinal direction with a 7.5 mm (0.3 in.) diam smooth specimen. Curves for 2014 and 2219 are mean values from publishedliterature 400

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Wrought Aluminum and Aluminum Alloys 11n 2219 Aluminum: Creep-rupture properties of 2219-T87 plate Temperature °C

OF

Time under stress,h

24

75

100

212

0.1 1 10 100 1000 0.1

300

10 100 1000 0.1

I

150

I

205

400

230

450

260

500

315

600

10 100 1000 0.1 1 10 100 1000 0.1 1 10 100 1000 0.1 1 10. 100 1000 0.1 I

370

700

10 100 1000 0.1 1 10 100 1000

SlressCor creepoC 0.1%

Rupturestress MPa ksi

MPa

ksi

MPa

ksl

MPa

ksl

MPa

ksl

460 455 450 435 420 400 380 350 330 315 345 315 290 260 235 255 230 205 180 150 206 185 170 150 130 170 160 145 125 105 115 105 90 62 34 59 48 34 23 17

450 425 405 395 380 365 345 330 315 305 315 295 275 250 230 240 215 185 165 145 195 170 160 140 125 160 145 130 115 105 110 105 83 55 31 55 45 30 20 13

65 62 59 57 55 53 50 48 46 44 46 43 40 36 33 35 31 27 24 21 28 25 23 20 18 23 21 19 17 15 16 15 12 8 4.5 8 6.5 4.4 2.9 1.9

420 400 385 380 370 350 340 325 310 295 310 290 260 235 205 230 200 170 145 130 180 165 145 125 115 150 140 125 110 97 105 97 76 52 28 52 41 26 17

61 58 56 55 54 51 49 47 45 43 45 42 38 34 30 33 29 25 21 19 26 24 21 18 17 22 20 18 16 14 15 14 11 7.5 4 7.5 6 3.8 2.5 1.6

385 380 370 365 360 340 325 305 290 260 290 260 235 200 165 200 165 140 115 97 165 140 115 105 83 140 125 105 90 69 97 83 62 45 26 48 32 17

56 55 54 53 52 49 47 44 42 38 42 38 34 29 24 29 24 20 17 14 24 20 17 15 12 20 18 15 13 10 14 12 9 6.5 3.8 7 4.7 2.4 1.6 1.2

370 365 360 350 345 325 310 290 260 240 270 240 205 165 140 165 140 110 97 83 140 115 97 83 69 125 105 83 69 59 83

54 53 52 51 50 47 45 42 38 35 39 35 30 24 20 24 20 16 14 12 20 17 14 i2 10 18 15 12 10 8.5 12 9.5 7.5 5 3.3 5 2.6 1.7 1.2 0.9

67 66 65 63 61 58 55 51 48 46 50 46 42 38 34 37 33 30 26 22 30 27 25 22 19 25 23 21 18 15 17 15 13 9 5 8.5 7 5 3.4 2.4

1.0%

0.5%

II

0.2%

II

8

66

52 34 23 34 18 12 8 6

2219 Aluminum: Microstructures. (a) 2219-T6 closed-die forging, solution heat treated and artificially aged. Longitudinal section. Worked structure contains some recrystallized grains. See adjoining figure for a totally unrecrystallized structure. Keller's reagent. 100x (b) 6061-F plate, 38 mm (1.5 in.) thick, as hot rolled 2219-T6 closed die forging, solution heat treated and artificially aged. Longitudinal section shows no recrystallization of the worked structure. Note the large amount of slip (light parallel lines) that has occurred on two sets of slip planes. Keller's reagent. 100x

(a)

(b)


2219 Aluminum: Creep-rupture properties of 2219-T851 plate 'Il>mperature

TUne under

of

stress,h

24

75

100

212

0.1 1 lO 100 lOoo 0.1 1 10 100 lOoo 0.1 1 10 100 lOoo lO,ooo 100,000 0.1 1 10 100 1000 lO,ooo 100,000 0.1 1 100 1000

°C

150

175

205

300

350

400

mooo

230

260

315

370

450

500

600

700

100,000 0.1 1 lO 100 1000 lO,ooo 100,000 0.1 1 10 100 1000 lO,ooo 100,000 0.1 1 lO 100 1000 lO,ooo 0.1 1 10 100 1000

Stressfor creep of Ruplurestress MPa ksi

455 450 435 425 420 395 370 350 330 315 340 315 290 260 235 205 170 305 275 250 220 185 160 130 270 235 180 150 125 97 230 200 170 150 125 97 66, 180 165 150 130 lO5 69 45 130 lt5 lO5 69 41 22 69 62 32 22 14

-

0.2%

0.5%

1.0%

0.1%

MPa

ksi

MPa

ksi

MPa

ksI

MPa

ksi

66 65 63 62 61 57 54 51 48 46 49 46 42 38 34 30 25

435 420 400 380 365 360 340 325 3lO 295 305 290 270 250 220

63 61 58 55 53 52 49 47 45 43

60 56 53 52 51 49 47 45 43 41 43 40 37 34 29

365 360 345 340 330 315 305 290 275 270 275 255 235 200 165

53 52 50 49 48 46 42 40 39 40 37 34 29 24

350 345 330 325 315 305 285 275 270 260 260 235 205 170 150

51 50 48 47 46

42 39 36 32

415 385 365 360 350 340 325 3lO 295 285 295 275 255 235 200

44

275 255 230 200 170

40 37 33 29 25

260 240 215 185 160

38 35 31 27 23

250 220 195 160 140

36 32 28 23 20

230 200 165 130 lO5

33 29 24 19 15

240 220 165 140 125

35 32 24 20 18

235 205 150 125

34 30 22 18

215 180 130 lt5

31 26 19 17

195 160 ltO

28 23 16 13

205 185 160 140 lt5

200 170 150 130 ltO

26 22 19 16 13

165 140 ltO

97

29 25 22 19 16 14

180 150 130 ltO 90

97

30 27 23 20 17 14

170 160 140 125 97 69

25 23 20 18 14 10

165 150 130 110 83

24 22 19 16 12

160 140 ltO 90 69

23 20 16 13 lO

145 115

125 115 97 69 41

18 17 14 lO 6

125 110 90 62 38

18 16 13 9 5.5

lt5 lO5 76 52 28

17 15

ltO

It

62 38 23

16 13 9 5.5 3.4

lO 9 4.3 2.9 1.9

69 59 27 18

lO 8.5 3.9 2.6 1.6

66 45 23 13

66 32 18

9.5 4.7 2.6

40 36 32 27 23 19 39 34 26 22 18 14 33 29 25 22 18 14 9.5 26 24 22 19 15 lO 6.5 19 17 15 lO 6 3.2 10 9 4.7 3.2 2.1

69 62 30 20

13

44

It

44

7.5 4.1 9.5 6.5 3.3 1.9

2319 Chemical Composition. Composition Limits. 5.80 to 6.80 Cu, 0.20 to 0040 Mn, 0.10 to 0.25 zr, 0.10 to 0.20 Ti, 0.05 to 0.15 V, 0.20 Si max, 0.30 Fe max, 0.02 Mg max, 0.10 Zn max, 0.0008 Be max, 0.05 others max (each), 0.15 others max (total)

Specifications (U.S. and/or Foreign). UNS. A92319. Government. QQ-A-566. MIL-E-16053

Characteristics Major alloying elements: 5.3Cu-0.3Mn-0.18Zr-0.lOV

Typical Uses. Electrode and filler rod for welding 2219

Recommended Heat Treating Practice Annealing.Temperature is 415°C (775 OF)

90

90 69

90 69 59

90

44 41 40 39 38 38 34 30 25 22

24 20 16 13 lO

21 17 13 lO 8.5


2618 Chemical Composition. Composition Limits. 0.10 to 0.25 Si, 0.90

Forgings and rolled rings are treated to T61 temper by heating them to 200 °C (390 OF) and maintaining that temperature for 20 h

to 1.30 Fe, 1.90 to 2.70 Cu, 1.30 to 1.80 Mg, 0.90 to 1.20 Ni, 0.10 Zn max, 0.040 to 0.10 Ti, 0.05 others max (each), 0.15 others max (total), bal Al

Specifications (U.S. and/or Foreign). AMS. Forgings and forging stock: 4132; ASTM. Forgings: B 247; SAE. J454; Government. Forgings: QQ-A-367; MIL-A-22771; (France) NFA-U2GN; (United Kingdom) BS H12

2618 Aluminum: Tensile properties of 2618-T61

Available Product Forms. Forgings and rolled rings

Characteristics

'IYpical Allproducts Property limits Dieforgings.thickness91 in.(c) Axis parallelto grainflow Axisnotparalleltograinflow Handforgings Thickness$2.000 in.(c)(O Longitudinal Long transverse Short Iransverse 2.001-3.000 in. Longitudinal Long transverse Short transverse 3.001-4.000in. Longitudinal Long transverse Short transverse Rolledrings.thicknessg.5oo in.(g) Tangential Axial

An AI-Cu-Mg-Si alloy

Typical Uses. For elevated temperature service, such as die and hand forgings for pistons and rotating, aircraft engine parts, tire molds, and rolled rings

Recommended Heat Treating Practice Solution Heat Treating. Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. Quenching is by total immersion in water, unless otherwise indicated. Water should be at room temperature and cooled so that its temperature remains below 38°C (100 OF) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here for solution treatment are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±1OOF) during time at temperature. To obtain T4 temper, parts are treated at 530°C (985 OF)

y.,ld strength MPa ksI

'Ienslle strength MPa ksi

Product andorientation

E1ongation(a), %

440

64

372

54

1O(b)

400 380

58 55

310 290

45 42

4(d)(e) 4(d)

400 380 360

58 55 52

325 290 290

47 42 42

7 5 4

395 380 360

57 55 52

315 290 290

46 42 42

7 5 4

385 365 350

56 53 51

310 275 270

45 40 39

7 5 4

380 380

55 55

285 285

41 41

6 5

(a) In 50 rnm (2 in.) or4 d. where d is diameterof reducedsectionof tensiletest specimen. (b) 12.5 nun (0.5 in.) diameter specimen.(c) Propertiesalso apply to forgingsmachined prior 10 heat treatment, providedmachinedthicknessis notless than half of original(as-forged)thickness.(d) Specimen takenfrom forgings.(e)Elongation6% minforspecimentakenfromseparatelyforgedcoupon. (0 Maximum cross-sectional area 930 cm2 (I fe). Not applicable to upset biscuit forgings or to rolled rings. (g) Applicableonly to rings having ratio of outsidediameter 10 wall thicknessequal to or greaterthan 10

Precipitation Heat Treating (Artificial Aging). Temperatures given here are nominal and time at temperature is approximate. Specific times depend on time needed for load to reach temperature. Soak times are measured from time load reaches a temperature of 6 °C (10 OF) of applicable temperature.

2618 Aluminum: Creep-rupture properties 'Iemperature

°C

OF

150

300

177

350

205

400

260

500

315

600

Stressforcreepof

Time under stress.h

Rupture.tress MPa ksi

MPa

ksi

MPa

ksi

MPa

ksi

MPa

ksi

0.1 I 10 100 1000 0.1 I 10 100 1000 0.1 I 10 100 1000 0.1 I 10 100 1000 0.1 I 10 100 1000

380 360 340 305 255 340 310 285 250 205 290 260 230 195 160 185 165 140 105 62 97 69 52 32 20

345 340 325 305 255 325 305 275 240 200 285 255 220 185 150 170 150 130 97 62 83 62 45 28 17

50 49 47 44 37 47 44 40 35 29 41 37 32 27 22 25 22 19 14 9 12 9 6.5 4.1 2.5

345 330 315 290 250 315 295 260 235 195 270 250 215 180 145 165 145 125 90 55 69 55 41 26 14

50 48 46 42 36 46 43 38 34 28 39 36 31 26 21 24 21 18 13 8 10 8 6 3.7 2.1

330 315 295 270 240 295 275 250 220 185 255 235 200 165 130 160 140 110 69 48 55 45 38 19

48 46 43 39 35 43 40 36 32 27 37 34 29 24 19 23 20 16 10 7 8 6.5 5.5 2.8

315 290 270 240 205 285 255 220 185 150 240 205 170 140 90 145 115 83 52

46 42 39 35 30 41 37 32 27 22 35 30 25 20 13 21 17 12 7.5

48 41 26 15

7 6 3.8 2.2

55 52 49 44 37 49 45 41 36 30 42 38 33 28 23 27 24 20 15 9 14 10 7.5 4.6 2.9

1.0%

0.5%

0.1%

0.2%


2618 Aluminum: Microstructures. (a) 2618-T4 closed-die forging, solution heat treated at 530°C (985 OF) for 2 h, quenched in boiling water. Small particles of CuMgAI2 precipitated at grain boundaries; larger particles are insoluble FeNiAlg phase. 0.5% HF. 500x. (b) 2618-T4 forging, solution heat treated at 530°C (985 OF) for 2 h and cooled in still air. Slower cooling resulted in an increase of CuMgAI2 at grain boundaries and within grains. 0.5% HF. 500x. (c) 2618-T61 forging, solution heat treated, quenched in boiling water, aged at 200°C (390 OF) for20 h, stabilized at230 °C (450 OF) for? h. CuMgAI2 has also precipitated in grains. 0.5% HF.500x. (d) 2618-T61 forging, solution heat treated, cooled in still air, aged. Note increase in precipitation and alloy depletion near light grain boundaries. 0.5% HF. 500x

(b)

(a)

(c)

(d)

2618 Aluminum: Typical tensile properties of 2618-T61 at various temperatures Yieldstrength Temperature of -c

Tensile strength MPa ksi

(0.2 % offset) MPa ksi

-196 -80 -28 24 100 149 204 260 316 371

538 462 441 441 427 345 221

421 379 372 372 372 303 179 62 31 24

-320

-112 -18 75 212 300 400 500 600 700

90 52 34

78.0 67.0 64.0 64.0 62.0 50.0 32.0 13.0 7.5 5.0

61.0 55.0 54.0 54.0 54.0 44.0 26.0 9.0 4.5 3.5

Elongation,

%

12 11 10 10 10 14 24 50 80 120

3003, Alclad 3003 Chemical Composition. Composition Limits (3003). 0.60 Si max, 0.70 Fe max, 0.05 to 0.20 Cu, 1.00 to 1.50 Mn, 0.10 Zn max, 0.05 others max (each), 0.15 others max (total) Composition Limits (Alclad 3003). 7072 cladding-O.lO Cu max, 0.10 Mg max, 0.10 Mn max + Si, 0.80 to 1.30 Zn, 0.05 others max (each), 0.15 others max (total) Specifications (U.S. and/or Foreign). AMS. (See adjoining table); ASME. (See adjoining table); ASTM. (See adjoining table); SAE. J454; UNS. 3003: A93003; Government. (See adjoining table); (Canada) CSA MClO; (France) NFA-Ml; (United Kingdom) BS N3; (Germany) DIN AIMn.lSO: AIMnlCu Available Product Forms. Include sheet, plate, drawn and extruded tubing, pipe, extruded wire, rod, bar, and shapes, rolled or cold-finished rod, bar, wire, rivets, forgings and forging stock, foil, and fin stock

Characteristics Major alloying elements: 1.2Mn-0.12Cu

Typical Uses. Used mainly where good formability, very good resistance to corrosion, or good weldability (or all three) are required. Also has more strength than unalloyed aluminum. Applications include cooking utensils, food and chemical handling, and storage equipment, tanks, trim for transportation equipment, lithographic sheet pressure vessels, and piping. Tempers include 0, H12, H14, H16, H18, and H25. Farm roofing and siding are typical uses for Alclad 3003. For more information on resistance to corrosion, machinability, brazeability, and weldability per alloy and temper see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Annealing. Commercial practice is to treat at 400 to 600 °C (750 to 1110 OF). Higher temperatures are only used for flash annealing


3003 Aluminum: Mechanical properties

Thmper

'lYpica\ properties 0 H12 H14 H\6 H18 Property limits 0(0.006-3.000 in. thick) H12(0.017-2.000 in. thick) H14(0.009-1.000 in. thick) HI6 (0.006-{).162 in. thick) H18(0.006-0.128 in. thick) H1l2 (0.250-0.499in. thick) (0.500-2.000in. thick) (2.000-3.000in. thick) Property limits, AI.lad 3003(.) 0(0.006-0.499 in. thick) (0.500-3.000in. thick) H12 (0.017-0.499in. thick) (0.500-2.000in. thick) H14 (0.009-0.499in. thick) (0.500-2.000in. thick) H16 (0.006-0.162 in. thick) H18(0.006-0.128 in. thick) HI12 (0.250-0.499in. thick) (0.500-2.000in. thick) (2.000-3.000in. thick)

MPa

ThnsUe strength Iosl MPa

Yieldstrength ksI MPa

Elongation,

42 6 18 125 145 21 25 175 27 185 Minimum

30-40 10-20 8-16 5-14 4-10

27

83 115 145 165

5 12 17 21 24

14-25 3-10 1-10 1-4 1-4

17 15 14.5

69 41 41

10 6 6

8 12 18

110 16 19 130 150 22 175 25 200 29 Minimum 97 115 140 165 . 185 115 105 100

14 17 20

24

ksI

Maximum 130 160 180 205

19 23 26 30

34

90 97

13 14

125 130

18 19

31 34

110 115

16 17

150 160

22 23

83

11 12

4-9 10

130 140 160 180

19 20 23 26

170 180 200

25 26 29

110 115 140

16 17 20

1-8 10 1-4 1-4

110 105 100

16 15 14.5

62 41 41

9 6 6

8 12 18

n

4.5 5.0

~

Hanlneoo RB(a) HR

28 35 40 47 55

45-65 55-75 70-90 75-92 84-95 Minimum

Shear streugtb MPa IIsI

76 83

97 105 110

11 12 14 15 16

FatIgue I!reD&Ih(b) MPa IIsI

48 55 62 69 69

7 8 9 10 10

14-25 23

(a)500 kg load, 10mm ball, 30 s durationofloading. (b) At5 x 108 cycles.RR Moore type test.(c) Mechanicalpropertiesof 3003clad with7072 are practicallythe same as for bare material, except that hardnessand fatigueresistancetend to be slightly lowerfor the cladproduct


3003 Aluminum: Microstructures. (a) 3003-0 sheet, annealed. Longitudinal section shows recrystallized grains. Grain elongation indicates rolling direction, but not the crystallographic orientation within each grain. Polarized light. Barker's reagent. 100x. (b) 3003-0 sheet, annealed. Same as adjoining microstructure, but shown at a higher magnification. Dispersion of insoluble particles of (Fe,Mn)Al s (large) and aluminum-manganese-silicon (both large and small) was not changed by annealing. 0.5% HF.750x

(a)

(b)

3003 Aluminum: Microstructures. 3003-F sheet, hot rolled. Longitudinal section shows stringer of oxide from an inclusion in the cast ingot and particles of phases that contain manganese, both primary (large, angular) and eutectic (small). As-polished. 500x

3004, Alclad 3004 Chemical Composition. Composition Limits (3004). 0.25 Cu max, 0.30 Si max, 0.70 Fe max, 1.00 to 1.50 Mn, 0.80 to 1.30 Mg, 0.25 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al Composition Limits (Alclad 3004). 7072 cladding-Q.lO Cu max, 0.10 Mg max, 0.10 Mn max, 0.7 Fe max + Si, 0.80 to 1.30 Zn, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. 3004: sheet and plate, B 209; extruded tubing, B 221; welded tubing, B 313, B 547. Alclad 3004: sheet and plate, B 209; welded tubing, B 313; culvert pipe, B 547; SAE. J 454; UNS. A93004; Government: culvert pipe. WW-P-402; (Australia) A 3004; (France) NFA-MIG; (Germany) DIN AIMnlMgl Available Product Forms. Sheet, plate, drawn tubing. Alclad: sheet and plate

Characteristics Major alloying elements: 1.2Mn-l.0Mg. Provides combination of good formability and higher strength than alloy 3003.

Typical Uses. Drawn and ironed rigid containers (cans). Chemical-handling and storage equipment, sheet metal work, builders' hardware, incandescent and fluorescent lamp bases. Alclad: siding, culvert pipe, industrial roofing. For more information on resistance to corrosion, cold workability, machining, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Annealing. Product is treated at 415°C (775 OF)


3004 Aluminum: Mechanical properties Thmper

MPa

'IYpical properties 0 H32 H34 H36 H38 Property limits 0(0.006-3.000 in. thick) H32 (0.017-2.000 in. thick) H34 (0.009-1.000 in. thick) H36 (0.006-0.162 in. thick) H38 (0.006-0.128 in. thick) H112(0.250-3.000 in. thick) Property limits, Alclad 3004(c) 0 (0.006-0.499in. thick) (0.500-3.000in. thick) H32 (0.017-0.499in. thick) (0.500-2.000in. thick) H34 (0.009-0.499in. thick) (0.500-1.000in. thick) H36(0.006-0.162 in. thick) H38 (0.006-0.128 in. thick) H112 (0.250-0.499in. thick) (0.500-3.000in. thick)

ThnslJe strength MPa ksi

180 26 215 31 240 35 260 38 285 41 Minimum

ElongaUon,

ksi

Yield strength MPa ksi

20-25 10-17 9-12 5-9 4-6

Maximum

69 10 170 25 200 29 230 33 250 36 Minimum

%

150 195 220 240 260 160

22 28 32 35 38 23

200 240 260 285

29 35 38 41

59 145 170 195 215 62

8.5 21 25 28 31 9

10-18 1-6 1-5 1-4 1-4 7

145 150

21 22

195 200

28 29

55 59

8 8.5

10-18 16

185 195

27 28

235 240

34 35

140 145

20 21

1-6 6

215 220 235 255

31 32 34 37

255 260 275

37 38 40

165 170 185

24 25 27

1-5 5 1-4 1-4

150 160

22

59 62

8.5 9

7 7

23

Hardness, HB(a)

45 52 63 70 77

Fatigue strength(b)

Shearstrength MPa ksl

MPa

ksi

110 115 125 140 145

97 105 105 110 110

14 15 15 16 16

16 17 18 20 21

(a) 500 kg load, 10mm ball,30 s durationofloading. (b) At5 x 108 cycles,R.R.Moore type test.(c)Mechanicalpropertiesof 3004 clad with7072 are practicallythe sameas for bare material,exceptthat hardnessandfatigueresistancetend tobe slightlylowerfor the clad product

3004 Aluminum: Typical mechanical properties at various temperatures °C

Thmperalure OF

o temper -200 -328 -100 -148 -30 -22 25 77 100 212 200 392 300 572 400 752 H34temper -200 -328 -100 -148 -30 -22 25 77 100 212 200 392 300 572 400 752 H38lemper -200 -328 -100 -148 -30 -22 25 77 100 212 200 392 300 572 400 752

ThnslJestreogth(a) MPa ksi

Yield strength(a) MPa

Elongation,

ksi

%

290 200 180 180 180 96 50 30

42.5 29 26 26 26 14 7.2 4.4

90 80 69 69 69 65 34 9

13.2 11.5 10 10 10 9.5 4.9 2.8

38 31 26 25 25 55 80 90

360 270 245 240 240 145 50 30

52 39 36 35 35 21 7.2 4.4

235 212 200 200 200 105 34 19

34 31 29 29 29 15 4.9 2.8

26 17 13 12 12 35 80 90

400

58 45 42 41 40 22 7.2 4.4

295 267 245 245 245 105 34 19

43 39 36 36 36 15 4.9 2.8

20 10 7 6 7 30 80 90

310 290 280 275 150 50 30

(a) Loweststrengthsfor exposuresup to 10000 h at temperature, no load;test loadingappliedat 35 MPa/min(5 ksi/min) 10 yieldstrengthand thenat strainrate of 5%/minto fracture


3105 Chemical Composition. Composition Limits. 0.60 Si max, 0.70 Fe max, 0.30 Cu max, 0.20 to 0.80 Mn, 0.20 to 0.80 Mg, 0.20 Cr max, 0.40 Zn max, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. B 209; SAE. J 454 Available Product Forms. Sheet, in 0, H12, H14, H16, H18, and H25

Typical Uses. Residential siding, mobile home sheet, gutters and downspouts, sheet metal work, bottle caps, and closures. For information on resistance to corrosion, machinability, brazeability, and weldability see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

tempers


Characteristics

Annealing. Treatment temperature is 345°C (650 "F)

Major alloying elements: 0.55Mn-0.50Mg

3105 Aluminum: Mechanical properties of 3105 sheet Thmper

MPa

ThosUe strength ksi MPa

Shear strength ksI

Yieldstrength ksI

Elongation, %

MPa

55 8 19 130 150 22 25 170 195 28 23 160 Minimum

24 7 5 4 3 8

83 97 105 110 115 105

MPa

ksi

'Iypical properties

0 Hl2 H14 H16 Hl8 H25 Property limits

17 115 22 150 25 170 195 28 31 215 26 180 Minimum

0(0.013-0.080 in.thick) HI2 (0.017-0.080 in.thick) Hl4 (0.013-0.080 in.thick) HI6 (0.013-0.080 in.thick) HI8 (0.013-0.080 in.thick) H25(0.013-0.080 in.thick)

97 130 150 170 195 160

14 19 22 25 28 23

Maximum 145 180 200 220

34 105 125 145 165 130

21 26 29 32

12 14 15 16 17 15

16-20 1-3 1-2 1-2 1-2 2-6

5 15 18 21 24 19

4032 Chemical Composition. Composition Limits. 11.00 to 13.50 Si, 1.00 Fe max, 0.50 to 1.30 Cu, 0.80 to 1.30 Mg, 0.10 Cr max, 0.50 to 1.30 Ni, 0.25 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al

Specifications (U.S. and/or Foreign). AMS. Forgings and forging stock: 4145; ASTM. Forgings: B247; SAE. J454; Government. Forgings: QQ-A-367; Foreign. (Canada) CSA SG121; (France) NF A-SI2UN; (Italy) UNI P-AISi12MgCuNi

4032 Aluminum: Fatigue strength of 4032-16 at various temperatures "C

Thmperature OF

24

75

150

300

Available Product Forms. Forgings and forging stock

Characteristics An Al-Cu-Mg-Si alloy for high temperature service

Typical Uses. Pistons and other parts that see high temperatures. For information on resistance to corrosion, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter


205

260

Solution Heat Treating. Heat to 500 to 515°C (930 to 960 OF), hold for 4 min at temperature, then quench in cold water. Quench heavy or complicated forgings in water at 65 to 100 °C (150 to 212 "F) Precipitation Heat Treating (Artificial Aging). Die forgings are heated to 170 to 175°C (340 to 345 OF), and held 8 to 12 h at temperature Annealing. Metal is heated to 415°C (775 "F); held for 2 to 3 h at temperature, then furnace cooled to 260°C (500 "F) at 25°C (50 OF) per hour max

400

500

No.of cycles

4

10 105 106 107 108 5x 108 105 106 108 8 sx 10 105 106 107 108 sx 108 105 106 107 108 sx 108

Stress(a)

MPa

lui

359 262 207 165 124 114 207 165

52 38 30 24 18 16.5 30 24 13 11.5

90

79 186 138 90

55 48 131

83 55 34 34

27 20

13 8 7 19 12 8 5 5

(a)Basedon rotatingbeamtestsat roomtemperatureandcantileverbeamtestsatelevatedtemperatures


4032 Aluminum: Creep-rupture properties StressCor creepoC: 'Thmperature OF °C

TImeunder stress,h

Rupture stress MPa ksi

MPa

lui

MPa

lui

100

0.1 1 10 100 1000 0.1 1 10 100 1000 0.1 1 10 100 1000

331 317 303 296 296 290 276 269 248 207 234 214 186 138 83

283 283 283 276 276 276 269 255 241 200 228 207 179 131 76

41 41 41 40 40 40 39 37 35 29 33 30 26 19 11

269 262 262 262 255 248 241 234 221 186 221 200 165 124 69

39 38 38 38 37 36 35 34 32 27 32 29 24 18 10

212

150

300

205

400

48

46

44 43 43 42 40 39 36 30 34 31 27 20 12

0.2%

0.5%

1.0%

lui

MPa

138 131 103 59

20 19 15 8.5

4032 Aluminum: Typical mechanical properties of 4032-T6 at various temperatures -c

'Thmperature of

-200 -100 -30 25 100 200 300 400

'Thwile strength ksi MPa

-328 -148 -22 77 212 392 572 752

460 415 385 380 345 90 38 21

67

60 56 55 50 13 5.5 3.1

Yieldstrength MPa ksi

337 325 315 315 300 62 24 12

49 47

46 46 44 9 3.5 1.8

Elongation, 'lo

11 10 9 9 9 30 70 90

4043 Chemical Composition. Composition Limits. 4.50 to 6.00 Si, 0.80 Fe max, 0.30 Cu max, 0.05 Mn max, 0.05 Mg max, 0.10 Zn max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), 0.0008 Be max (welding electrode only), bal Al

Available Product Forms. Welding rod and electrodes

Major alloying element: 5.2 Si

Specifications (U.S. and/or Foreign). AMS. Bare welding rod and

Typical Uses. General purpose weld filler alloy (rod or wire) for welding

electrodes: 4190; SAE. J454; Government. Bare welding rod and electrodes: QQ-R-566, MIL-E-16053; spray gun wire: MIL-W-6712; (Australia) B 4043; (Canada)CSA S5; (France) NF A-S5; (United Kingdom) BS N21; (Germany) DIN AISi5, Werstoff-Nr. 3.2245

all wrought and foundry alloys (except those rich in magnesium)

Characteristics

Recommended Heat Treating Practice Annealing. Product is annealed at 350°C (660 "F)

5005 Chemical Composition. Composition Limits. 0.30 Si max, 0.70 Fe max, 0.20 Cu max, 0.20 Mn max, 0.50 to 1.10 Mg, 0.10 Cr max, 0.25 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al

clearer and lighter than anodized 3003, and color match with 6063 architectural extrusions is better

Typical Uses. Electrical conductor wire, cooking utensils, appliances,

Specifications (U.S. and/or Foreign). ASTM. Sheet and plate: B 209. Wire, HI9 temper; B 396. Stranded conductor: B 397. Rivet wire and rod: B 316. Rolled rod: B 531. Drawn tubing: B 483; SAE. J 454; UNS. A95005; Government. Rivet wire and rod: QQ-A-430; (France) NFA00.6; (United Kingdom) B5 N41; (Germany) DIN AIMg1. ISO: AIMgI

Available Product Forms. Sheet, plate, wire and rod, conductor, tubing. Tempers include 0, H12, H14, H16, H18, H32, H34, H36, H38

Characteristics Major alloying element: 0.8 Mg. Medium strength and good resistance to corrosion are properties similar to those of Alloy 3003. Anodized 5005 is

and architectural uses. o

For more information on resistance to corrosion, cold workability, machinability, brazeability, and weldability see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Annealing. Product is treated at 345°C (650 OF); holding at temperature is not required Hot Working Temperature. Range is 260 to 510 °C (500 to 950 "F)


5005 Aluminum: Mechanical property limitsfor sheet and plate Y;eld

Thnsilestrength

Minimum

Maximum

strength (min) ksi MPa

Thmper

MPa

ksi

MPa

ksi

0

105 125 145 165 185 120 140 160 180

15 18 21 24 27 17 20 23 26

145 165 185 205

21 24 27 30

35 95 115 135

5 14 17 18

160 180 200

23 26 29

85 105 125

12 15 18

115 105 100

17 15 15

H12 H14 H16 H18 H32 H34 H36 H38 H1I2 0.250-0.492 in. thick 0.492-1.60in. thick 1.60-3.20in. thick

5005 Aluminum: Typical mechanicalproperties

Elongation (min)!a), %

12-22 2-9 1-8 1-3 1-3 3-10 2-8 1-4 1-4 8 10 16

Thmper

0 Hl2 Hl4 H16 H18 832 834 836 838

Thnsile strength(a) ksi MPa

124 138 159 179 200 138 159 179 200

18 20 23 26 29 20 23 26 29

Yield strength(a) MPa ksi

41 131 152 172 193 117 138 165 186

6 19 22 25 28 17

20 24 27

E1ongation(a)(b),

Hardness(c),

%

DB

25 10 6 5 4 11 8 6 5

28

Shear strength ksi MPa

76 97 97 103 110 97 97 103 110

36 41 46 51

11 14 14 15 16 14 14 15 16

(a) Strengths and elongationsunchanged or improved at low temperatures.(b) 1.6nun (0.0625 in.) thickspecimen. (c) 500 kg load; 10nun diam ball

(a) In 50 nun (2 in.) or 5d, where d is diameter or reduced section of tensiletest specimen.Where a range of values appears in this colunm, the specified minimum elongation varies with thicknessof the mill product

5050 Chemical Composition. Composition Limits. 0040 Si max, 0.70 Fe max, 0.20 Cu max, 0.10 Mn max, 1.10 to 1.80 Mg, 0.10 Cr max, 0.25 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASlM. Sheet and plate: B 209. Drawn, seamless tubing: B 210. Drawn tubing: B 483. Welded tubing: B 313, B 547; SAE. J454; UNS. A95050; (France) NFA-G1; (Italy) P-AlMg1.5; (Switzerland) AI1.5Mg; (United Kingdom) BS 3L44. ISO: AlMg1.5

Hot Working Temperature. Product is heated in range of260 to 510 °C (500 to 950 oF)

5050 Aluminum: Typical tensile properties Thmperalure

Available Product Forms. Sheet, plate, tubing, pipe, rod, bar, wire

"C

Characteristics

-196

-SO -28

Major alloying element: 1.4 Mg

Typical Uses. Builder's hardware, refrigerator trim, coiled tubes, tubing for auto gas and oil lines, welded irrigation pipe. For information on resistance to corrosion, cold workability, machinability, braze ability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

-SO

Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 OF); holding at temperature is not required

5050 Aluminum: Tensile-property limits Thnsile strwgth (min) Thmper

MPa

ksl

o

125 150 170 185 200

18 22 25 27 29

H32 H34 836 838

Yield strength (min) MPa ksi

41 110 138 151

6 16 20 22

24 100 150 205 260 315 370 -196

Elongation (min)!a), %

16-20 4-6 3-5 2-4 2-4

(a) Wherea range of valuesappearsinthiscolunm,specified minimumelongation varieswith thickness of the mill product

-28 24 100 150 205 260 315 370 -196

-SO -28 24 100 150 205 260 315 370

OF

-320 -112 -18 75 212 300 400 500 600 700 -320 -112 -18 75 212 300 400 500 600 700 -320 -112 -18 75 212 300 400 500 600 700

Thnsilestrength(a) MPa ksi

Yield strength (0.2 % offset)!a) ksi MPa

255 150 145 145 145 130 95 60 41 27 305 205 195 195 195 170 95 60 41 27 315 235 220 220 215 185 95 60 41 27

70 60 55 55 55 55 50 41 29 18 205 170 165 165 165 150 50 41 29 18 250 205 200 200 200 170 50 41 29 18

37 22 21 21 21 19 14 9 6 3.9

44 30

28 28 28 25 14 9 6 3.9 46 34 32 32 31 27 14 9 6 3.9

10 8.5 8 8 8 8 7.5 6 4.2 2.6 30 25 24 24 24 22 7.5 6 4.2 2.6 36 30 29 29 29 25 7.5 6 4.2 2.6

(a) Lowest strengthsfor exposuresup to 10 000 h at temperature;no load; test loading applied at35 MFa/min (5 ksi/min) to yield strength and then at strainrate of 5%/min to fracture

Wrought Aluminum and Aluminum Alloys /187 5050 Aluminum: Typical mechanical properties

Thmper

Thmlle strength(a) MPa ksi

Yield streng!h(a) ksf MPa

0 H32 H34 H36 H38

145 170 190 205 220

55 145 165 180 200

21 25 28 30 32

Eiongation(a)(b), %

Hardnesste),

HB

Shearstrength MPa ksl

24 9 8 7 6

36 46 53 58 63

105 115 123 130 138

8 21 24 26 29

Fatigue strength(d) ksi MPa

15 17 18 19 20

83 90 90 97 97

12 13 13 14 14

8

(8) Strengths andelongationgenerally unchanged or improvedat lowtempemtures. (b) 1.6mrn(0.625in.) thicksheetspecimen. (c)500kg load;10mrndiamball.(d)At5 x 10 cycles;R.R.Mooretypetest

5052 Chemical Composition. Composition Limits. 0.25 Si max, 0.40 Fe max, 0.10 Cu max, 0.10 Mn max, 2.20 to 2.80 Mg, 0.15 to 0.35 Cr,O.lO Zn max, 0.05 others max (each), 0.15 others max (total), bal Al

Characteristics Major alloying elements: 2.5Mg-0.25Cr. Applied when a combination of good workability, good resistance to corrosion, high fatigue strength, weldability, and moderate static strength is required

Specifications (U.S. and/or Foreign). AMS. (See adjoining Table); ASTM. (See adjoining Table); SAE. J454; UNS. A95052; Government. Sheet and plate: QQ-A-250/8. Foil: MIL-A-81596. Rolled or cold finished wire, rod, and bar: QQ-A-22517. Drawn, seamless tubing: WW-T-700/4. Rivet wire and rod: QQ-A430. Rivets: MIL-R-24243; (Canada) CSA GR20; (France) NF A-G2.5C; (Italy) ON.l P-AlMg2.5; (Germany) DIN AIMg2.5. ISO: AIMg2.5

Typical Uses. Sheet metal work, hydraulic tubing, appliances, street light standards, rivets, and wire. Tempers include 0, H32, H34, H36, and H38. For more information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Available Product Forms. Sheet; plate; bar and shapes (extruded); wire, rod, and bar (rolled or cold fmished); tubing; rivet wire and rod; foil

Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)

5052Aluminum. Representative isothermal annealing curves for 5052-H18 350

50


505d.H18 300

250 ~

Q.

:;: • 200

t

~

~

150

:;

100

~

/175 °c (350 OF)

"\-

-. -, -

",I

/205 °c (400 OF)

40

"230°C (450 ° F)

'I

260°C (500 OF)

"'--

--

.L2 90 °c

r--2

(550°F)1

\315 °c (600 OF) 1

50

o

o

0.5

1.5

2.5 Time, h

3.5

4.5

188/ Heat Treater's Guide: Nonferrous Alloys 5052 Aluminum: Typical mechanical properties Elongation, ...(a) 'ThnslJe

YleId

'IOmper

lI!mIgth(a) MPa bi

0 H32 H34 H36 H38

195 230 260 '1J5 290

strength(a) MPa bi

28

90 195 215 240 255

33 38 40 42

U.5mm (0.51u.)

Bard......

dlam

HB(b)

25 12 10 8 7

'1J 16 12 9 7

47 60 68 73 77

13 28 31 35 37

Fatlgue

Shear

l.6mm (o.0625Iu.) thkk

strength MPa bi

MPa

bi

125 140 145 160 165

110 115 125 130 140

16 17 18 19 20

Itreogtb(cl

18 20 21 23 24

(a) Strengthsandelongationsunchangedor improvedat low temperatures. (b) 500kg load; 10mm warn ball.(c) At5 x loBcycles;RR Moore type test

5052 Aluminum: Typicaltensile properties at various temperatures Temperature 'IOmper

0

H34

H38

OC

-196

OF

-320 -SO -1l2 -28 -18 24 75 100 212 150 300 205 400 260 500 315 600 370 700 -196 -320 -SO -1l2 -28 -18 24 75 100 212 150 300 205 400 260 500 315 600 370 700 -196 -320 -80 -112 -28 -18 24 75 100 212 150 300

ThnsiJe strength MPa ksi 303 200 193 193 193 159 117 83 52 34 379 276 262 262 262 207 165 83 52 34 414 303 290 290 '1J6 234

44 29

28 28

28 23 17 12 7.5 5 55 40 38 38 38 30 24 12 7.5 5 60 44 42 42 40 34

YIeld Itreogth (0.2'" otr..,1) MPa bi

110 90 90 90 90 90 76 52 38 21 248 221 214 214 214 186 103 52 38 21 303 262 255 255 248 193

16 13 13 13 13 13 II

7.5 5.5 3 36 32 31 31 31 27 15 7.5 5.5 3 44 38 37 37 36 28

5052 Aluminum: Standard specifications SpecUkationNo.

Elongation,

...

46 35 32 30 36 50 60 80 110 130 28 21 18 16 18 27 45 80 110 130 25 18 15 14 16 24

MID Conn

Sheetandplate Sheet,plate.bar.andshapes(extruded) Wire. rod.and bar(rolledor cold finished) 1\100 Drawn Drawn. seamless Hydraulic Extruded Extruded. seamless Condenser Condenserwith integral fins Welded Rivetwireandrod Foil

AMS

ASTM

4015 4016.4017 4114

B209 B221 B211

4069 4070 4071

B483 B210 B221 B241 B234 B404 B313,B547 B316

4004

5056, Alclad 5056 Chemical Composition. Composition Limits (5056). 0.30 Si max, 0.40 Fe max, 0.10 Cu max, 0.05 to 0.20 Mn, 4.50 to 5.60 Mg, 0.20 Cr max, 0.10 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al Composition Limits (Alclad 5056). 6253 cladding-Si, 45 to 65% of Mg content, 0.50 Fe max, 0.10 Cu max, 1.00 to 1.50 Mg, 0.15 to 0.35 Cr, 1.60 to 2.40 Zn, 0.05 others max (each), 0.15 others max (total), bal AI Specifications (U.S. and/or Foreign). AMS. Rolled or cold fmished wire, rod, and bar: 4182. Foil: 4005; ASTM. Rivet wire and rod: B 316. Rolled or cold fmished wire, rod, and bar: B 211. Alclad, rolled or cold finished wire, rod, and bar: B 211; SAE. J 454; UNS. A95056; Government. Rivet wire and rod: QQ-A430, foil: MIL-A-8l596; (Austria) AlMg5; (Canada) CSA-GM50R; (United Kingdom) BS N6 2L.58; (Germany) DIN AlMg5. ISO: AlMg5

Available Product Forms. Rolled or cold finished wire, rod, and bar; rivet wire and rod

Characteristics Major alloying elements: 5.0Mg-0.1Mn-0.lCr

Typical Uses. Rivets for use with magnesium alloy and cable sheathing, zipper stock, and nails. Alclad wire is used exclusively in the fabrication of insect screens and other instances where wire products require good resistance to corrosion. For more information on resistance to corrosion, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Annealing. Treatment is at 415°C (775 "F); holding attemperature is not required

Hot Working Temperature. Range is 315 to 480°C (600 to 900 oF)


5056 Aluminum: Typical mechanical properties 'ThnslJe strength(a) MPa ksl

'Thmper

0 H18 H38

290 434 414

Yieldstrength(a) MPa ksl

42 63 60

152 407 345

22 59 50

Eiongallon(a)(h), %

Hanlness(c), HB

35 10 15

65 105 100

Fatigue otrength(d) MPa ksi

Shearstrength MPa ksi

179 234 221

138 152 152

26

34 32

20 22 22

8 (8) Strengthsand elongationare unchangedor improvedat low temperatures. (b) 12.5rom(0.50in.) dlam;roundspecimen.(c) 500 kg load; 10 romdiam ball.(d)At 5 X 10 cycles; R.R Moore type test

5056 Aluminum: Typical tensileproperties 'Iemperamre

'Thmper

-c

OF

0

24 150 205 260 315 370 24 150 205 260 315 370

75 300 400 500

H38

'ThnslJe strength(a) ksl MPa

y,.ld strength(a) ksJ MPa

Elongation, %

5056 Aluminum: Mechanical-property limits for rolled or cold finished wire,rod, andbar 'Thnslle s!mlgth(mia) MPa ksl

Thmper

600

700 75 300 400 500 600

700

290 214 152 110 76 41 414 262 179 110 76 41

42 31 22 16 11 6 60 38 26 16 11 6

150 117 90 69 48 28 345 214 124 69 48 28

22 17 13 10 7 4 50 .31 18 10 7 4

35 55 65 80 100 130 15 30 50 80 100 130

(8) Loweststrengthsfor exposuresup to 10000 h at temperature, no load;testloadingappliedat 35 MPalmin (5 ksilmin)to yieldstrengthand then at strainrate of5%/min to fracture

BareSOS6 0 Hlll H12 H32 H14 H34 H18 H38 H192 H392 AicladSOS6 H192 H392 H393

315 (max) 305 315 305 360 345 400 380 415 400 360 345 370(a)

46 (max)

44 46

44 52 50 58 55 60 58 52 50 54

(a)Yieldstrength (min), 325 MPa (47 ksi)

5083 Chemical Composition. Composition Limits. 0040 Si max, 0040 Fe max, 0.10 Cu max, 0040 to 1.00 Mn, 4.00 to 4.90 Mg; 0.05 to 0.25 Cr, 0.25 Zn max, 0.15 Ti max, 0.05 othersmax (each), 0.15 others max (total),bal AI Specifications (U.S. and/or Foreign). AMS. Sheet and plate: 4056, 4057,4058,4059; ASTM. Sheet and plate: B 209. Extruded wire, bar, rods, shapes, and tubing: B 221. Extruded seamless tubing: B 241. Drawn seamless tubing: B 210. Welded tubing: B 547. Forgings: B 247. Gas and oil transmission pipe: B 245; SAE. J454; Government. Sheet and plate: QQ-A-250/6. Extruded wire, rod, bar, shapes and tubing: QQ-A-200/4. Forgings: QQ-A-367. Armor plate: MIL-A-46027. Extruded armor: MILA-46083. Forged armor: MIL-A-45225; (Canada) CSA GM4l; (United Kingdom) BS H8; (Germany) DIN AIMg4.5Mn, Werstoff-Nr. 3.3457, ISO: AIMg4.5Mn Available Product Forms. Sheet; plate; extruded wire, rod, bars, shapes, and tubing; extruded seamless tubing; drawn seamless tubing; welded tubing; forgings; gas and oil transmission pipe

Characteristics

For information on resistance to corrosion, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter


5083 Aluminum: Typical tensile properties 'Thmper

'Thnsll.strength(a) MPa ksi

YIeldsIreDgtb MPa ksi

Eiongatlon(a)(h), %

Major alloying elements: 4.4Mg-0.7Mn-0.15Cr. Suitable for applications requiring weidability, moderate high strength, and good resistance to corrosion

0 8112 H116 H321 H323,H32 H343,H34

Typical Uses. Marine, auto, and aircraft parts; unfired pressure vessels; cryogenics; TV towers; drilling rigs, transportation equipment, missile components, and armor plate. Tempers include H32l, H1I6, HIll.

(a)Strengthsand elongationsare unchangedor improvedatlow temperatures, (b) 1.6rom(0.0625 in.) thickspecimens

290 303 317 317 324 345

42

44 46 46 47 50

145 193 228 228 248 283

21 28 33 33 36 41

22 16 16 16 10 9

190 I Heat Treater's Guide: Nonferrous Alloys 5083 Aluminum: Mechanical-property limits Tensile strength Minimum MPa ksi

Temper

Yield strength Maximum MPa ksl

Minimum ksi MPa

350 345

125 lI5 lIO 105 95

18 17 16 15 14

Maximum MPa ksi

Elongation (min)(a),%

0 0.051-1.5000in. thick 1.501-3.000in. thick 3.001-5.000in. thick 5.001-7.000in. thick 7.001-8.000in. thick HlI2 0.250-1.500in. thick 1.501-3.000in. thick H1l6 0.063-1.500in. thick 1.501-3.000in. thick H321 0.188-1.500in. thick 1.501-3.000in. thick H323 H343

16 16 14-16 14 12

40 39 38 37 36

275 270

40 39

125 lI5

18 17

12 12

305 285

44 41

215 200

31 29

12 12

305 285 310 345

44 41 45 50

215 200 235 270

31 29 34 39

385 385 370 405

51 50

56 56 54 59

200 200

29 29

275 270 260 255 250

295 295 305 340

43 43 44 49

12 12 8-10 6-8

(a) In 50 nun (2 in.) or 4d, where d is diameterof reduced sectionof tensiletestspecimen.Wherea range of valuesappearsin thiscolumn, the specifiedminimumelongationvaries with thicknessof the mill product

5083 Aluminum: Microstructures. (a) 5083-H112 plate, cold rolled. Longitudinal section shows particles of primary MnAl a (gray, outlined). Small, dark areas may be particles of insoluble phases, such as phases that contain magnesium (for example, M92Si) or that contain manganese. Keller's reagent. 50x. (b) 5083 plate, cold rolled. The coarse, gray areas are particles of insoluble (Fe,Mn)aSiAI,2; adjacent black areas are voids caused by breakup of the brittle (Fe,Mn)aSiAI'2 particles during cold rolling. Separate black areas may be insoluble particles of M9 2Si. As-polished. 500x

(a)

(b)

5083 Aluminum: Typical tensile properties at various temperatures 'Thmperature OF -c

-195

-80 -30 25 100 150 205 260 315 370

-315 -lI2 -22 80 212 302 400 500 600 698

'Iensile strength(a) MPa ksl

405 295 290 290 275 215 150 115

75 41

59 43 42 42 40 31 22 17 II 6

Yield strength (0.2% offset)(a) MPa ksl

165 145 145 145 145 130 115 75 50 29

24 21 21 21 21 19 17 II 7.5 4.2

Elongation, %

36 30 27 25 36 50 60 80 lIO 130

(a) Loweststrengthfor exposures up to 10 000 h at temperature, no load; test loadingappliedat 35 MPalmin(5 ksilmin)to yield strengthand then at strainrate of IO%/min to fracture


5086, Alclad 5086 Chemical Composition. Composition Limits. 0040 Si max, 0.50 Fe max, 0.20 to 0.70 Mn, 3.50 to 4.50 Mg, 0.25 Zn max, 0.15 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Sheet and plate: B 209. Extruded bar, wire, rod, shapes, and tubing: B 221. Extruded seamless tubing: B 241. Drawn seamless tubing: B 313, B 547. Gas and ore transmission pipe: B 345. Alclad 5086. Sheet and plate: B 209; SAE. J454; UNS. A95086; Government. Sheet and Plate: QQ-A-250/7, QQ-A-250/19. Extruded wire, rod, bar, shapes, and tubing: QQ-A-200/5. Drawn, seamless tubing: WW-T-700/5; Foreign. (France) NFA-G4MC; (Germany) DIN AlMg4. ISO: AlMg4 Available Product Forms. Sheet; plate; extruded wire, rod, bar, shapes, and tubing; welded tubing; gas and oil transmission pipe. Alclad, sheet and plate

Characteristics Major alloying elements; 4.0Mg-OAMn-0.15Cu. Applications include those requiring a weldable, moderate strength alloy with comparatively good resistance to corrosion

Typical Uses. Marine, auto, and aircraft parts, cryogenics, TV towers, drilling rigs, transportation equipment, missile components, armor plate, and unfired, welded pressure vessels.

5086 Aluminum: Microstructure. 5086-H34 plate, 13-mm (0.5in.) thick, cold rolled and stabilized at 120 to 175 0p (250to 350 OF) to prevent age softening. Undesirable continuous network of M92Al a particles precipitated at grain boundaries; large particles are insoluble phases. 25% HNOa• 250x

For additional information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required Hot Working Temperature. The range is 315 to 480 °C (600 to 900 OF)

5086 Aluminum: Typical tensile properties of 5086-0 at various temperatures Temperature

-c

-196 -80 -28 24 100 149 204 260 316 371

OF

-320 -112 -18 75 212 300 400 500 600 700

Tensile strength(a) ksi MPa 379 269 262 262 262 200 152 117 76 41

Yield strength (0.2 % ofl'set)(a) MPa ksi 131 117 117 117 117 110 103 76 52 29

55 39 38 38 38 29 22 17 11 6

Elongation, %

46 35 32 30 36 50 60 80 110 130

19 17 17 17 17 16 15 11 7.5 4.2

(a)Lowest strengthsfor exposuresup to 10 000 h at temperature, no load; test loadingappliedat 35 MPalmin(5 ksilmin)to yieldstrengthand thenat strainrate of 5%/minto fracture

5086 Aluminum: Tensile properties Temper Typical properties 0 H32,H1l6 H34 H112 Property limits 0(0.020-2.000 in. thick) H32 (0.020-2.000in.thick) H34(0.009-1.000in. thick) H36(0.006-0.162in. thick) H38(0.006-0.020in. thick) H112 (0.188-0.499in. thick) (0.500-1.000 in. thick) (1.001-3.000in. thick) (2.001-3.000in. thick) H116(0.063-2.000in. thick)

MPa

Tensile strength ksi MPa

260 38 42 290 47 325 270 39 Minimum 240 275 305 325 345

35 40 44 47 50

250 240 240 235 275

36 35 35 34 40

ksi

Maximum 305 325 350 370

44 47 51 54

Yield strength Elongation(a), MPa ksi %

115 17 205 30 255 37 130 19 Minimum

22 12 10 14 Minimum

95 195 235 260 285

14 28 34 38 41

15-18 6-12 4-10 3-6 3

125 110 95 95 195

18 16 14 14 28

8 10 14 14 8-10

(a) In 50 rom (2 in.) or 4d,where d is diameterof reduced sectionof tensile test specimen.Wherea range of values appearsin this column,specifiedminimumelongationvaries with thicknessof the millproduct

51 Chemical Composition. Composition Limits. 0.25 Si max, 0.40 Fe max, 0.10 Cu max, 0.10 Mn max, 3.10 to 3.90 Mg, 0.15 to 0.35 Cr, 0.20 Zn max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total),bal AI

seamless tubing: B 210. Welded tubing: B 313, B 547; SAE. J454; UNS. A95154; (Canada) CSA GR40; (France) NF A-GC3; (United Kingdom) BS N5. ISO: AIMg3.5

Specifications (U.S. and/or Foreign). AMS. Sheet and plate: 4018, 4019; ASTM. Sheet and plate: B 209. Rolled or cold finished wire, rod, and bar: B 211. Extruded wire, rod, bar, shapes, and tubing: B 221. Drawn,

Available Product Forms. Sheet and plate; rolled or cold finished wire, rod, and bar; extruded wire, rod, bar, shapes, and tubing; drawn seamless tubing; and welded tubing

192/ Heat Treater's Guide: Nonferrous Alloys 5154 Aluminum: Typicaltensile properties of 5154-0 at various temperatures

Characteristics Major alloying elements: 3.5Mg-0.25Cr

Typical Uses. Welded structures, storage tanks, pressure vessels, marine structures, and transportation trailer tanks. For additional information on corrosion resistance, cold workability, machinability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

-1%

--so -28 24 100 150 205

Recommended Heat Treating Practice Annealing. Treatmentis at 345°C (650 OF); holding at temperature is not

260

required

315 370

Hot Working Temperature. Range is 260 to 510 °C (500 to 950 OF)

YIeld strength !O.2%oft'.gel) MPa ksi

'lOruile strength MPa ksI

'Iemperamre OF "C

-320 -112 -18 75 212 300 400 500 600 700

360 250 240 240 240 200 150 115 75 41

130 115 115 115 115 110 105 75 50 29

52 36 35 35 35 29 22 17 11 6

19 17 17 17 17 16 15 11 7.5 4.2

FJongation!a),

...

46 35 32 30 30 50 60 80 110 130

(a)In 50mm (2 in.) or 4d.whered is diameterof reducedsectionoftensiletestspecimen

5154 Aluminum: Mechanical properties Thmper

'JYpicalproperties 0 H32 H34

H36 H38 Hll2 Property limits 0(0.020-3.000 in. thick) H32(0.020-2.000 in. thick) H34 (0.009-1.000 in. thick) H36 (0.006-0.162 in. thick) H38(0.006-0.128 in. thick) Hll2 (0.250-0.499in. thick) (0.500-3.000in. thick)

MPa

Yieldstrength ks\ MPa

EIongation!a),

ksi

...

1Iardness(h). HB

27 15 13 12 10 25

58 67 73 78 80 63

Maximum

117 17 207 30 33 228 248 36 39 269 117 17 Minimum

'lO...itestrength ksi MPa

240 35 270 39 42 290 310 45 330 48 240 35 Minimum 205 250 270 290 310

30 36 39 42 45

220 205

32 30

285 295 315 340

41 43 46 49

75 180 200 220 240

11 26 29 32 35

12to 18 5to 12 41010 3105 3105

125 75

18 11

8 11to 15

Shear strengtb MPa

ksI

152 152 165 179 193

22 22 24 26

28

Fatigue strength!e) ksi MPa

117 124 131 138 145 117

17 18 19 20 21 17

(a) In 50 mm (2 in.) or4d. where d is diameterof tensileteslspecimen. Wherea rangeof valuesappearsin thiscolumn.specifiedminimumelongationvarieswith thickness of themillproduct. (h) 500 kg load;10mmball.(c)At 5 X 108 cyclesof completely reversedstress;R.R.Mooretypetest

5182 Chemical Composition. Composition Limits. 0.20 Si max, 0.35 Fe

Hot Working Temperature. Range is 260 to 510 °C (500 to 950 "F)

max, 0.15 Cu max, 0.20 to 0.50 Mn, 4.00 to 5.00 Mg, 0.10 Cr max, 0.25 Zn max, 0.10 Ti max. 0.05 others max (each), 0.15 others max (total), bal AI

Specifications (U.S. and/or Foreign). UNS. J95182 Available Product Form. Sheet

Characteristics Major alloying elements: 4.5Mg-0.35Mn

Typical Uses. Container ends, auto body panels and reinforcement members. brackets, and parts

Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 oF)

5182 Aluminum: Typicaltensile properties 'Iemper

o H32 H34 HI9(c)

'lOmitestrengthCa) MPa ksi

276 317 338 421

40 46 49 61

Yieldstrength!a) MPa ksi

138 234

283 393

19 34 41 57

Elongalion!a)(h),

...

25 12 10 4

(a) Strengths and elongations are unchanged or increasedat low temperatures. (h) 1.6mm (0.0625 in.) thickspecimen. (c)Propertiesof thistemperareforcontainerendstock0.25to 0.38mm(0.010 100.015in.) thick

Next Page Wrought Aluminum and Aluminum Alloys

/193

5252 Chemical Composition. Composition Limits. 0.08 Si max, 0.10 Fe max, 0.10 Cu max, 0.10 Mn max, 2.20 to 2.80 Mg, 0.05 Zn max, 0.05 V max, 0.03 others max (each), 0.10 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Sheet: B 209; SAE. J454;lnNS.A95252


Available Product Forms. Sheet 5252 Aluminum: Tensile properties

Characteristics

YIeld strength MPa Ilsi

'l\",.1Ie strength

Major alloying element: 2.5Mg. Can be bright dipped or anodized to give a bright. clear finish Typical Uses. Sheet metal work, hydraulic tubing, automotive and appliance trim, where more strength than that provided by other trim alloys is needed. Available tempers include 0, H32, H34, H36, H38. For additional information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

MPa

Thmper

Ilsi

MPa

Ilsi

'IYPicalproperties H25 235 34 170 H28,H38 283 41 240 Property limits for 0.75-2.3 mm (0.030-0.090in.) thick sheet Minimum Maximum 205 215 260

H24 H25 H28

30 31 38

260 270

EIoogatloo(a).

...

l1(a) 5(a)

25 35

Minimum 10 9 3

38 39

(a) 1.6 mm(0.0625in.) thickspecimen

5254 Chemical Composition. Composition Limits. 0.45 Si max + Fe, 0.05 Cu max, 0.01 Mn max, 3.10 to 3.90 Mg, 0.15 to 0.35 Cr, 0.20 Zn max, 0.05 Ti max, 0.05 others max (each), 0.15 others max (total), bal AI Specifications (U.S. and/or Foreign). ASTM. Sheet and plate: B 209. Extruded seamless tubing: B 241; SAE. J454; UNS. A95254; (Canada) CSA GR40 Available Product Forms. Sheet and plate

Typical Uses. Storage vessels for hydrogen peroxide and other chemicals. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter


Characteristics

Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required

Major alloying elements: 3.5Mg-0.25Cr


5254 Aluminum: Mechanical properties Thnsile strength Thmper

MPa

ksi

MPa

ksi

YIeld strength MPa kst

Elongation,

115 17 205 30 23G 33 250 36 270 39 115 17 Minimum(d)

27 15 13 12 10 25

...

H~(a).

Shear strength Ilsi

HB

MPa

58 67 73 78 80 63

150 150 165 180 195

Fa!igue strengthlb) Ilsi MPa

'Iypleal properties(c)

o H32 H34 H36 H38 H112 Property limits

o H32 H34 H36 H38 H112 6-12.5 mm(0.250-0.499in.) thick 13-75mm (0.500-3.000in.)thick

240 35 270 39 290 42 310 45 330 48 240 35 Minimum 205 250 270 290 310

30 36 39 42 45

220 205

32 30

Maximum 285 295 315 340

41 43 46 49

75 180 200 220 240

11 26 29 32 35

12-18 5-12 4-10 3-5 3-5

125 75

18 11

8 11-15

22 22

24 26 28

115 125 130 140 145 115

17 18 19 20 21 17

(a) 500kgload; 10mm ball, (b) At5 X 108cycles;R.R. Mooretypetest.(c)Strengthsandelongationsareunchangedor Increasedatlow tempemtures. (d)In 50 mm (2 in.) or 41. whered isdiameterof reduced sectionof testspecimen.Wherea rangeof valuesappearsin thiscolumn,specifiedminimumelongationvarieswith thicknessof the millproduct

Previous Page

194/ Heat Treater's Guide: Nonferrous Alloys 5254 Aluminum: Typical tensile properties of 5254-0 at various temperatures °C

Thmperature of

-196 -80 -28 24 100 ISO 205 260 315 370

'Iensile strength(a) MPa ksi

-320

-112 -18 75 212 300 400 500 600 700

360 250 240 240 240 200 150 ll5 75 41

52 36 35 35 35 29 22

17 II 6

Yield strengthla) MPa ksi

130 ll5 ll5 ll5 ll5 llO 105 75 50 29

19 17 17 17 17 16 IS II 7.5 4.2

Elongation,

%

46 35 32 30 36 50 60 80 llO 130

(a) Loweststrengthsfor exposure up to 10 000 h at temperature, no load; testloadingappliedat 35 MPa/min(5 ksi/min)to yieldstrengthand then at strainrate of 5%/min to fracture

5356 Chemical Composition. Composition Limits. 0.25 Si max, 0.40 Fe max, 0.10 Cu max, 0.05 to 0.20 Mn, 4.50 to 5.5 Mg, 0.05 to 0.20 Cr, 0.10 Zn max, 0.06 to 0.20 Ti, 0.05 others max (each), 0.15 others max (total), balAI

Characteristics Major alloying elements: 5.0Mg-0.12Mn-0.12Cr Typical Uses. Welding base metals high (73%) in magnesium

Specifications (U.S. and/or Foreign). UNS. A95356; Government. QQ-R-566, MIL-E-16053; (Canada) CSA GM50P; (France) NF A-GS


Available Product Forms. Welding electrodes and filler wire

Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)

5454 Chemical Composition. Composition Limits. 0.25 Si max, 0.40 Fe max, 0.10 Cu max, 0.50 to 1.00 Mn, 2.40 to 3.00 Mg, 0.05 to 0.20 Cr, 0.25 Zn max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al

Hot Working Temperatures. Range is 260 to 510 °C (500 to 950 "F)

Specifications (U.S. and/or Foreign). ASTM. Sheet and plate: B 209. Extruded wire, rod, bar, shapes, and tubing: B 221. Extruded seamless tubing: B 241. Condenser tubing: B 234. Condenser tubing with integral fins: B 404. Welded tubing: B 547; SAE. J454; UNS. A95454; Government. Sheet and plate: QQ-2501l0. Extruded wire, rod, bar, shapes, and tubing: QQ-A-2oo/6; (Canada) CSA GM31N; (France) NF A-G2.5MC; (United Kingdom) B5 N51; (Germany) DIN AIMg2.7Mn. ISO: AIMg3Mn

5454 Aluminum: Microstructure. 5454, hot-rolled slab, longitudinal section. Oxide stringer from an inclusion in the cast ingot. The structure also shows some particles of (Fe,Mn)Al a (light gray). As-polished. 50 Ox

Available Product Forms. Sheet; plate; extruded wire, rod, bar, shapes, and tubing

Characteristics Major alloying elements: 2.7Mg-0.8Mn-0.12Cr Typical Uses. Welded structures, pressure vessels, and tubing for marine service. Available in 0, H32, H34, and HIll tempers. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Annealing. Treating is at 345°C (650 OF); holding at temperature is not required


5454 Aluminum: Typical tensile properties of 5454 at various temperatures

5454 Aluminum: Mechanical properties Yield Temper

Tensile strength MPa ksi MPa ksI

strength MPa ksi

Elongatloo,%

250 275 305

22 10 10 8 8 14 18 18

Shear Hardness strength (a),HB MPa ksi

H32 H34 H36 H38 Hlll H112 H311 Property limits

0 H32 H34 H112 6-12.5mm (0.250-0.499 in.) thick 13-75mm (0.500-3.00 in.) thick

OF

Teosile strength(a) MPa ksi


Eloogalioo, %

o temper

'IYpical properties

0

Thmperature °C

36 40

49 54 260 38 250 36 38 260 Minimum

Maximum

117 17 207 30 241 35 276 40 310 45 179 26 124 18 26 179 Minimum

215 250 270

31 36 39

285 305 325

85 180 200

12 26 29

12-18(b) 5-12(b) 4-10(b)

220

32

125

18

8

215

31

85

12

11-15(b)

44

340 370

41

44 47

62 73 81

159 165 179

23 24 26

70 62 70

159 159 159

23 23 23

-196 -80 -28

24

(a) 500 kg load; 10 mm ball. (b) Range of values indicates that specified minimum elongation varies with thickness of mill product

100 150 205 260 315 370

-320 -112 -18 75 212 300

400 500 600 700

370 255 250 250 250 200 150 115 75 41

54 37 36 36 36 29 22 17 11 6

130 115 115 115 115 110 105 75 50 29

19 17 17 17 17 16 15 11 7.5 4.2

39 30 27 25 31 50 60 80 110 130

405 290 285 275 270 220 170 115 75 41

59 42 41 40 39 32 25 17 11 6

250 215 205 205 200 180 130 75 50 29

36 31 30 30 29 26 19 11 7.5 4.2

32 23 20 18 20 37 45 80 110 130

63

285 250 240 240 235 195 130 75 50 29

41 36 35 35 34 28 29 11 7.5 4.2

30 21 18 16 18 32 45 80 110 130

H32temper -196 -80 -28 24 100 150 205

-320 -112 -18 75 212 300

260

500

315 370

700

400 600

H34temper -196 -80 -28 24 100 150 205 260 315 370

-320 -112 -18 75 212 300

400 500 600 700

435 315 305 305 295 235 180 115 75 41

46

44 44 43 34 26 17 11 6

(a) Lowest strengths for exposures up to 10 000 h at temperature, no load, test loading applied at 35 MPalmin (5 ksilmin) to yield strength and then at strain rate of 5%/min to fracture

5456 Chemical Composition. Composition Limits. 0.25 Si max, 0.40 Fe max, 0.10 Cu max, 0.50 to 1.00 Mn, 4.70 to 5.50 Mg, 0.05 to 0.20 Cr, 0.25 Cr max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), bal A1 Specifications (U.S. and/or Foreign). ASTM. Sheet and plate: B 209. Extruded wire, rod, bar, shapes, and tubing: B 221. Extruded seamless tubing: B 241. Drawn, seamless tubing: B 210; SAE. J454; UNS. A95456; Government. Sheet and plate: QQ-A-250/9, QQ-A-250/20. Extruded wire, rod, bar, shapes, and tubing: QQ-A-200/7. Armor plate: MIL-A-46027. Extruded armor: Mll..-A-46083. Forged armor: Mll..-A-45225

Available Product Forms. Sheet; plate; extruded wire, rod, bar, shapes, and tubing, armor plate

Characteristics Major alloying elements: 5.IMg-0.8Mn-0.12Cr

Typical Uses. High strength welded structures, pressure vessels, marine applications, storage tanks, armor plate. Available in 0, H32l, and Hl16 tempers, For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required


196/ Heat Treater's Guide: Nonferrous Alloys 5456 Aluminum: Tensile properties 'Iemper

MFa

ThnsiIe strength k.si MPa

Typical properties 0 H111 H112 H321(b), H116(c)

310 324 310 352

45 47 45 51

ksl

MPa

YIeld strength k.si MPa

159 228 165 255

23 33 24 37

Elongation, %

k.si

24(a) 18(a) 22(a) 16(a) Mlnlmum(d)

Property 1Imlts

Mlnlmum

Maximum

Mlnlmum

InSOmm

Maximum

In5d(S.6S.,pt)

0 1.20-6.30 mmthick 6.30-80.00 mmthick 80.00-120.00 mmthick 120.00-160.00 mmthick 160.00-200.00 mmthick H1I2 6.30-40.00 mmthick 40.00-80.00 mmthick H116(c)(e) 1.60-30.00 mmthick 30.00-40.00 mmthick 40.00-80.00 mmthick 80.00-110.00 mmthick H321 4.00-12.50 mmthick 12.50-40.00 mmthick 40.00-80.00 mmthick H323 1.20-6.30 mmthick H343 1.20-6.30 mm thick

130 125 120 115 105

19 18 17 17 15

42 41

130 125

19 18

12

10 10

46

230 215 200 170

33 31 29 25

10

10 10 10 10

290 285 275 270 265

42 41 40 39 38

290 285 315 305 285 275

365 360

53 52

44

41 40

315 305 285

46 44

205 205

30 30

16 16

12

41

405 385 385

59 56 56

230 215 200

33 31 29

315 305 295

43

330

48

400

58

250

36

315

46

6t08

365

53

435

63

285

41

350

51

6t08

46 44

14 12 12 10

10 10

(a) 12.5(0.5 in.) diam specimen. (b)Material in thistempernotrecommended forapplications requiring exposuretoseawater. (c)Hl16 designation alsoappliesto thecondition previously designated H117. (d) Elongations in 50 mm(2 in.) applyto thicknesses through12.5mm(0.5 in.); elongations in 5d (5.65.,pt), whered is diameter andAis cross-sectional areaof tensiletestspecimen, applyto material over 12.5mm(0.5 in.) thick.(e)Materialin thistemperrequired to passanexfoliation corrosiontestadministered by thepurchaser

5456Aluminum: Microstructures. (a) 5456plate, hot rolled.Longitudinal section, Polarized light. Partial recrystallization occurred immediatelyafter hot rollingfrom residual heat. This type of recrystallization is frequently referred to as "dynamic recrystallization." Barker's reagent. 100x. (b) 5456 plate, 6.4 mm (0.25 in.) thick, cold rolled and stress relieved below the solvus at 245°C (475 OF). Particles are (Fe,Mn)Ala (gray), M92Si (black), andM92AI3 (fineprecipitate). Thereis nocontinuous networkof precipitate at grainboundaries. 25%HN03 • 500x. (c) 5456-0 plate, 13 mm(0.5in.) thick, hot rolled, and annealed abovethe solvus. Rapidcoolingresulted in retention of M92AI3 in solid solution. The light, outlinedparticlesare insoluble(Fe,Mn)Al a; the dark particles are insolubleM92Si. 25% HN0 3 • 500x

(a)

(b)

(c)


5457 Chemical Composition. Composition Limits. 0.08 Si max, 0.10 Fe max, 0.20 Cu max, 0.15 to 0.45 Mn, 0.08 to 1.20 Mg, 0.05 Zn max, 0.05 V max, 0.03 others max (each), 0.10 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Sheet: B 209; UNS. A95457 Available Product Forms. Sheet

Typical Uses. Brightened and anodized trim for autos and appliances. Is readily formed in both annealed and H25 tempers.

For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter


Characteris.tics

Annealing. Treat at 345°C (650 "F); holding at temperature is not required

Major alloying elements: 1.0Mg-0.30Mn. Fine grain size is required in most applications


5457 Aluminum: Microstructures. (a) 5457-F extrusion. A transverse section, photographed with polarized light. Surface grains (top) show random reflection, indicating random crystallographic orientation; interior grains show uniform reflection indicating a high degree of preferred orientation. Barker's reagent. 1OOx. (b) 5457-F plate 6.4-mm (0.25-in.) thick, hot rolled. Fine particles of M92Si precipitated during the rolling. If carried through to final sheet, this amount of precipitate would cause an objectionable milky appearance in a subsequently applied anodic coating. 0.5% HF. 500x. (c)5457-0 plate 1O-mm (O.4-in.) thick, longitudinal section. Annealed at 345°C (650 OF). Polarized light. The grains are equiaxed. Barker's reagent. 100x

(a)

(b)

(c)

5457 Aluminum: Microstructures. (a) Effect of cold rolling on 5457-0 plate, originally 10 mm (0.4 in.) thick, annealed at 345°C (650 OF). Polarized light. 10% reduction. Barker's reagent. 100x. (b) Effect of cold rolling on 5457-0 plate, originally 10 mm (0.4 in.) thick, annealed at 345°C (650 OF). Polarized light. 40% reduction. Barker's reagent. 100x. (c) Effect of cold rolling on 5457-0 plate, originally 10 mm (0.4 in.) thick, annealed at 345°C (650 OF). Polarized light. 80% reduction. Barker's reagent. 100x

(a)

(b)

(c)

198/ Heat Treater's Guide: Nonferrous Alloys 5457 Aluminum: Typical mechanical properties 'Thnslle strength!.)

Yield

strength!.)

Eiongation!.)(b),

Hardnesslc),

'Thmper

MPa

ksI

MP.

ksi

~

HB

MP.

ksi

0 H25 H38.H28

130 180 205

19 26 30

50 160 185

7 23 27

22 12 6

32 48 55

85 110 125

12 16 18

Shearstrength

(a) Strengths andelongations areunchanged or improved at lowertemperatures. (b) 1.6 mm (0.625 in.) thickspecimen. (c) 500 kgload; lOmmdiam ball

5652 Chemical Composition. Composition Limits. 0.40 Si max + Fe, 0.04 Cu max, 0.01 Mn max, 2.20 to 2.80 Mg, 0.15 to 0.35 Cr, 0.10 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al

Typical Uses. Storage vessels for hydrogen peroxide and other chemicals. Available in 0, H32. H34, H36, H38 tempers.

Specifications (U.S.and/or Foreign). ASTM. Sheet and plate: B 209. Extruded seamless tubing: B 241; SAE. J454; UNS. A95652

For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Available Product Forms. Sheet, plate, extruded tubing


Characteristics

required

Major alloying elements: 2.5Mg-0.25Cr


Annealing. Treatment is at 345°C (650 "F); holding at temperature is not

5652 Aluminum: Mechanical properties FIIIigue

'Thmper

'Iypleal properties 0 H32 H34 H36 H38 Property limits 0 H32 H34 H36 H38 H112 (0.250-0.499in. thick) !0.5OO-3.000 in. thick)

MP.

'ThnsIIe strength ksi MP.

195 28 230 33 260 38 275 40 290 42 Minimum 170 215 235 255 270

25 31 34 37 39

195 170

28 25

Yield strength ksl

Maximum 215 260 285 305

31 38 41 44

MP.

ksl

90 13 195 28 215 31 240 35 255 37 Minimum

EJong.Uon!.),

Hardness(b),

~

DB

MP.

ksi

MPa

ksi

25 12 10 8 7 Minimum

47 60 68 73 77

124 138 145 158 265

18 20 21 23 24

110 117 124 131 138

16

65 160 180 200 220

9.5 23 26 29 32

14-18 4-12 3-10 2-4 2-4

110 65

16 9.5

7 12-16

Shearstrength

strength!c)

17

18 19 20

(a) In 50 mm(2 in.) or4d. whered isdiameter ofreducedsectiouof tension-test specimen. Wherearangeofvaluesappears in thiscolumn,thespecified minimumelongation varieswiththickness of the mill product. (b) 500 kgload; 10 mmball.(c)At 5 x 108 cycles;RR Mooretypetest

5657 Chemical Composition. Composition Limits. 0.08 Si max, 0.10 Fe max, 0.10 Cu max, 0.03 Mn max, 0.60 to 1.00 Mg, 0.05 Zn max, 0.03 Ga max, 0.05 V max, 0.02 others max (each), 0.05 others max (total), bal AI

Characteristics Major alloying element: 0.8Mg. Fine grain size is essential for almost all applications

Specifications (U.S. and/or Foreign). ASTM. B 209; UNS. A95657;

Typical Uses. Brightened and anodized auto and appliance trim. Avail-

(Italy) B-AlMgO.9

able in 0, H32, H34, H36, and H38 tempers.

Available Product Forms. Sheet

Wrought Aluminum and Aluminum Alloys /199 For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 OF); holding at temperature is not required Hot Working Temperature. Range is 260 to 510 °C (500 to 950 OF)

5657 Aluminum: Tensile properties MPa

Temper

Typical properlies(b) H25 H28,H38 Properly limits H241(e) H25 H26 H28

Tensilestrength ksi MPa ksi

160 23 195 28 Minimum 125 140 150 170

18 20 22 25


140 165 Maximum 180 195 205

26 28 30

20

24

Elongation(a), %

12 7 Minimum 13 8 7 5

(a) In 50 mm (2 in.) or 4d, where d is diameterofredueed sectionof tension-test specimen. (b) Strengths and elongations are unchanged or increasedat lowtemperatures. (e)Materialin this tempersubjectto somerecrystallization andattendantlossof brightness

5657 Aluminum: Microstructures. (a) 5657-F sheet, cold rolled (85% reduction). Longitudinal section. Polarized light. Grains are greatly elongated and contribute to high strength, but ductility is lower than for specimen annealed at 315°C (600 OF). Barker's reagent. 100x. (b) 5657-F sheet, 85% reduction, stress relieved at 300°C (570 OF) for 1 h. Polarized light. Structure shows onset of recrystallization, which improves formability. Barker's reagent. 1OOx. (c) 5657-F sheet, 85% reduction, annealed at 315°C (600 OF) for 1 h. Polarized light. Recrystallized grains and bands of unrecrystallized grains. Barker's reagent. 100x

(b)

(a)

(c)

5657 Aluminum: Microstructures. (a) 5657 ingot. Dendritic segregation (coring) of titanium. Black spots are etch pits. Anodized coating from Barker's reagent was stripped with 10% H3 P0 4 at 80°C (175 OF). 200x. (b) 5657 sheet. Banding from dendritic segregation (coring) of titanium in the ingot in accompanying figure. Anodized coating from Barker's reagent was stripped with 10% H3 P0 4 at 80°C (175 OF). 200x

(a)

(b)


6005 Chemical Composition. Composition Limits. 0.6 to 0.9 Si, 0.35 Fe max, O.lOCu max, O.lOMn max, 0.40 to 0.60 Mg, 0.10 Cr max, O.lOZn max, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Extrudedrod,bar,shapes, and tubing: B 221; SAE. J451; UNS. A96005 Available Product Forms. Extruded wire, rod, bars, shapes, and tubing

Characteristics Major alloying elements: 0.8Si-0.5Mg Typical Uses. Extruded shapes and tubing for commercial applications requiring greater strength than that of alloy 6063. More common products are ladders and TV antennas. Caveat: Alloy is not recommended for applications requiring resistance to impact loading. Available in T1 and T5 tempers. Alloy is generally brazeable and weldable by all commercial procedures and methods

General Considerations. Material should be quenched from solution treating temperature as rapidly as possible with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature and cooled to keep to temperature below 38°C (lOO "F) during the quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here for solution treatment are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±lO OF) during time at temperature. Note: By suitable control extrusion temperature, product may be quenched directly from the extrusion press to provide specified properties for this temper Precipitation Heat Treating (Artificial Aging). Product is heated to metal temperature of 175°C (345 "F) and held for 8 h to obtain T5 temper. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±lO "F) during time at temperature Annealing. Treatment is at415 °C (775 OF); timeattemperatureis 2 to3 h

Recommended Heat Treating Practice Solution Heat Treating. Extruded rod, bar, shapes, and tubing are treated at a metal temperature of 530°C (985 "F) for a T1 temper.

6009 Chemical Composition. Composition Limits.0.60 to 1.00 Si, 0.50 Fe max, 0.15 to 0.60 Cu, 0.20 to 0.80 Mn, 0.40 to 0.80 Mg, 0.10 Cr max, 0.25 Zn max, 0.10Ti max, 0.05 others max (each), 0.15 others max (total), balAI Specifications (U.S. and/or Foreign). UNS. A96009 Available Product Forms. Sheet

Characteristics Major Alloying Elements. 0.80Si-0.60Mg-0.50Mn-0.35Cu Typical Uses. Auto body sheet Formability Requirements. For sheet in T4 temper, 1t radius required for 90° bending. It for flanging material 0.80 to 1.30 mm (0.032 to 0.050 in.) thick. Only roped hems, "made by bending 180° or 2t interface thickness, can be made in sheet 0.80 to 1.30 mm (0.315 to 0.05 in.) thick. Olsen cup height typically is 9.1 mm (0.36 in.) when tested using 25 mm (1 in.) diam top die at 15 MPa (2200 psi) hold-down pressure and polyethylene film lubricant. Strain hardening exponent (n) typically is 0.22; plastic strain ratio (r) typically is 0.70

maintained at a temperature below 38°C (lOO OF) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±lO "F) of nominal during time at temperature Precipitation Heat Treating (Artificial Aging). Sheet is treated to T6 temper at 205°C (400 OF) for I h. This time at temperature is approximate. Specific times depend on time required for load to reach temperature. Times are based on rapid heating, with soak time measured from time load reaches temperature within 6 °C (lO OF) of applicable temperature. Alternative treatments are available: 4 hat 190°C (375 OF) or 8 h at 175 °C (345 OF) Annealing.Treatment is 415°C (775 OF)

6009 Aluminum: Typical tensile properties of 6009 automobile body sheet

Recommended Heat Treating Practice Solution Heat Treating. Sheet is treated to T4 temper at a metal temperature of 555°C (1030 OF). Alternative treatments: 4 h at 190°C (375 oF) or 8 h at 175°C (345 OF). General Considerations.Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching by total immersion in water, unless otherwise indicated, water should be at room temperature and

Orientation

Thnsile strength ksl MPH

Yieldstrength ksl

MPH

EJongHIIon, %

T4temper Longitudinal Transverse and 45°

234 228

34 33

131 124

19 18

24 25

345 338

50 49

324 296

47 43

13

T6temper longitudinal Transverse and 45·

12


6010 Chemical Composition. Composition Limits. 0.80 to 1.20 Si, 0.50 Fe max, 0.15 to 0.60 Cu, 0.20 to 0.80 Mn, 0.60 to 1.00 Mg, 0.10 Cr max, 0.25 Zn max, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), balAl Specifications (U.S. and/or Foreign). UNS. A96010 Available Product Forms. Auto body sheet

removal from furnace. When quenching by total immersion in water, unless otherwise indicated, water should be at room temperature and maintained at a temperature below 38°C (100 oF) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here are nominal and should be maintained within ±6 °C (±1OOF) of nominal during time at temperature

Precipitation Heat Treating (Artificial Aging). Sheet is treated to T6 temper at 205°C (400 OF) for I h. This time at temperature is approximate. Specific types depend on time required for load to reach temperature. Times are based on rapid heating, with soak time measured from time load reaches temperature within 6 °C (10 "F) of applicable temperature.

Characteristics Major alloying elements: 1.00Si-0.80Mg-0.5Mn-0.35Cu

Typical Uses. Auto body sheet Formability Requirements. For sheet in T4 temper, It radius required to 90° bending, It for flanging material 0.80 to 1.30 Mn (0.032 to 0.050 in.) thick. Only roped seams, made by bending 180° or 2t interface thickness, can be made in sheet 0.80 to 1.30 mm (0.315 to 0.05 in.) thick. Olsen cup height typically is 9.1 m min (0.36 in.) when tested using 25 mm (1 in.) diam top die at 15 MPa (2200 psi) hold-down pressure and polyethylene film lubricant. Strain hardening exponent (n) typically is 0.22; Plastic strain ratio (r) typically is 0.70

Recommended Heat Treating Practice Solution Heat Treating. Sheet is treated to T4 temper at metal temperature of 565°C (1050 oF) General Considerations. Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after

Alternative treatments are available: 4 h at 190°C (375 "F), or 8 h at 175 °C (345 oF)

6010 Aluminum: Typical tensile properties of 6010 automobile body sheet 'IOnsIIe otrength lis; MPa

Orientallon

T4temper Longitudinal Transverse and45° T6temper Longitudinal Transverse and45°

YIdd strength lis;

MPa

EIougalion, II

296 290

43 42

186 112

21 25

23 24

386 319

56 55

312 352

54 51

12

11

6010 Aluminum: Time-temperature property diagram. Effectof aging time and temperature on longitudinalyield strength of 6010-T4 500~-----..--------r----------,

6010-14

234 MPa (34 ksl) 262 MPa (38 ksi) 290 MPa (42 ksl) 317 MPa (46 ksi)

250 225 u

331 MPa (48 ksl) 175 338 MPa (49 ksl) 345 MPa (50 ksi) 200 338 MPa (49 ksl) 300 207 MPa (30 ksi)+--~.---_~~~~=t'-oII~ 331 MPa (48 ksi) 150 234 MPa (34 ksi) 317 MPa (46 ksl) 290 MPa (42 ksi) 262 _ MPa (38 ksi)_ _....L.250 '----'-_ --= 125 10 1 102 ~

_

0

...e~

:::J

Q)

a. E

~

~

Time,h

6061, Alclad 6061 Chemical Composition. Composition Limits (6061). 0.40 to 0.80 Si, 0.70 Fe max, 0.15 to 0.40 Cu, 0.15 Mn max, 0.80 to 1.20 Mg, 0.04 to 0.35 Cr, 0.25 Zn max, 0.15 Ti max, 0.05 others max (each), 0.15 others max (total), bal AI

Composition Limits (Alclad 6061). 7072 cladding-O.70 Si max + Fe, 0.10 Cu max, 0.10 Mn max, 0.10 Mg, max, 0.80 to 1.30 Zn, 0.05 others max (each), 0.15 others max (total), bal Al

2021 Heat Treater's Guide: Nonferrous Alloys Specifications (U.S. and/or Foreign). AMS. (See adjoining Table); ASTM. (See adjoining Table); UNS. A96061; Government. (See adjoining Table); (Canada) CSA GSI1N; (France) NF A-GSUC; (United Kingdom) BS H20. ISO: AIMgSiCu

Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here are nominal, and should be attained as rapidly as possible and maintained within ±6 °C (±100F) of nominal during time at temperature

Available Product Forms. Sheet; plate; rolled or cold-finished wire, rod, and bar; extruded rod, bar, shapes, and tubing; structural shapes; pipe; drawn pipe; die and hand forgings; rolled rings

Precipitation Heat Treating (Artificial Aging). The following products (sheet; plate; rolled or cold finished wire, rod, and bar; and drawn tubing) are heated to a metal temperature of 160°C (320 oF) and held for 18 h.

Characteristics Major alloying elements: 1.0Mg-0.6Si-0.30Cu-0.2OCr

Typical Uses. Provides combination of strength, weldability, and corrosion resistance needed for structural applications; trucks, towers, canoes, railroad cars, furniture, pipelines. Tempers include T4, T451, T451O, T4511, T6, T651, T652, T651 1. For more information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter

The following products (extruded rod, bar, shapes, and tubing; die and hand forgings; and rolled rings) are heated to a metal temperature of 175 °C (345 OF) and held for 8 h

Special considerations: 8

8

8

Recommended Heat Treating Practice 8

Solution Heat Treating. All products are treated to T4, T42, T45, T45l, T451O, and T4511 tempers at 530°C (985 OF). Special considerations: 8 8 8

8

Only tread plate is treated to T4 temper at 530°C (985 OF) Plate, rolled or cold finished rod, bar, shapes and tubing in T451 temper; extruded rod, bar, shapes, and tubing in T4510 and T4511 tempers are all stress relieved by stretching to produce specified amount of set prior to precipitation heat treatment Rolled rings in T452 temper are stress relieved by 1 to 5% cold reduction subsequent to solution heat treatment and prior to precipitation heat treatment

General Information. Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching by total immersion in water, unless otherwise indicated, water should be at room temperature and maintained at a temperature below 38°C (100 "F) during quenching cycle.

8

Only tread plate is treated at 160°C (320 "F) and held at temperature for 18 h to obtain T6 temper Plate and rolled or cold finished wire, rod, and bar are treated at 160°C (320 OF) and held at temperature for 18 h to obtain T651 temper Extruded rod, bar, shapes, and tubing are treated at 175°C (345 OF) and held at temperature for 8 h Rolled or cold finished wire, rod, and bar are treated at 160°C (320 OF) and held at temperature of 18 h to obtain T89 temper. Cold working after solution treating is necessary to get desired properties in precipitation treating Rolled or cold finished wire, rod, and bar are treated at 160°C (320 OF) and held at temperature for 18 h to obtain T93, T94, and T913 tempers Rolled rings are treated at 175°C (345 OF) and held at temperature 8 h to obtain T652 temper. Parts are stress relieved by 1 to 5% cold reduction subsequent to solution treating and prior to precipitation treating

Alternative treatment for rolled or cold finished wire, rod, and bar in T6, T62, T89, T93, T94, T651, T913 tempers; and drawn tubing in T6 and T62 tempers: 8 h at 170°C (340 OF) versus standard 18 h at 160°C (320 OF)

General Information. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±10 "F) of nominal during time at temperature annealing. See Table titled "Typical Annealing Treatments for Aluminum Alloy Mill Products" in introduction titled "Heat Treating Aluminum Alloys"

6061 Aluminum: Microstructures. (a) 6061-F plate, 38 mm (1.5 in.) thick, as hot rolled (71% reduction).' Longitudinal section from center of plate thickness. Particles are Fe3SiAI,2 (gray, scriptlike) and M92Si (black). 0.5% HF.250x. (b) 6061-F plate, 38 mm (1.5 in.) thick, as hot rolled (91% reduction). Longitudinal section from near plate surface. HF. 250x. (c) 6061-F 6.4-mm (0.25-in.) sheet, hot rolled (reduced 98%); midthickness longitudinal section. Most M92Si will dissolve during solution treating. 0.5% HF.250x

...

-

.

-(a)

(b)

(c)

.'


6061 Aluminum. Effect of quenching medium on strength of 6061-T6 sheet. Water-immersion quench equals 100%. Control of coolant flow will minimize decrease in mechanical properties

Mill form and condition

Bar 6061 Sheetand plate


Thickness, 0.001 in.

150

100

100

Standard specifications

-.............. t---

r-. '\

200

250

II V Water ~

-,

-,

60

Treadplate Wire.rod.andbar (rolledorcoldftnished)

spray

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-,

Structuralshapes Thbe(drawn) Thbe(seamless)

2500

3150

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QQ-A-2501ll

B632 B211

MIL-F-17132

B221

QQ-A-200/8

B808 B241 B483 B210

QQ-A-200/8

4115 4116 4117 4128 4129 4150 4160 4161 4172 4173 4113

Tube(condenser) Tube(condenser withintegralftns) Thbe(welded)

250

II

Pipe Pipe(gasandoil transmission) Forgings Forgingstock

~irblast

10

Rivet wire Impacts Structural pipeandtube(extruded) Aiclad6061 Sheetandplate

;j1

6061·Tt sheet

60 1250

2500

3150

5000

6250

1500

Th ickness, JIm

QQ-A-22518

WW-T-700/6

MIL-T-7081 B234 B404 B313 B549

Tube(waveguide)

t\.

80

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Tube(hydraulic)

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90

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150

B209

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1500

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6250

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Thickness, 0.001 in. 100

100

5000

Thickness,

LIVE GRAPH

4025 4026 4027 4043 4053

4079 4080 4082 4081 4083

50 1250

ASTM

Tube(extruded. seamless)

6061.Tt sheet

Specification No. Government

AMS

4127 4127 4146

B241 B345 B247

B316 B429 4020 4021 4022 4023

MIL-W-85 MIL-W-23068 MIL-W-23351 MIL-P-25995 QQ-A-367.MIL-A-22771 QQ-A-367 QQ-A-430 MIL-A-12545 MIL-P-25995

B209

6061 Aluminum: Time-temperature-property diagram. Curves at 95% of maximum tensile stress for various alloys. A = 7075; B = 2017; C = 6061; D =6063

600


500

-:.-:-,:,,--==.~.

400

A

U

0.300

I-

200 100 0

1

100

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t,s

1000


6061 Aluminum. Aging characteristics of 6061 sheet

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6061 Aluminum. Aging characteristics of aluminum sheet alloys at room temperature, at 0 °C (32 OF), and at -18°C (0 OF)


6061

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I yea,

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10

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6061 Aluminum: Typical tensile properties of 6061-T6 or T651 at various temperatures

0

iii 0 0

0.01

0.1

10

104

100

Duration of precipitation heat treatment, h



105

'Thmperalure of "C

-196 -80 -28 24 100 150 205 260 315 370

-320 -112 -18 75 212 300 400 500 600 700

'ThnsUestrength(a) MPa ksi

414 338 324 310 290 234 131 51 32 24

60 49 47 45 42 34 19 7.5 4.6 3

rleld strength (0.2% oll"set)(a) ksl MPa

324 290 283 276 262 214 103 34 19 12

47 42 41

40 38 31 15 5 2.7 1.8

Elongation, %

22 18 17 17 18 20 28 60 85 95

(a) Lowest strength for exposures up 10 10 000 h at temperature, no load; testloading applied at 35 MPalmin (5 ksilmin) to yield strength and then at strain rate of 5%/min to fracture

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6061 Aluminum: Time-temperature property diagrams. Composition: AI-0.55% Mg-0.6B% Si-0.01% Cr-0.014% Mn-O.ll% Fe-0.036% Cu-O.Ol% li0.002% B. Treatment: Solution heat-treated at 550°C (1020 OF) for 1 to 1.5 h, down quenched to various temperatures into molten salt, held at temperature for varying times, water quenched, and aged. Maximum quenched and aged yield strength 3B.4 ksl (264 MPa) Iso-yield curve is 90% of quenched and aged yield strength

1 411'

90% ofT6 YS

100 141

6'

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24 48 96 192 400

Solution treatment time, h

206.0, A206.0 (4.5Cu-O.30Mn-O.25Mg-O.22Ti) Specifications U.S. and/or Foreign. AMS. 4235,4236,4237 Chemical Composition. Composition Limits. 4.2 to 5.0 Cu, 0.15 to 0.35 Mg, 0.20 to 0.50 Mn, 0.10 Si max, 0.15 Fe max, 0.10 Zn max, 0.15 to 0.30 Ti, 0.05 Ni max, 0.05 Sn max, 0.05 others (each) max, 0.15 others (total) max, bal AI. A206.0: 4.2 to 5.0 Cu, 0.15 to 0.35 Mg, 0.20 to 0.50 Mn, 0.05 Si max, 0.10 Fe max, 0.10 Zn max, 0.15 to 0.30Ti, 0.05 Ni max, 0.05 Sn max, 0.05 others (each) max, 0.15 others (total) max, bal Al

Applications Typical Uses. Structural castings in heat-treated temper for automotive, aerospace, and other applications where high tensile and yield strength and moderate elongation are needed. Gear housings, truck spring hanger castings, and other applications where high fracture toughness is required. Cylinder heads for gasoline and diesel motors, turbine and supercharger impellers, other applications where high strength at elevated temperatures and special aging treatment are required Precautions in Use. Subject to corrosion problems due to copper content of alloy. T4 and TI heat treatments qualify and meet federal test

requirements for stress-corrosion cracking. T6 temper should not be used where stress-corrosion cracking could be a problem

Mechanical Properties Tensile Properties. Separately cast test bars. Tensile strength and yield strength, see Table and Figure. Elongation in 50 mm or 2 in. (typical for A206.0-TI): 11.7% at room temperature, 14.0% at 120°C (250 oF), 17.7% at 175°C (350 OF). Reduction in area (typical for A206.0-TI): 26.0% at room temperature, 40.4% at 120°C (250 OF), 53.7% at 175°C (350 OF) Hardness. T4 temper, 118 HV; TI temper, 137 HV

Chemical Properties General Corrosion Behavior. Comparable to other wrought or cast aluminum alloys containing equivalent amounts of copper

Fabrication Characteristics Weldability. Fair repair welding characteristics

Aluminum Casting Alloys /247

Recommended Heat Treating Practice • T7 temper, 200°C (390 "F), hold at temperature for 8 h • T6 temper, 155°C (310 "F), hold at temperature for 8 h • T4 temper, room temperature

Solution Temperature. See Table Aging Temperature. See Table, or use the following:

A206.0-T7: Effect of temperature on strength. (a) Tensile properties. (b) Shear strength. (c) Compressive properties. (d) Bearing strengths. (e) Unnotched fatigue limits. (f) Notched fatigue limits.

LIVE GRAPH

LIVE GRAPH 100

50

500

150

Temperature, OF 200 250


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70

60 ._

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50

75

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175

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300

350

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\390.0,sand castings 26 F.T5 180 T6 40 275 T7 36 250 A390.0, permanent mold castings F,T5 29 200 45 T6 310 T7 260 38 390.0, conventional die castings 40.5 F 280 T5 43 295 390.0, Acurad castings F 30 205 T5 205 30 T6 53 365 40 T7 275

Hardness(a)(c), HB

180 275 250

26 40 36

100 140 115

200 310 260

29 45 38

110 145 120

240 260

35 38

195 200 365 275

28 29 53 40

Fatigue strength(d) MPa ksi

105

15

115 100

17 14.5

120 125

140

20

110 110 150 125

90 95

13 14 17 16

115

110

(a)Tensilepropertiesand hardnessaredetennined from standardcast-to-sizetensilespecimens 12.7 mm(0.5in.)diameterforsand,pennanentmold,andAcuradcastingsand6.4rrun(0.25 in.)diameter for die castings and tested without machining the surface. (b) 0.2% offset. For 390.0 and A39O.0 castings,yield strength normallyequals tensilestrength because0.2% offsetis not reachedprior to fracture.(c) 500 kg load; 10mm ball. (d)At 5 x 108 cycles;R.R.Moore type test

413.0, A413.0 (12Si) Commercial Names. Fonner designation. 413.0: 13. A413.0: A13 Specifications U.S.and/or Foreign. Fonner ASTM. 413.0: S12B. B85 SI2A; SAE. A413.0: J453, 305; UNS number. 413.0: A04130. A413.0: A14130; Government. A413.0: QQ-A-591 (class 2); Foreign. Canada: A413.0, CSA SI2P; France: NF A-S13. ISO: AlSi12

Chemical Composition. Composition Limits. 413.0: 1.0 Cu max, 0.10 Mg max, 0.35 Mn max, 11.0 to 13.0 Si, 2.0 Fe max, 0.50 Ni max, 0.50 Zn max, 0.15 Sn max, 0.25 others (total) max, bal AI. A413.0: 1.0 Cu max, 0.10 Mg max, 0.35 Mn max, 11.0 to 13.0 Si, 1.3 Fe max, 0.50 Ni max, 0.50 Zn max, 0.15 Sn max, 0.25 others (total) max, bal AI

Consequence of Exceeding Impurity Limits. Content of impurities may be quite high before serious effects are detected. Increasing copper lowers corrosion resistance; increasing iron and magnesium lowers ductility; increasing silicon content may lead to machining problems

Applications Typical Uses. Miscellaneous thin-walled and intricately designed castings. Other applications where excellent castability, resistance to corrosion, and pressure tightness are required

Mechanical Properties Tensile Properties. Typical for separately cast test bars, as-cast. 413.0: tensile strength, 300 MPa (43 ksi); yield strength, 145 MPa (21 ksi); elongation, 2.5% in 50 mrn or 2 in. A413.0: tensile strength, 290 MPa (42

ksi); yield strength, 130 MPa (19 ksi); elongation, 3.5% in 50 mrn or 2 in. See Table

Fabrication Characteristics Joining. Rivet compositions: 6053-T4, 6053-T6, 6053-T61. Soft solder: After copper plating, then use methods applicable to copper-base alloys. Resistance welding: flash method

Alloy413.0-F: Typicaltensile properties for separately cast test bars at elevated temperature Temperature OF

-c

-195 ~O

-28 24 100 150 205 260 315 370

-320 -112 -18 75 212 300 400 500 600 700

Tensile strength MPa ksi 360 310 303 295 255 220 165 90 50 30

(a)0.2% offset. (b) In 50mmor2 in.

52 45 44 43 37 32 24 13 7 4.5

Yield strength(a) ksi MPa 160 145 145 145 140 130 105 60 30 15

23 21 21 21 20

19 15 9 4.5 2.5

Eiongation(h). %

1.5 2 2 2.5 5 8 15 30 35 40


443.0, A443.0, 8443.0, C443.0 (5.2Si) Commercial Names. Fonner designation. 43

Fabrication Characteristics

Specifications U.S.and/or Foreign. Fonner ASTM.443.0:S5B. B443.0: S5A. C443.0: S5C; SAE. C443.0: 304; UNS number. 443.0: A04430. A443.0: Al4430. B443.0: A24430. C443.0: A34430; Government. B443.0: QQ-A-601 (class 2). C443.0: QQ-A-591; Foreign. Canada: CSA S5

Joining. Rivet compositions: 6053-T4, 6053-T6, 6053-T61. Soft solder with copper plate and use methods applicable to copper-base alloys for die castings. Use Alcoa No. 802, no flux or rub-tin with Alcoa No. 802 for sand and permanent mold castings. Sand and pennanent mold casting alloys (unless otherwise noted): braze with Alcoa No. 717; Alcoa No. 33 flux; flame either reducing oxyacetylene or reducing oxyhydrogen. Atomic-hydrogen weld with 4043 alloy; Alcoa No. 22 flux. Oxyacetylene weld with 4043 alloy; Alcoa No. 22 flux; neutral flame. Metal-arc weld with 4043 alloy; Alcoa No. 27 flux. Carbon-arc weld with 4043 alloy; Alcoa No. 24 flux (automatic), Alcoa No. 27 flux (manual). Tungsten-arc argon-atmosphere weld 4043 alloy; no flux. Resistance weld: flash method for die cast alloys; spot, seam, and flash methods for sand and pennanent mold cast alloys

Chemical Composition. Composition Limits. 443.0: 0.6 Cu max, 0.05 Mg max. 0.50 Mn max, 4.5 to 6.0 Si, 0.8 Fe max, 0.25 Cr max, 0.50 Zn max, 0.25 Ti max, 0.35 others (total) max, bal AI. A443.0: 0.30 Cu max, 0.05 Mg max, 0.50 Mn max, 4.5 to 6.0 Si, 0.8 Fe max, 0.25 Cr max, 0.50 Zn max. 0.25 Ti max, 0.35 others (total) max, bal AI. B443.0: 0.15 Cu max, 0.05 Mg max. 0.35 Mn max, 4.5 to 6.0 Si, 0.8 Fe max, 0.35 Zn max, 0.25 Ti max, 0.25 others (total) max, bal AI. C443.0: 0.6 Cu max, 0.10 Mg max, 0.35 Mn max, 4.5 to 6.0 si, 2.0 Fe max, 0.50 Ni max, 0.50 Zn max, 0.15 Sn max. 0.25 others (total) max, bal Al Consequence of Exceeding Impurity Limits. For die cast alloy, relatively large quantities of impurities may be present before serious effects are detected. Increasing copper tends to lower resistance to corrosion; increasing iron and magnesium tends to lower ductility. For sand and permanent mold cast alloys, high copper. iron, or nickel decreases ductility and resistance to corrosion. Increasing magnesium reduces ductility

Applications Typical Uses. Cooking utensils, food-handling equipment, marine fittings, miscellaneous thin-section castings. Die castings: applications where good pressure tightness, above-average ductility, and excellent resistance to corrosion are required. Sand and permanent mold castings: applications where very good castability and resistance to corrosion with moderate strength are required

Mechanical Properties Tensile Properties. See Table Hardness. F temper: 443.0 (sand castings): 40 HB. B443.0 (permanent mold castings): 45 HB. C443.0 (die castings): 65 HB (500 kg load, 10 rom ball)

Alloy 443.0, 443.0-F, 8443.0-F, C443.0-F: Typical tensile properties for separately cast test bars Temperature OF OC

'IensUestrengtb MP. ksl

443.0-F sand castings 24 130 75 B443.0-F permanent mold castings 24 160 75 C443.0-F die castings 24 230 75 100 195 212 150 150 300 205 400 110 260 500 60 315 600 35 370 700 25

Yieldstrengtb!.) MP. ksi

Elong8lion(b), 'I

19

55

8

8

23

60

9

10

33 28 22 16 9 5 3.5

110 110 105 85 40 25 15

16 16 15 12 6 3.5 2.5

9 9 10 25 30 35 35

(a) 0.2% offset. (b)In50mmor2in.

514.0 (4Mg) Commercial Names. Fonner designation. 214

Applications

Specifications U.S. and/or Foreign. Fonner ASTM. G4A; SAE. 320; UNS number. A05140; Government. QQ-A-60l (class 5); Foreign. Canada: CSA G4. United Kingdom: DID 165. ISO: AIMg3

Typical Uses. Dairy and food-handling applications. cooking utensils. fittings for chemical and sewage use. Other applications where excellent resistance to corrosion and tarnish are required

Chemical Composition. Composition Limits. 0.15 Cu max, 3.5 to 4.5 Mg, 0.35 Mn max, 0.35 Si max, 0.50 Fe max. 0.15 Zn max, 0.25 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal Al

Mechanical Properties

Consequence of EXceeding Impurity Limits. High copper or nickel greatly decreases resistance to corrosion and decreases ductility. High iron, silicon, or manganese decreases strength and ductility. Tin reduces resistance to corrosion

Tensile Properties. Typical, F temper. Tensile strength, 145 MPa (21 ksi); yield strength, 95 MPa (14 ksi); elongation, 3.0%. See Table Hardness. 50 HB (500 kg load, 10 rom ball)

Fabrication Characteristics Joining. Rivet compositions: 6053-T4. 6053-T6, 6053-T61. Soft solder with Alcoa No. 802; no flux. Rub-tin with Alcoa No. 802. Braze with Alcoa

Aluminum Casting Alloys /265 No. 717; Alcoa No. 33 flux; flame either reducing oxyacetylene or reducing oxyhydrogen. Atomic-hydrogen weld with 4043 alloy; Alcoa No. 22 flux. Oxyacetylene weld with 4043 alloy; Alcoa No. 22 flux; flame neutral. Metal-arc weld with 4043 alloy; Alcoa No. 27 flux. Carbon-arc weld with 4043 alloy; Alcoa No. 24 flux (automatic), Alcoa 27 flux (manual). Tungsten-arc argon-atmosphere weld with 4043; no flux. Resistance welding: spot, seam, and flash welds

Alloy 514.0-F: Typical tensile properties for separately cast test bars 'Thmperature OF

°C

24 150 205 260 315

75 300 400 500 600

'Thnsile strength lis; MP.

170 150 125 90 60

25 22 18 13 9

YieldS\ftngth(.) MP. ksi

85 85 85 55 30

12 12 12 8 4

Elongation, II>

9 7 9 12 17

(a) 0.2% offset

518.0 (8Mg) Commercial Names. Former designation. 218 Specifications U.S. and/or Foreign. Former AS'IM. G8A; UNS number. A05180; Government.QQ-A-591 Chemical Composition. Composition Limits. 0.25 Cu max, 7.5 to 8.5 Mg, 0.35 Mnmax, 0.35 Si max, 1.8Femax,0.15Nimax, 0.15 Zn max, 0.15 Sn max, 0.25 others (total) max, bal Al

Applications Typical Uses. Alloy has excellent corrosion resistance and machinability; high ductility; poor castability (is hot short). Takes a high polish;

difficult to attain a uniform appearance after anodizing. Non-heat treatable. Poor weldability and brazeability. Used for die cast marine fittings, ornamental hardware, ornamental automotive parts, and other applications requiring the highest corrosion resistance

Mechanical Properties Tensile Properties. Typical, F temper. Tensile strength, 310 MPa (45 ksi); yield strength, 190 MPa (28 ksi); elongation, 5 to 8% in 50 rnm or 2 in. Hardness. 80 HB (500 kg, 10 rnm load)

520.0 (10Mg) Commercial Names. Former designation. 220 Specifications U.S. and/or Foreign. AMS. 4240; Former AS'IM. GIOA; SAE. 324; UNS number. A05200; Government. QQ-A-60l (class 16); Foreign. Canada: CSAGIO. France: NF A-GIO. ISO: AIMglO Chemical Composition. Composition Limits. 0.25 Cu max, 9.5 to 10.6 Mg, 0.15 Mn max, 0.25 Si max, 0.30 Fe max, 0.15 Zn max, 0.25 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal Al

Hardness. 75 HB (500 kg load, 10 rnm ball)

Fabrication Characteristics Joining. Rivet compositions: 6053-T4, 6053-T6, 6053-T61. Soft solder with Alcoa No. 802; no flux. Rub-tin with Alcoa No. 802. Resistance welding: spot, seam, and flash methods

Consequence of Exceeding Impurity Limits. High copper or nickel greatly decreases resistance to corrosion. High iron, silicon, or manganese contents adversely affect mechanical properties

Applications Typical Uses. Aircraft fittings, railroad passenger-car frames, miscellaneous castings requiring strength and shock resistance. Other applications where excellent machinability and resistance to corrosion with highest strength and elongation of any aluminum sand casting alloy are desired

Mechanical Properties Tensile Properties. Typical. T4 temper: tensile strength, 330 MPa (48 ksi); yield strength, 180 MPa (26 ksi); elongation in 50 mm or 2 in., 16%. See Table

Alloy 520.0-F: Typical tensile properties for separately cast test bars at elevated temperature 'Thmperalure OF -c

24 150 205 260 315

75 300 400 500 600

(a) In 50mmor2 in.

'IImsIJe strenglh MP. ksl

315 240 150 105 70

46 35 22 15 10.5

0.211> yleldstrength ksI MPa

170 130 80 50 25

25 19

11.5 7.5 3.5

EIongatlon(.), II>

14 16 40 55 70


535.0, A535.0, B535.0 (7Mg) Commercial Names. Former designations. 535.0: Almag35. A535.0: A218. B535.0: B218

Specifications U.S.and/or Foreign. Fonner AMS. 4238A, 4239; Former ASTM. 535.0: GM70B; UNS number. 535.0: A05350. A535.0: A15350. B535.0: A25350; Government. 535.0: QQ-A-601, QQ-A-371 Chemical Composition. Composition Limits. 535.0: 0.05 Cu max, 6.2 to 7.5 Mg, 0.10 to 0.25 Mn, 0.15 Si max, 0.15 Fe max, 0.10 to 0.25 Ti, 0.003 to 0.007 Be, 0.002 B max, bal AI. A535.0: 0.10 Cu max, 6.5 to 7.5 Mg, 0.10 to 0.25 Mn, 0.20 Si max, 0.20 Fe max, 0.25 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal AI. B535.0: 0.10 Cu max, 6.5 to 7.5 Mg, 0.05 Mn max, 0.15 Si max, 0.15 Fe max, 0.10 to 0.25 Ti, 0.05 others (each) max, 0.15 others (total) max, bal Al

Applications Typical Uses. Maximum properties are available immediately after casting without the aid of heat treatment or natural aging. Used in parts in computing devices, aircraft and missile guidance systems, and electric equipment where dimensional stability is essential. Highly useful in marine and other corrosive-prone applications

speeds. 535.0 takes a very high mirror polish. Normally this alloy is used for sand and permanent mold castings, but it can also be used for die castings. Where high dimensional tolerance is required, the following procedure should be used: rough machine parts; heat at 200°C (400 "F) for 14 h; cycle between -73 to 100 °C (100 to 212 "F) five times (30 h/cycle); finish machine; heat 10 h at 200°C (400 OF); cycle between -73 to 100°C (-100 to 212 "F) 25 times (30 h/cycle). 535.0 may be stress relieved at approximately 370°C (700 OF) for 5 h; air cool. Creep resistance at 370°C (700 OF) is very low, permitting plastic flow under the load of locked-up stresses and resulting in stress-free castings. On air cooling from 370 °C (700 OF), 535.0 will have full hard and physical properties and will be stable. After being stress relieved, most castings from 535.0, A535.0, and B535.0 can be rough and finish machined without breaking into the machining sequence

Weldability. Can be welded by any inert gas shielded-arc systems using filler material of 5356 or 535.0 aluminum. Welding fluxes should be avoided if possible. Because of the beryllium content in alloy 535.0, care should be taken not to inhale fumes during welding Anodizing. Use sulfuric acid process to produce a pure satin white finish capable of being dyed to brilliant pastel colors

Mechanical Properties Tensile Properties. F and T5 tempers: 535.0: Tensile strength: typical, 275 MPa (40 ksi); minimum, 240 MPa (35 ksi). Yield strength: typical, 140 MPa (20 ksi); minimum, 125 MPa (18 ksi). Elongation in 50 mm or 2 in.: typical, 13%; minimum, 8.0%. See Table

Hardness. Typical: 60 HB. Minimum: 70 HB

Chemical Properties General Corrosion Behavior. 535.0 has the highest resistance to corrosion of any of the common aluminum casting alloys

Fabrication Characteristics Machinability. Superior, can be milled at speeds four times faster than other aluminum casting alloys. High microfinishes can be achieved at high

Alloy 535.0-F: Typical tensile properties for separately cast test bars at elevated temperature Thmpernlure OF °C

150 175 205 260 315 370

300 350 400 500 600 700

Thmile strength list MPa

260 235 220 180 140 105

37.5 34 32 26.5 20.5 15.5

EIoogation(a),

"

11 14 14

13 13 12

(a) In 50 nun or 2 in.

712.0 (5.8Zn-O.6Mg-O.5Cr-O.2Ti) Commercial Names. Former designations. D712.0, D612, 40E Specifications U.S. and/or Foreign. Fonner ASTM. ZG61A; SAE. 310; UNS number. A47120; Government. QQ-A-601 (class 17)

Applications Typical Uses. Applications where a good combination of mechanical

Chemical Composition. Composition Limits. 0.25 Cu max, 0.50 to

properties is required without heat treatment: shock and corrosion resistance, machinability, dimensional stability, no distortion in heat treating

0.65 Mg, 0.10 Mn max, 0.30 Si max, 0.50 Fe max, 0.40 to 0.6 Cr, 5.0 to 6.5 Zn, 0.15 to 0.25 Ti, 0.05 others (each) max, 0.20 others (total) max, bal Al

Mechanical Properties Tensile Properties. F or T5 temper. Typical tensile strength, 240 MPa (35 ksi); yield strength, 170 MPa (25 ksi); elongation, 5%. Low-temperature strength after 24 h at -70°C (-94 oF): tensile strength, 265 MPa (38.4 ksi); elongation in 50 mm or 2 in., 5%. See Table

Aluminum Casting Alloys /267 Hardness. 70 HB (500 kg load, 10 mm ball)

Recommended Heat Treating Practice Aging Temperature. T5 temper: room temperature for 21 days or at 157 °C (315 "F) for 6 to 8 h

Alloy 712.0-F: Typical tensile properties for separately cast test bars at elevated temperature Thmperature 0C

OF

79 120 175

175 250 350

'Thnsile strength MPa ksi

235 205 135

0.2 % yleldstrength MPa ksi

34 29.5 19.5

210 175 115

30.5 25 17

E1ongation(a), %

3 2 6

(a)In50mmor2in.

713.0 (7.5Zn-O.7Cu-O.35Mg) Commercial Names. Former designation. 613, Tenzaloy Specifications U.S. and/or Foreign. Former ASTM. Sand castings, B26 ZC81A. Permanent mold castings, B108 ZC8lB; Former SAE. 315; UNS number. A07130; Government. Sand castings, QQ-A-601 (class 22). Permanent mold castings: QQ-A-596 (class 12) Chemical Composition. Composition Limits. 0.40 to 1.0 Cu, 0.20 to 0.50 Mg, 0.6 Mn max, 0.25 Si max, 1.1 Fe max, 0.35 Cr max, 0.15 Ni max, 7.0 to 8.0 Zn, 0.25 Ti max, 0.10 others (each) max, 0.25 others (total) max, balAI

Applications Typical Uses. Cast aluminum furniture and other very large casting applications that require high strength without heat treatment. 713.0 ages at room temperature to produce mechanical properties equivalent to those of common heat-treated aluminum cast alloys. These properties develop in 10 to 14 days at room temperature or in 12 h at 120°C (250 "F)

Mechanical Properties Tensile Properties. Typical for T5 temper, aged at room temperature for 21 days or artificially aged at 120 ± 5.5 °C (250 ± 10 OF) for 16 h. Sand casting: tensile strength, 205 MPa (30 ksi); yield strength: ISO MPa (22 ksi); elongation, 4.0% in 50 mm or 2 in. Permanent mold casting: tensile

strength, 220 MPa (32 ksi); yield strength: ISO MPa (22 ksi); elongation, 3.0% in 50 mm or 2 in.

Chemical Properties General Corrosion Behavior. Good resistance to corrosion, equivalent to aluminum-silicon alloys. A typical corrosion test showed no loss in mechanical properties after immersion for 90 days in aerated 3% salt-water solution. Not subject to acceleration of corrosion by stress or to stress-corrosion cracking as determined by the standard test of exposure for 14 days to the corrosive medium while under a continuous load of 75% of yield strength

Fabrication Characteristics Machinability. Good machinability and polishing characteristics. Very good dimensional stability. Fully aged material shows a decrease in length of less than 0.1 min/in. of length. If713.0 is given a stress-relief treatment of 6 h at 450°C (850 "F) and air cooled, it ages naturally. The resulting product is a stress-free, full-strength casting. This is not possible with any heat-treatable aluminum alloy Weldability. For high-strength welds, shielded-arc methods can be used with filler alloys 5154 and 5356 Brazeability. Readily brazed at 540 to 595°C (1000 to 1100 "P) using any of the common brazing methods

771.0 (7ln-O.9Mg-O.13Cr) Commercial Names. Former designation. Precedent 71A


Specifications U.S. and/or Foreign. Former ASTM. 771.0: ZG71B; UNS number. A07710; Government. 771.0: QQ-A-60lE

Tensile Properties. See Table

Chemical Composition. Composition Limits. 0.10 Cu max, 0.8 to 1.0 Mg, 0.10 Mn max, 0.15 Si max, 0.15 Fe max, 0.06 to 0.20 Cr, 6.5 to 7.5 Zn, 0.10 to 0.20 Ti, 0.05 others (each) max, 0.15 others (total), bal Al

Applications Typical Uses. Applications where dimension stability is important. Polishes to a high luster; anodizes with good clean appearance. Good corrosion resistance

Fabrication Characteristics Machinability. 771.0-T5 has good stability and machinability. It can be milled five times faster and hole worked at twice the speed of alloys such as 356.0 and 319.0. It can be finished machined in one clamping operation to flatness tolerance of 0.001 in. This reduces total cost of machining over most casting alloys, which require two clamping operations to obtain this type of flatness tolerance Weldability. Can be welded by either gas tungsten-arc or gas metal-arc welding using 5356 rod or wire. Special procedure should be followed in welding to ensure good results.

268/ Heat Treater's Guide: Nonferrous Alloys If parts are to be welded, the operation should be made part of the heat-treating cycle. If welding is to be done on T6 or 17 I parts, the castings are heated to 580°C (1080 "F), removed from the heat-treating furnace, and welded while hot. The parts are then returned to the furnace and the T6 and 171 heat treatments continued. If the parts are to be used in the T52 or T2 temper, they are heated to 415°C (775 OF), taken from the furnace, welded hot, then returned to the furnace and the heat treatment continued. Items to be used in the T51 temper are heated to 205°C (405 "F), taken from the furnace, welded hot, then returned to the furnace and T51 treatment continued. Repair weld parts should be heated and welded as described above

The T5 temper should not be welded but can be welded if the procedure for T51 is used

Recommended Heat Treating Practice See Table

Alloy 771.0: Heat treatments

T2

Alloy 771.0: Minimum mechanical properties for separately cast test bars

T5 T6

'Iemper

T5 T51 T52 T6 TIl

ThosiIe strength (min) ksI MPa

290 220 250 290 330

42 32 36 42 48

YlOId strength (Min)(a) MPa ksI

260 185 205 240 310

38 1:1 30 35 45

E1ongatlon(b),

...

Hardness(c). DB

1.5 3.0 1.5 5.0 2.0

100 85 85 90 120

(a) 0.2%offset, (b) In 50mmor2 in. (c)500 kg load. 10mrnbaIl

'frealmeDl

'Iemper

T51 T52

TIl

Holdat415± 14°C (775±25 OF) for5 h; cooloutsidefurnacein stillair toroom temperature; hardenbyreheatingto 180±3 °C(36O±5 OF) for4 h;cool in air Holdat 180± 3 °C (355± 5 oF)for 3 to 5 h; cooloutsidefurnacein still air to room temperature Hold8t580 to 595°C (1080to 1100oF)for6 h;cooloutsidefurnace to roomtemperature in stillair;agebyholdingfor 3 h at 130°C (265oF)followed bycoolingin stillair Agebyholding8t205 °C (405oF)for6 h; cool in still air Holdat415 °C(775±25 oF)for5 h; coolfrom415 to 345°C (775t0650°F)in2hor more;coolfrom345to230°C (650to 450 "P) innotmorethan0.5h (20 mindesirable); coolfrom230 to 120°C (450to250 oF)inapproximately 2 h;coolfrom 120°C (250oF) to roomtemperature instill air outsideoffurnace;hardenbyreheatingto 165°C (330"P) for6to 16h andcoolingoutsideoffurnace in still air Holdat 580to 595°C (1080to 1100oF)for6 h;cooloutsidefurnace ioroomtemperature in stillair;agebyholdingat 140°C (285oF)for IS h followed bycoolingin stillair. Similarproperties can be obtainedbyagingat ISS°C (310°F) for3 h

850.0 (6.28n-1Cu-1 Ni) Commercial Names. Former designation. 750

Applications

Specifications U.S. and/or Foreign. AMS. Permanent mold casting: 4275; UNS number. A08500; Government. QQ-A-596 (class 15)

Typical Uses. Applications where excellent bearing qualities are required

Chemical Composition. Composition Limits. 0.7 to 1.3 Cu, 0.10 Mg max, 0.10 Mn max, 0.7 Si max, 0.7 Fe max, 5.5 to 7.0 Sn, 0.7 to 1.3 Ni, 0.20 Ti max, 0.30 others (total) max, bal Al Consequence of Exceeding Impurity Limits. High iron, manganese, or magnesium decreases ductility and increases hardness. High silicon modifies bearing characteristics

Mechanical Properties Tensile Properties. Typical for T5 temper: tensile strength, 160 MPa (23 ksi); yield strength, 75 MPa (11 ksi); elongation in 50 rom or2 in., 10% Hardness. T5 temper: 45 HB (500 kg load. 10 mm ball)

Recommended Heat Treating Practice Aging Temperature. 230°C (450 OF); hold at temperature for 8 h

Heat Treating Aluminum-Lithium Alloys Commercial aluminum-lithium alloys are targeted as advanced materials for aerospace technology primarily because of their low density, high specific modulus, and excellent fatigue and cryogenic toughness properties. Superior fatigue crack propagation resistance in comparison with that of traditional2xxx and 7xxx alloys, is primarily due to high levels of crack tip shielding, meandering crack paths, and the resultant roughness-induced crack closure. However, the fact that these alloys derive their superior properties extrinsically from the above mechanisms has certain implications with respect to small-crack and variable-amplitude behavior. For example, aluminum-lithium alloys lose their fatigue advantage over conventional aluminum alloys in compression-dominated variable-amplitude

fatigue spectra tests. However, in tension-dominated spectra, aluminumlithium alloys show greater retardations on the application of single-peak tensile overloads. The principal disadvantages of peak-strength aluminum-lithium alloys are reduced ductility and fracture toughness in the short-transverse direction, anisotropy of in-plane propeties, the need for cold work to attain peak properties, and accelerated fatigue crack extension rates when cracks are microstructurally small. These limitations have precluded the direct substitution of aluminum airframe alloys. However, certain aluminum-lithium alloys exhibit more damage tolerance, strength, and corrosion resistance than other aluminum-lithium alloys.

Weldalite 049 an AI-Cu-Li alloy Chemical Composition. Nominal. 5.4 Cu, 1.3 u, 0.4 Ag, 0.4 Mg, 0.14 Zr, Other, each: 0.4 Ag, bal Al

Product Forms. The alloy is available as sheet, plate, forgings, and extrusions

Applications. A weldable alloy for aerospace applications, such as propellant tanks for cryogenic service, Weldalite 049 was designed to replace major aluminum alloys such as 2219 and 2014 in launch system applications

In high strength plate and forging applications, Weldalite 049 is compared with 7075-T651 In welding applications for sheet, plate, forgings, and extrusions, it is compared with 2219

Characteristics Joining. Weldalite 049 has very good weldability; for example, it displays no discernible hot cracking in highly restrained weldments made by gas tungsten arc, gas metal arc, and variable polarity plasma arc (VPPA) welding. Extremely high weldment strengths have been reported using conventional 2319 filler, and even higher weldment strengths have been obtained with the use of a proprietary Weldalite filler (see adjoining Table). A mean VPPA weldment strength of 370 MPa (54 ksi) has been obtained by welding Weldalite 049 with 049 filler. High strengths (310 MPa, or 45 ksi, ultimate tensile strength) have also been attained with tungsten inertgas welds Forging. The ability of Weldalite 049 to attain high strength without cold work is particularly beneficial for forgings, where the uniform introduction of cold work is often impractical. Weldalite 049 small-scale forgings and commercial Boeing hook forgings have displayed tensile strengths of greater than 700 MPa (100 ksi). See Table for tensile properties in various tempers and product forms

Mechanical Properties Fracture Toughness. See Table for plain strain fracture toughness of Weldalite 049 extruded bar

Yield Strength, See Figure for the yield strengths of Weldalite 049 and another aluminum-lithium alloy, 2219 in the T87 temper, at cryogenic temperatures

Recommended Heat Treating Practice Like other age-hardened aluminum alloys, aluminum-lithium alloys achieve precipitation strengthening by thermal aging after a solution heat treatment. The precipitate structure is sensitive to a number of processing variables, including, but not limited to, the quenching rate following the solution heat treatment, the degree of cold deformation prior to aging, and the aging time and temperature. Minor alloying elements can also have a significant effect on the aging process by changing the interface energy of the precipitate, by increasing the vacancy concentration, and/or by raising the critical temperature for homogeneous precipitation. Like some other age-hardened 2xxx aluminum alloys, aluminum-lithium-base alloys also gain increased strength and toughness from deformation prior to aging. This unusual phenomenon has given rise to a number of thennomechanical processing steps for aluminum-lithium alloys aimed at optimizing mechanical properties after artificial aging Weldalite 049 shows high strength in a variety ofproducts and tempers (see adjoining Table). Its natural aging response is extremely strong with cold work (temper TI), and even stronger without cold work (1'4); in fact, it has a stronger natural aging response than that of any other known aluminum alloy. Weldalite 049 undergoes reversion during the early stages of artificial aging, and its ductility increases significantly up to 24%. Tensile strengths of 700 MPa (100 ksi) have been attained in both T6 and T8 tempers produced in the laboratory. As shown in adjoining Figure, specimens of Weldalite 049 in the peak-aged condition all have essentially the same level of hardness despite varying degrees (from 0.5 to 9%) of cold work prior to aging; the yield strength of Weldalite 049 is also relatively unaffected by prior cold work The ability of Weldalite 049 to attain high strength without cold work is particularly beneficial for forgings, where the uniform introduction ofcold work is often impractical (see adjoining Table). Weldalite 049 small-scale forgings and commercial Boeing hook forgings have displayed tensile strengths of greater than 700 MPa (100 ksi)


Weldalite049: Aging. Aging response of Weldalite 049 with various amounts of deformation prior to aging. Approximate aging temperature, 170°C (340 OF) 100


~, , ','l.

90

'.

-:". ,.A

-:

....A

~ 80

~

g>~

c:

'E '" 70 :r:

ii.. \ " \ ", \

,,

60

50

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-

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t

0.2

,

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,

,,

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--:::::- ~

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~.,.~ en

'J r

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10

20

50

I

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100

200

-

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500

Aging time, h

Unaged

Weldalite 049: Plane-strain fracture toughness (Kid of extruded bar Thmperature OF

°C 21 21

21 21 21 -195 -195

70 70 70 70 70 -320 -320

'Iemper

Orientation(a)

1'3 1'3 1'3

L-T T-L T-L L-T L-T T-L T-L

T6E4 T6E4

1'3 1'3


Kr

Aluminum-Lithium Alloys /271 Weldalite 049: Mean tensile properties of Weldalite 049, 2090, and 2219 weldments with conventional and Weldalite filler Thlckness

Base

'Thmperature(a)

metal/filler

VPPAsquore butt weldments(b) 2219/2319 RT 22191049 RT 22191049 RT 209012319 RT 20901049 RT 049/2319 RT 0491049 RT 0491049 RT VPPAweldments of extruded plote(c) 175°C (350 oF) 0491049 0491049 RT -195°C (-320 oF) 0491049 -253 °C (-423 oF) 0491049

mm

in.

PoSlWeld temper

Weldposllion

9.5 9.5 5.8 13 6.5 9.5 9.5 9.5

0.375 0.375 0.230 0.500 0.255 0.375 0.375 0.375

As-welded As-welded As-welded As-welded As-welded As-welded As-welded Naturallyagedfor 800 h

60· borizontal 60· horizontal 60° horizontal Venical 60· horizontal Vertical 60° horizontal 60· horizontal

9.5 9.5 9.5 9.5

0.375 0.375 0.375 0.375

As-welded As-welded As-welded As-welded

Ultimate tensilestrength MPa ksi

Yieldstrength MPa ksi

Elongation, %, in 25 mm (1 in.) 50 mm (2 in.)

273 283 325 252 285 274 315 372

39.6 41.1 47.1 36.5 41.3 39.8 45.7 54.0

140 154 161 156 147 248 249 290

20.4 22.3 23.4 22.7 21.3 36.0 36.1 42.1

7.9 7.1 9.0 8.6 7.1 1.5 1.5 3.0

287 372 413 505

41.6 54.0 59.9 73.2

188 290 360 427

27.3 42.0 52.2 61.9

5.4 3.0 1.9 1.7

4.6 4.7 5.0 4.7 3.8 1.0 1.5

(a) RT,room temperature. (b) Allfractures occurredin theheat-affected zone.(e) 100 x 9.5 mm (4 x 0.375 in.)plate

Weldalite 049: Yield strength. Yield strengths of two aluminum-lithium candidate alloys for cryogenic tankage applications. Strain rate, 4 x 10-4/swith a 0.5 h hold at temperature Temperature, OF

-400


III

::2 800

~

700

~

600

c

-200

-100

1000 900

11.

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-300

J--

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:2 500 Q)

0

100

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:i~25~024 g, E 15

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2091

2

4

6

8

10

12

Amount of cold working, %

14

~


2091: Resllonse of aluminum-lithium alloys 2090 and2091 to chemical milling Respo.... cbarac:leriolk

2090

Standard chemical millIng solution (NaOH + Na2S) Roughness, 11m Qiin.) 3.4-3.8 (135-150) 38-46 (1.5-1.8) Elchmte perside,lIm1min (milslrnin) TEA-modified chemical milling solutlon(a) Roughness,11M Qiio.) 2.25-2.35(89-93) Elchrateperside,lIm1min(mils/min) 43-50 (1.7-2.0)

AIIoy .... ponse 201Af/075

2091

0.9-1.0 (36-41) 40 (1.6)

1.8(70) 63.5 (2.5)

0.80-0.85(31-34) 40 (1.6)

1.65(65) 66 (2.6)

(a) Sodiumhydroxide,triethanolamine(I'EA), and sodiumsulfide

8090 Chemical Composition. Registered Limits. 0.20 Si, 0.30 Fe, 1.00 to 1.60 Cu, 0.10 Mn, 0.60 to 1.30 Mg, 0.10 Cr, 0.25 Zn, 2.20 to 2.70 u, 0.04 to 0.16 Zr, 0.10 Ti, others 0.05 (each), others 0.15 (total), bal Al Product Forms. Product forms include plate, extrusions, and forgings. Welded products also are available Applications. Aerospace applications are based on two critical requirements: damage tolerance and lowest possible density

Characteristics Alloy 8090 was developed to be a damage-tolerant medium-strength alloy with about 10% lower density and 11% higher modulus than 2024 and 2014, two commonly used aluminum alloys The chemical composition of 8090 has been registered with the Aluminum Association. And a variety of tempers have been developed that offer useful combinations of strength, corrosion resistance, damage tolerance, and fabricability, but there has been no official registration in the United States for any of these tempers or for any of the product forms. Descriptions of commonly used unofficial temper designations are given in an adjoining Table Strength and Toughness. Because alloy 8090 and its tempers and product forms are relatively new and unregistered, property data are incomplete. Available data for the current capabilities of 8090 products and tempers are given in an adjoining Table. The medium-strength products of alloy 8090 are aged to near-peak strength and show small changes in properties after elevated temperature exposure (see Table). The very underaged (damage-tolerant) products will undergo additional aging upon exposure to elevated temperatures. Changes in strength and toughness at cryogenic temperatures are more pronounced in 8090 than in conventional aluminum alloys; 8090 has a substantially higher strength and toughness at cryogenic temperatures (see Table) Microstructure. Plate, extrusions, and forgings have an unrecrystallized microstructure; damage-tolerant sheet has a recrystallized microstructure. Higher-strength sheet is available with a recrystallized or unrecrystallized microstructure (see Figure) Other considerations:

• The in-plane anisotropy of tensile properties for unrecrystallized products (plate, extrusions, forgings, and some medium-strength sheet) is higher in 8090 than in conventional alloys, placing more importance on 45° and shear properties

• Recrystallized damage-tolerant sheet and recrystallized mediumstrength sheet show much less anisotropy of tensile properties than do the unrecrystallized products Corrosion Properties. Performance is a strong function of the degree of artificial aging and the microstructure. Corrosion performance by product and temper for various types of corrosion tests is summarized in an adjoining Table

Alloy 8090 has displayed generally good exfoliation resistance in atmospheric exposure. For thick products, short-transverse SCC resistance is best in the peaked-aged temper. Thick products with unrecrystallized microstructures have good SCC resistance in the long-transverse direction, whereas those with recrystallized structures have a lower SCC threshold Forming. Bend tests indicate that 8090 has a lower material springback than that associated with conventional aluminum alloys Welding. The alloy is commercially weldable with the gas metal arc, gas tungsten arc, and electron beam processes

Recommended Heat Treating Practice Like other age-hardened aluminum alloys, aluminum-lithium alloys achieve precipitation strengthening by thermal aging after a solution heat treatment. The precipitate structure is sensitive to a number of processing variables, including, but not limited to, the quenching rate following the solution heat treatment, the degree of cold deformation prior to aging, and the aging time and temperature. Minor alloying elements can also have a significant effect on the aging process by changing the interface energy of the precipitate, by increasing the vacancy concentration, and/or by raising the critical temperature for homogeneous precipitation. Like some other age-hardened 2xxx aluminum alloys, aluminum-lithium-base alloys also gain increased strength and toughness from deformation prior to aging. This unusual phenomenon has given rise to a number of thermomechanical processing steps for aluminum-lithium alloys aimed at optimizing mechanical properties after artificial aging Solution Heat Treating. Alloy 8090 extruded bar is treated to the T3 temper at 540°C (1000 oF)

Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated water should be at room temperature, and suitably cooled so it stays below 38°C (100 OF) during quench cycle

Aluminum-Lithium Alloys /277 Nominal temperatures should be reached as rapidly as possible and maintained within ±6 °C (±1O "F) of nominal during time at temperature

Precipitation Heat Treating. Alloy 8090 extruded bar is peak aged at 190°C (375 oF) for 12 h

Cold working after solution treatment and before precipitation hardening is necessary to get specified properties in this temper (f3)

Time at temperature is approximate, Actual time depends on time required for load to reach temperature, with soak time measured from time load reaches temperature within ±6 °C (±l0 OF)

8090: Tensile properties and fracture toughness MInImum and Ifill Annealing temperatnre

Alloy

Common name

C19500

cztooo C22000 C22600 C23000 C24000 C26000 C26800,czrooo, C27400 C28000 C314OO, C31600 cnceo, C33500 C33200,C34200,C35300 C34000,C35000 C35600 C36000 C36500,C36600,C36700,C36800 C37000 C37700 C38500 C41100 C41300 C42500 C443OO, C44400,C44500 C46200,C46400-C467OO C48200,C48500 C50500 C5looo,C521oo,C524OO C53200,C534OO, C54400 C60600,C60800 C61000 C613OO, C61400 C61800,C62300-C625OO C61900 C63000 C63200 C64200 C63800 C65100 C65500 C66700 C67OOO, C674OO, C67500 C68700 C68800 C70600

cnooo.cnsoo C72500 C74500,C75200 C754OO, C75700,C77000 C78200 Cast copper alloys C95300-C95800

Gildingmetal Commercial bronze Jewelrybronze Red brass Low brass Cartridgebrass Yellowbrass Muntzmetal Leadedcommercial bronzes Low-leaded brass High-leaded brass Medium-leaded brass Extra-high-leaded brass Free-cutting brass LeadedMuntzmetal Free-cutting Muntzmetal Forgingbrass Architectural bronze

Inhibitedadmiralty brasses Navalbrass Leadednavalbrass Phosphorbronze Phosphorbronze Free-cutting phosphorbronze Aluminumbronze Aluminumbronze Aluminumbronze Aluminumbronze Aluminumbronze Aluminumbronze Aluminumbronze Low-silicon bronze High-silicon bronze Manganesebrass Manganesebronze Aluminumbrass Coppernickel, 10% Coppernickel, 20%,Coppernickel,30% Nickelsilver Nickelsilver Leadednickelsilver Aluminumbronzecastings

°C

OF

375-600 425-800 425-800 425-750 425-725 425-700 425-750 425-700 425-600 425-650 425-650 425-650 425-650 425-650 425-600 425-600 425-650 425-600 425-600 425-600 425-750 475-750 425-600 425-600 425-600 475-650 475-675 475-675 550-650 615-900 750-875 600-650(b) 550-800 6oo-700(c) 625-700(c) 600-700 400-600 475-675 475-700 500-700 425-600 425-600 4llO-600 600-825 650-825 675-800 600-750 600-815 500-620

750-1100 800-1450 800-1450 800-1400 800-1350 800-1300 800-1400 800-1300 800-1100 800-1200 800-1200 800-1200 800-1200 800-1200 800-1100 800-1100 800-1200 800-1100 800-1100 800-1100 800-1400 900-1400 800-1100 800-1100 800-1100 900-1200 900-1250 900-1250 1000-1200 1125-1650 1400-1600 l1oo-1200(b) 1000-1450 l100-1300(c) 1150-1300(c) 1100-1300 750-1100 900-1250 900-1300 930-1300 800-1100 800-1100 750-1100 1100-1500 1200-1500 1250-1475 1100-1400 1100-1500 930-1150

620-670

1150-1225

(a) Solution-treating temperature;seeTable4 for temperatures for specificalloys.(b) Cool rapidly(coolingmethodimportantin determining result of annealing),(c) Air cool (coolingmethodimportantin determiningresultof annealing)

Stress Relieving This process relieves internal stress in materials or parts without appreciably affecting their properties, Treatments are applied to wrought or cast copper and copper alloys. During the processing or fabrication of copper or copper alloys by cold working, strength and hardness increase as a result of plastic strain. Because plastic strain is accompanied by elastic strain, residual stresses remain in the product and can result in stress-corrosion cracking ofmaterial

in storage or service. unpredictable distortion during cutting or machining, and hot cracking during processing, brazing, or welding. In brasses that contain more than 15% Zn, stress-corrosion cracking, or "season cracking," can occur if sufficient amounts of residual tensile stress and trace amounts of atmospheric ammonia are present. Other copper alloys, such as cold-worked aluminum bronzes and silicon bronzes, may stress-corrosion crack in more severe environments.

Copper Alloys I 287

Table 2 Typical stress-relieving temperatures for wrought coppersandcopper alloys St...ss-...llen.mpemture ror Sheeland strip Rod andwire

Flat

Copperor copper alloy number Coppers Cl1000 C12000 C12200 C14200 Copper alloys C21000 C22000,C22600 C23000 C26000 C27000 C31400 C33000,C33200 C33500 C34000.C35000 C353oo.C356OO, C36000.C37700 C43000 C43400 C44300-C445OO C46200.C46400-C467OO C51000 C52100 C54400 C651OO. C65500 C68700 C69700 C70600 C71500 C73500 C74500 C75200 C75400 C75700 C77000

product.(a) °C(OF)

Electrolytic tough-pitch Phosphorus deoxidizedDLP Phosphorus deoxidizedDHP Phosphorus deoxidizedDPA

180(335)

Gilding,95% Commercial bronzeandjewelrybronze Redbrass,low brass Cartridgebrass Yellow brass,65% Leadedcommercialbronze High-andlow-leadedbrasses Low-leaded brasses Medium-leaded brasses Leaded.free-cutting, andforgingbrasses

275(525) 275 (525) 275 (525) 260(500) 260(500)

Nam.

Admiraltybrasses Navalbrasses PhosphorbronzeA PhosphorbronzeC PhosphorbronzeB-2 Siliconbronzes Aluminum brass.arsenical Coppernickel.10% Coppernickel,30% Nickelsilver.65-10 Nickelsilver.65-18 Nickelsilver.65-15 Nickelsilver,65-12 Nickelsilver.55-18

OC(OF)

Wire(c) °C(OF)

°C(°F)

180(335)

180(355)

180(355)

180(355)

275 (525) 275 (525) 275 (525) 260(500) 260(500)

260(500)

260(500)

275(525) 275(525)

275 (525) 275 (525)

275 (525)

275 (525)

420(790) 460(860) 380(715)

420(790) 460(860) 380(715)

380(715)

380(715)

340(645)

'Thbe(d)

OC (OF)

Part.

Rod(b)

'Thhe(.) °C(OF)

°C(OF)

220(430) 240(465) 260(500)

200(390) 220(430) 240(465)

330(625) 320(610) 290(555)

275(525) 260(500) 260(500)

320(610)

260(500)

320(610)

260(500)

330(625)

290(555)

480(895) 520(970)

420(790) 460(860)

Part.

300(570) 300(570) 290(555) 290(555) 300(570)

260(500) 260(500) 250(480) 250(480) 260(500)

275 (525) 275 (525) 260(500) 260(500) 275 (525)

290(555)

250(480)

260(500)

290(555) 300(570)

250(480) 260(500)

260(500) 275(525)

290(555) 300(570) 300(570) 300(570) 300(570)

250(480) 260(500) 260(500) 275(525)

260(500) 275 (525) 275 (525) 275 (525) 275 (525)

360(680)

360(680)

360(680)

400(750) 340(645)

350(660) 290(555)

380 (715) 320(610)

400(750) 350(660)

350(660) 300(570)

380 (715) 340(645)

Parts

340(645)

Note: Annealingtime is 1h with the exceptionoftube. (a)Extrahard. (b) Halfhard.(c)Spring.(d) Annealingtime for tube is 20 min.(e)Harddrawn

Stress-relief heat treatments are carried out at temperatures below those normally used for annealing. Typical temperatures for selected coppers and copper alloys are given in Table 2 (wrought products) and Table 3 (cast products).

Table 3 Typical stress-relieving temperatures for cast copperalloys Copperalloy number

°C

OF

CB1300-C82200 C82400-C82800 C83300-C84800 C95200-C95800 C96600-C978oo C99300

260 200 260 315 260 510

500 390 500 600 500 950

Thmpemture

Note:Time is 1 h per 25 mm (I in.) of sectionthicknessexceptfor copperalloy C99300;timefor it is 4 h per 25 mm (l in.)

Hardening Copper alloys that are hardened by heat treatment are of two general types; those that are softened by high-temperature quenching and hardened by lower-temperature precipitation heat treatments, and those that are hardened by quenching from high temperatures through martensitic-type reactions. Alloys that harden during low-to-intermediate-temperature treatments following solution quenching include precipitation-hardening, spinodal-hardening, and order-hardening types. Quench-hardening alloys comprise aluminum bronzes, nickel-aluminum bronzes, and a few special

copper-zinc alloys. Usually quench-hardened alloys are tempered to improve toughness and ductility and reduce hardness in a manner similar to that used for alloy steels. Low-Temperature-Hardening Alloys. For purposes of comparison, Table 4 lists examples of the various types of low-temperature-hardening alloys, as well as typical heat treatments (precipitation hardening and spinodal hardening) and attainable property levels for these alloys.

288/ Heat Treater's Guide: Nonferrous Alloys Table 4 Typicalheat treatments and resulting properties for severallow-temperature-hardening alloys Aging treatment °C

of

°C

of

Time,b

Hardneu

Eledrlcal conductivity, %IACS(b)

980 760-800 900-950 980-1000 775-800 885

1795 1400-1475 1650-1740 1795-1830 1425-1475 1625

500-550 300-350 455-490 425-500 305-325 482

930-1025 575-660 850-915 800-930 580-620 900

3 1-3 1-4 2-4 5 I

30HRB 35-44HRC 95-98HRB 68HRB 180HB 170HB

87-95 22 48 80 15 17

900-950 815-845

1650-1740 1500-1550

425-7fIJ 35Q.3fIJ

800-1400 6f1J-680

1-2 4

86HRC 32HRC

4-4

Solullon-trealing temperature(a) Alloy

Precipitation hardening C15000 C17000.CI72oo, C17300 C175OO. CI7600 CI8000(c),CI8400.CI85oo.C815oo C94700 C99400 Spinodal hardening C71900 C72800

Temperature

(a)Solutiontreatingisfollowedby waterquenching.(b) International AnnealedCopperStandard. (c) AlloyC18000(81540)mustbe doubleaged, typically3 h at 540 °C (1000 oF) followedby 3 h at 425°C (800 "P) (U.S. Patent 4.191.flJl) in orderto developthe higherlevelsofelectricalconduclivityandhardness

Order-Hardening Alloys. Certain alloys, generally those that are nearly saturated with an alloying element dissolved in the a phase, undergo an ordering reaction when highly cold worked material is annealed at a relatively low temperature. C61500, C63800, C68800, and C69000 are examples of copper alloys that exhibit this behavior. Strengthening is attributed to the short-range ordering of the dissolved atoms within the copper matrix, which greatly impedes the motion of dislocations through the crystals. The low-temperature order-annealing treatment also acts as a stressrelieving treatment, which raises yield strength by reducing stress concentrations in the lattice at the focuses of dislocation pileups.

Quench Hardening and Tempering. Quench hardening and tempering (also referred to as quench and temper hardening) are used primarily for aluminum bronze and nickel-aluminum bronze alloys, and occasionally for some cast manganese bronze alloys with zinc equivalents of37 to 41%. Aluminum bronzes with 9 to 11.5% AI, as well as nickel-aluminum bronzes with 8.5 to 11.5% AI, respond in a practical way to quench hardening by a martensitic-type reaction. Generally alloys higher in aluminum content are too susceptible to quench cracking for this treatment, and those with lower aluminum contents do not contain enough high-temperature ~ phase to respond properly.

Copper-Beryllium Alloys Because the solid solubility of beryllium in an a-copper matrix decreases as the temperature is lowered, beryllium-copper alloys are precipitation hardenable. Heat treatment typically consists of solution annealing, followed by precipitation hardening. Table 5 gives recommended schedules for the solution treating and precipitation hardening of the five major copper-beryllium alloys that are produced in wrought form. Optimum mechanical and physical properties for specific applications can be attained by varying these schedules, but the temperatures and times given in the adjoining Table constitute the most conventional practice and typically provide maximum tensile strength. In addition, better age hardening characteristics can be obtained if the material is cold worked after the solution anneal. Solution Treating. Wrought copper-beryllium alloy mill products are generally supplied solution treated or solution treated and cold worked

(Table 6). Material in these conditions can be fabricated without further heat treatment. Thus, solution treating is not typically a part of the fabricating process unless it is necessitated by a special requirement such as softening of the material for additional forming or is used as a salvage operation for parts that have been incorrectly heated for precipitation hardening. Precipitation Hardening. The cold working of solution-treated copper-beryllium alloys influences the strength attainable through subsequent aging; the greatest response to aging occurs in material in the cold-rolled hard temper. In general, work hardening offers no advantage beyond the hard temper because formability is poor and control of the precipitationhardening treatment for maximum strength is critical. For some applications, however, wire is drawn to higher levels of cold work prior to precipitation hardening. Table 7 lists the properties typically specified for mill products of the common copper-beryllium alloys.

Table 5 Solution treating and precipitation hardening of copper-beryllium alloys

Alloy

C17000 CI7200 C17300 C17500 C17510

Solution treatmenna) Thmperature 'llme(b). OF °C b 775-800 775-800 775-800 900-925 900-925

1425-1475 1425-1475 1425-1475 1650-1700 1650-1700

0.5-3 0.5-3 0.5-3 0.5-3 0.5-3

Aging treatment Temperature Time, °C

OF

b

300-330 300-330 300-330 455-480 455-480

575-625 575-625 575-625 850-900 850-900

1-3 1-3 1-3 1-3 1-3

(a) All alloysare cooled immediatelyandrapidlyfromthe solution-treating temperature. Thin sections such as stripcan be cooled in circulatingatmosphere;heaviersectionsrequirewaterquenching. (b) Shortertimesmaybe desirableto minimizegrain growth,particularlyfor thinsections

Table 6 Typical conditions of copper-beryllium mill products Tensile strengtb before aging Temper

Description

MPa

ksI

TBOO

Solutiontreated Solutiontreatedand cold workedto quarterhard Solutiontreatedandcold worked 10half hard Solutiontreatedandcold workedto hard

480 550 625 7fIJ

70 80 91 110

TOOl

TD02 TD04

Copper Alloys /289

Table 7 Properties and precipitation treatments usually specified for copper-beryllium alloys E1ongation(b). II>

Hardness(c)

Electri

b> c:

~

.. -e

c

0.044 Ag 30

200

QQ-C-502, QQ-C-576

QQ-C-576

QQ-C-502 QQ-C-502

QQ-C-502 QQ-B-825, MIL-B-19231 QQ-B-825 QQ-W-343. MIL-W-3318

~

.". >=

>=

QQ-C-502, QQ-C-576 QQ-C-502 QQ-C-502, QQ-B-825 QQ-B-825 QQ-W-343, MIL-W-3318

Xi

.=

300

20 100

QQ-B-825 QQ-W-343, MIL-W-3318

10 0 As drawn

200

400 300 Temperature,OC

0 600

Cl0400, Cl0500, and Cl0700: Typical mechanical properties Temper

Flat products, 1 mm (0.04 ln.) thick OS025 HOO HOI H02 H04 H08 HIO M20 Flat products, 6 mm (0,25 in.) thick OS050 HOO HOI H04 M20 Flat products, 25 rom (l ln.) thick H04 Rod, 6 mm (0.25 m.) in diameter H80(4O%) Rod, 25 mm (1 in.) in diameter OS050 H80(35%) M20 Rod, 50 mm (2 in.) in diameter H80(16%) Wire,2 mm (0.08 ln.) in diameter OS050 H04 H08 Shapes, 13 rom (0.50 in.) section size OSOSO H80(15%) M20

M3a

Tensilestrength MPo ksi

Yieldstreng1h(a) MPo ksi

235 250 260 290 345 380 395 235

34 36 38 42 50 55 57 34

76 195 205 250 310 345 365 69

220 250 260 345 220

32 36 38 50 32

310

Hardu ess HRB HR30T

Elongation in SOmm (1 iIL), %

HRF

11 28 30 36 45 50 53 10

45 30 25 14 6 4 4 45

45 60 70 84 90 94 95 45

10 25 40 50 60 62

69 195 205 310 69

10 28 30 45 10

50 40 35 12 50

40 60 70 90 40

10 25 50

45

275

40

20

85

380

55

345

50

10

220 330 220

32 48 32

69 305 69

10

44

310

45

275

240 380 455

35 55 66

220 275 220 220

32 40 32 32

Thbing, 25 mm (1.0 in.) diameter x 1.65 rom (0.065 in.) wall thickness OS050 32 220 OS025 235 34 H80(l5%) 275 40 H80(50%) 380 55

Shear strenglh ksi MPo

160 170 170 180 195 200 200 160

23 25 25 26 28 29 29 23

150 170 170 195 150

22 25 25 28

45

180

26

94

60

200

29

40 87 40

47

10

55 16 55

150 185 150

22 27 22

40

20

85

45

180

26

165 200 230

24 29 33 22 26 22 22 22 23 26 29

25 36 50 57 63 64

35(b) l.5(c) 1.5(c) 69 220 69 69

10 32 10 10

50 30 50 50

40 40 40

150 180 150 150

69 76 220 345

10 11 32 50

45 45 25 8

40 45 77 95

150 160 180 200

(a) AtO.5% extension underload. (b) Elongation in 25 nun (10 in.). (c) Elongation in 1500 nun (60 in.)

35

35 60

45 62

22


C10800 Commercial Names. Trade name. AMAX-LP copper; Common name. Oxygen-free, low phosphorus copper

Chemical Composition. Composition Limits. 99.95 Cu + Ag + P, 0.005 to 0.012 P min

Specifications (U.S. and/or Foreign). ASTM. Flat products: B 113, B 152, B 187, B 432. Pipe: B 42, B 302. Rod: B 12, B 133. Shapes: B 133. Tubing: B 68, B 75, B 88, B lll, B 188, B 251, B 280, B 306, B 357, B 360, B 372, B 395, B 447, B 543

Characteristics Typical Uses. Refrigerator and air conditioning tubing and terminals, clad products, gas and burner lines and units, oil burner tubes, condenser and heat exchanger tubes, pulp and paper lines, steam and water lines, tank gage lines, plumbing pipe and tubing, thermostatic control tubing, plate for welded continuous casting molds, tanks, kettles, and rotating bands

Fabrication Characteristics. Same as those ofC10100

Recommended Heat Treating Practice Annealing. Temperature range is 375 to 650°C (710 to 1200 oF) Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 "P) Cl0800: Typical mechanical properties .'!ensilestrength MPa ksi

'Iemper

Yield s1reoglh(a) MPa ksl

ElongaUon In SOmm(2 In.), %

HRF

Flat products, 1 mm (0.04 in.) thick 05025 HOO HOI H02 H04 H08

235 250 260 290 345 380

34 36 38 42 50 55

76 195 205 250 310 345

11 28 30 36 45 50

45 30 25 14 6 4

45 60 70 84 90 94

Flat products, 6 mm (0.25 in.) thick 05050 HOO H04 M20

220 250 345 220

32 36 50 32

69 195 310 69

10 28 45 10

50 40 12 50

40 60 90 40

Flat products, 25 mm (1 in.) thick H04

310

45

275

40

20

Rod, 6 mm (0.25 ln.) in diameter H80(4O%)

380

55

345

50

Rod, 25 mm (1 ln.) in diameter H80(35%)

330

48

305

Rod, 50 mm (2 in.) in diameter H80(16%)

310

45

275

Thbing, 25 mm (l in.) outside diameter x 1.65 mm (0.065 OS050 220 OS025 235 H55(l5%) 275 H80(4O%) 380

Hardness HRB HRJOT


160 170 170 180 195 200

23 25 25 26 28 29

10 50

150 170 195 150

22 25 28 22

85

45

180

26

20

94

60

200

29

44

16

87

47

185

27

40

20

85

45

180

26

150 160 180 200

22 23 26 29

195

28

10 25 40 50 60

25 36 50 57 63

Fa!lgue streogth(h) MPa ksl

76

11

90 90 97

13 13 14

115

17

ln.) wall thickness 32 34 40 55

69 76 220 345

10 11 32 50

45 45 25 8

40 45 77 95

35 60

50

310

45

10

90

50

45 63

Pipe,3/4 SPS H80(30%)

345 8

(a) Al 0.5% extension under load. (b) Al 10 cycles

C11000 (99.95Cu-0.040) Common Name. Electrolytic, tough pitch copper Designation. ETP Chemical Composition. Composition Limits. 99.90 Cu min (silver counted as copper) Silver has little or no effect on mechanical and electrical properties, but does raise recrystallization temperature and tends to produce fine grain copper Iron in commercial copper has no effect on mechanical properties, but traces can cause C11000 to be slightly ferromagnetic

Sulfur causes spewing and unsoundness; is kept below 0.003% in ordinary refining practice

Specifications (U.S. and/or Foreign). AMS. Sheet and strip: 4500. Wire: 470; ASME. Plate for locomotive fire boxes: SB11. Rod for locomotive stay bolts: SBI2; ASTM. See adjoining Table; SAE. J463; Government. Federal specifications: see adjoining Table. Military specifications: Rod: MIL-C-12166. Wire: MIL-W-3318, MIL-W-6712

Characteristics Typical Uses. C11000 is produced in all forms except pipe. Typical uses: downspouts, flashing, gutters, roofing, screening, gaskets, radiators, bus-

Wrought Copper 1301 Joining. Soldering properties are excellent; brazing and resistance butt

bars, electrical wire, stranded conductors, contacts, radio parts, switches, ball floats, butts, cotter pins. nails, rivets, soldering copper, tacks, chemical processing equipment, kettles, pans, printing rolls, rotating bands, roadbed expansion plates

welding properties are good. Gas shielded, arc welding properties are rated fair. Not recommended: oxyfuel gas, shielded metal are, resistance spot and resistance seam welding Caveat: Cll00 is subject to embrittlement when heated to 370°C (700 "F) or above in a reducing atmosphere, as in annealing, brazing, or welding. Embrittlement can be rapid if hydrogen or carbon monoxide is present in reducing atmosphere

General Corrosion Behavior. Copper often is used where resistance to corrosion is of prime importance. Sometimes it is better to use a copper alloy instead of an unalloyed copper. Tough pitch copper is considered to be immune in stress corrosion cracking in ammonia and other agents that induce such cracking of brasses. But tough pitch copper is susceptible to embrittlement in reducing atmospheres, especially those containing hydrogen

Recommended Heat Treating Practice Annealing. Temperature range is 475 to 750°C (890 to 1380 "F). Also see adjoining Figures concerning variations in tensile properties and grain size also time-temperature relationships in annealing

Machinability. 20% that ofC36000 (free-cutting brass) Forgeability. 65% that of C37700 (forging brass)

Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 "F)

Formability. Cold working and hot forming properties are excellent

'IYpical Softening Temperature is 360°C (680 oF)

C11000: Tensile properties. Variation of tensile properties and grain size of electrolytictough pitchcopper and similarcoppers

400

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\

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I-

1200

I

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/

1;/

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400 500 600 Annealing temperature, °C

700

800

900


Cll000: Typical mechanical properties Tensile strength ksi MPa

Temper

Yield strength(a) ksi MPa

Elongation in SOmm (2 In.), %

HRF

45 45 30 25 14 6 4 4 45

40 45 60 70 84 90 94 95 45 40 60 70


Hardness HRB HRJOT

Fatigue strength(b) MPa ksi

Flat products,l mm (0.04 in.) thick OS050 OS025 HOO HOI H02 H04 H08 HIO M20

10 11 28 30 36 45 50 53

150 160 170 170 180 195 200 200 160

22 23 25 25 26 28 29 29 23

150 170 170 195 150

22 25 25 28 22

45

180

26

94

60

200

29

55 16 55

40 87 40

47

150 185 150

22 27 22

20

85

45

180

26

165 200 230

24 29 33

150 160 180 200

22 23 26 29

150 180 150 150

22 26 22 22

220 235 250 260 290 345 380 395 235

32 34 36 38 42 50 55 57 34

69 76 195 205 250 310 345 365 69

220 250 260 345 220

32 36 38 50 32

69 195 205 310 69

28 30 45 10

50 40 35 12 50

40

310

45

275

40

20

85

380

55

345

50

10

220 330 220

32 48 32

69 305 69

10 44 10

310

45

275

40

240 380 455

35 55

10

10 25 40 50 60 62

25 36 50 57 63 64

76

11

90

90

13 13

97

14

115(c)

17(c)

Flat products, 6 mm (0.25 in.) thick OS050 HOO HOI H04 M20

10

10

25 50

90

Flat products, 25 mm (1.0 ln.) thick H04 Rod, 6 mm (0.251n.) in diameter H80(4O%) Rod, 25 mm (1.0 in.) in diameter OS050 H80(35%) M20 Rod, 50 mm (2.0 in.) in diameter H80(l6%) Wire,2 mm (0.08 in.) in diameter OS050 H04 H08

35(d) 1.5(e) 1.5(e)

66

Thbe, 25 mm (1.0 in.) diameter x 1.65 mm (0.065 in.) wall thickness OS050 OS025 H55(l5%) H80(4O%)

220 235 275 380

32 34 40 55

69 76 220 345

10 11 32 50

45 45 25 8

40 45 77 95

220 275 220 220

32 40 32 32

69 220 69 69

10 32 10 10

50 30 50 50

40

35 60

45 63

Shapes, 13 mm (0.50 in.) in diameter OS050 H80(15%) M20 M30

35 40 40

(a) At 0.5% extension under load. (b) At 10Kcycles in a reversed bending test. (c) At3 x 10K cycles in a rotating beam test. (d) Elongation in 250 nun (lOin.). (e) Elongation in 1500 nun (60 in.)

C11000: Tensileproperties. Short-time elevated-temperature tensile properties

LIVE GRAPH

LIVE GRAPH 200

400

,f

400

--

600

800

I

I

1000

1200 80

-

300

:;;

t

e.

200

~

100

l:

-.......

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~02temper ~

061tem~

100

200

300

40 ~ 30

;/I.

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400

Temperature.oC

500

600

60

t

l:

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o

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200

400

700

800

1000

1200

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r: 0 e '" 0

600

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Temperature, OF

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Temperature, OF

o o

100

200

300

400

Temperature,OC

500

600

700

Wrought Copper I 303

C11000: Tensile properties. Variation of tensile properties with amount of cold reduction by rolling


400

Cll000: ASTMand federal specifications

50 300 40

rf.

Spe
'""'"'-

Yieldstrength!a) MPa ksI

4 15 44 54 60 64 66

28 30 32 34 37 39 40

195 205 220 235 255 270 275

Note: Values for flatproducts.1 mrn(0.04 in.)thick.(a)At 0.5% extensionunderload


C21000: Properties. Variation of propertieswith zinc contentfor wroughtcopper-zincalloys


700

.

45

80

100 90

600

40

70 80

Q.

~

£500 C,

70

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(/)

30

U

50 25

300 40 200 80

40 100

30

60 40 20 80 Reduction of area by drawing, %

Hardness, cold drawn tempers

Elongation

100

22

060 temper 90

12.0 ~

~

;J!.

c0

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Cl

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c:

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Density and velocity of sound 8.2 Cu

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Electrical and thermel conductivities

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Annealing temperature, OF

500

200

400

600

800

1000

1200

I

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60 'iii

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1200

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1600

1800

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600 700 800 900 1000 Annealing temperature, °0

'--------------------------'

Wrought Copper /337

C26000: Annealing data. Finish rolling reduction 40.6%

LIVE GRAPH

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400

120

600

c

800

1000

1200

I

I

I

'\'

-.

:c 110 ex: :c

liOJ

100

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GPa 10· psi HB(b)

ThmUe strength MPa ksi

Microstructure. Has duplex structures of face-centered cubic alpha plus metastable, body-centered cubic beta with iron-rich precipitates

Forgeability. 75% that of C37700 (forging brass)

C62300: Typical mechanical properties of rod at various temperatures

-c

requiring resistance to corrosion. Caveat: not suitable for use in oxidizing acids

114 85 54 41

18.4 15.7 16.5 16.1 16.5 12.4 7.9 5.9

193 170 168 165 152 148 98 54

125 121 124 120 138 79 73 51

18.1 17.5 18.0 17.4 20.0 11.5 10.6 7.4

195 171 168 161 151 146 97 46

111

Annealing. Temperature range is 600 to 650°C (1110 to 1200 "F) Hot Working. Temperature range is 700 to 875 °C (1290 to 1610 "F) Hot shortness temperature is 1010 °C (1850 OF)

Annealed -182

-60 -29 20 205 315 425 540

-295 -75 -20 70 400

600 800 1000

(a) At 0.5% extension under load. (b) 3000 kg (6615Ib) load

C62300: Typical compressive properties for rod, H50 temper

Rod diameter

0.111> MPa ksI

g5 nun (:!>1 in.) 25-50 nun (1-2 in.) 50-75 nun (2-3 in.)

360 345 315

52 50 46

Compressivestrength at pennanent ..t or 1% lOll> MPa ksi MPa ksl

485 450 415

70 65 60

825 675

6W

120 98 90

2011> MPa ksi

965 930 895

140 135 130


C62300: Charpy V-notch. Variation in Charpy V-notch impact strength with temperature

Temperature. of -200

80

0

200 400 600

800 1000


-,

f

60 I----+----+---+------j ~ jCOld finished 40 ~ 40

/'

'\

1

j

20

/

/

'

I~i""ealed

o

-200

0

200

~~ 400

0

600

Temperature.YO

C62400 (86Cu-11AI-3Fe) Common name. Aluminum bronze, 11% Chemical Composition. Composition Limits. 82.80 to 88.00 Cu, 10.00 to 11.50 AI, 2.00 to 4.50 Fe, 0.30 Mn max, 0.25 Si max, 0.20 Sn max, 0.50 others max (total). Caveat: excessive Si and Al reduce ductility

Specifications (U.S. and/or Foreign). SAE J463

(0.011 in.lrev); fmishing speed, 290 mlmin (950 ftlmin) with feed of 0.1 mm1rev (0.004 in.lrev) Practice with carbide cutters at rate of 2.3 to 6.4 mrn (0.09 to 0.25 in.) cut: roughing speed, 53 mlmin (175 ftlmin) with feed of 0.3 mm1rev (0.011 in.lrev); finishing speed, 38 to 45 mlmin (125 to 150 ftlmin) with feed of 0.3 mm1rev (0.011 in.lmin)

Characteristics

Weldability. Similar to that of C62300

Duplex microstructure consists of alpha plus metastable beta phases and iron-rich precipitates


Typical Uses. Produced as rod and bar which are used in gears, wear

Annealing. Temperature range is 600 to 700 °C (1110 to 1290 "F)

plates, cams, bushings. nuts, drift pins, tie rods. Caveat: Parts can lose ductility with prolonged heating in range of 370 to 565°C (700 to 1050 "F), Also, alloy isn't suitable for use in oxidizing acids

General Corrosion Resistance. For general corrosion behavior, see article on C61400. Alloy resists nonoxidizing mineral acids, but hydrochloric is more corrosive than other acids of its type. Also, alloy is susceptible to dealloying, but heat treatment provides relief. In addition, alloy can't be used in presence of oxidizing acid like nitric

Machinability. 50% that of C36000 (free-cutting brass). Chips break readily. Carbide and tool steel cutters are used. Typical practice for tool steel cutters: roughing speed, 90 mlmin (300 ftlmin) with feed of 0.3 mlrev

Hot Working. Temperature range is 760 to 925°C (1400 to 1700 oF)

C62400: Typicalcompressive properties for rod, H50 temper Compressive strengthat pennanenl oel of

Ulllmale

Rod diameter

MPa

ksl

MPa

ksi

MPa

ksi

oompresslve strength MPa ksi

525 mm (SI in.) 25-50mm (1-2 in.) 50-75mm(2-3 in.)

290 220 175

42 32 25

470

68 58 48

885 825 795

128 120 115

1140 1090 1090

O.l~

l~

400

330

10~

16S 158 158

C62500 (82.7Cu-4.3Fe-13AI) Commercial Name. Trade names: AMPCO 21, Wearite 4-13

Typical Uses. Include guide bushings, wear strip, cams, sheet metal

Chemical Composition. Composition Limits. 12.50 to 13.50 AI, 3.50

forming dies, and forming rolls

to 5.00 Fe, 2.00 Mn max, 0.50 others max (total), bal Cu. Caveat: presence of elements such as Pb, Zn, P, and Si in more than trace amounts can cause hot shortness, reduced wear resistance, and increase tendency to spall

Microstructure. Primarily body-centered cubic beta phase with small crystals of ordered, close-packed, hexagonal gamma phase

Characteristics

ambient moisture and industrial atmospheres. But the alloy rarely is used in strongly corrosive environments. General corrosion properties are inferior to those of C62400 and C62300

Low ductility and low resistance to impact make it advisable to provide adequate structural support for C62500 components subjected to shock loads or high stress. Also, alloy's resistance to corrosion is inferior to that of aluminum bronzes containing less aluminum

General Corrosion Resistance. Corrosion resistance is adequate in

Machinability. 20% that of C36000 (free-cutting brass)

Wrought Copper /369 Formability. Hot forming properties are excellent. Cold working is not recommended

Recommended Heat Treating Practice Annealing. Temperature range is 600 to 650°C (1110 to 1200 "F)

Joining. Gas-shielded arc and shielded metal arc welding properties are good; brazing and resistance welding properties, fair. Not recommended: oxyfuel gas welding and soldering

Hot Working. Temperature range is 745 to 850 °C (1375 to 1560 "P)

C63800 (95Cu-2.8AI-1.8Si-O.40Co) Commercial Name. Trade name: Coronze


Chemical Composition. Composition Limits. 2.50 to 3.10 AI, 1.50

Annealing. Temperature range is 400 to 600°C (750 to 1110 "F). Also

to 2.10 Si, 0.25 to 0.55 Co, 0.80 Zn max, 0.10 Ni max, 0.05 Pb max, 0.10 Fe max, 0.10 Mn min, bal Cu

see adjoining figure on anneal resistance

Characteristics Typical Uses. Springs, switch parts, contacts, relay springs, glass sealing, porcelain enameling

C63800: Typical mechanical propertiesofsheet and strip

General Corrosion Resistance. C63800 is more resistant to stress corrosion than the nickel silvers, and are close to phosphor bronzes in performance. Resistance to crevice corrosion is far superior to that ofmost other copper alloys. At elevated temperatures, oxidation resistance is excellent. On the basis of weight gain after heating 2 to 24 h in air at temperatures of600 to 800 °C (1100 to 1300 OF), the alloy was consistently superior to Nickel 270, Nichrome (80Ni-20Cr), type 301 stainless steel, Incoloy 800 (ASTM B 408), C60600. Superiority was especially evident at 800°C (1300 OF)

Formability. Cold working and hot forming properties are excellent. Parts are formed by blanking, drawing, bending, shearing, and stamping Joining. Soldering usually is done with standard fluxes. Commonly used joining processes are brazing, gas-shielded arc welding, and all forms of resistance welding

Thmper

061 HOI H02 H03 H04 H06 H08 HIO

82 96 106 111 120 124 130 130(a)

565 660 730 765 825 855 895 895(a)

FJongatioo 105Omm (110.),'h

YIeldslreogth at 0.2'h offset MPa ksI

'Iensilestrength ksi MPa

56 82 93 99 109

385 565 640 680 750 780 800 820(a)

33 17 10 8 5 4 3 2(b)

113 116 119(a)

94 97 98 99 100 100 lOO(a)

C63800: Tensile properties. Typical short-time tensile properties of H02 temper Click here to view

C63800:Tensile properties. Annealresistanceof C63BOO strip, HOB temper. Typical room-temperature tensile properties for material annealed 1 h at varioustemperatures Click here to view

400

1000 BOO III

n,

:2

.£ ~

~

600

-

600

BOO I

-- l'\

\\ j

-

~ .

'" c I!!

400

t:

-e

Q;

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300

t

:E

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'#.

ci

Cold drawn 40%

.... Cold drawn 70%

100

•

-5

N

• Cold drawn 26%

200

400

200

20

o Cold drawn 25% and annealed

100

~~

800

400

600

800

0 1000

o

-400

-200

o

Testing temperature, °c

I

100

80

~'\ 1\ ~\ ~

-

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• Cold drawn 40% and annealed

+200

1600

I

-,

20

-a....:

v Cold drawn 70% and annealed

0 -400

1200

'200

400

~ ~.ri

600

800

o 1000

Testing temperature, °c

C71900 (67.2Cu-30Ni-2.8Cr) Commercial Name. Previous trade names. Copper-nickel, chromiumbearing; CA719; Common name. Cupronickel with Cr Chemical Composition. Composition Limits. 28.00 to 32.00 Ni, 2.40 to 3.20 Cr, 0.5 Fe max, 0.20 to 1.00 Mn, 0.10 to 0.20 Ti, 0.02 to 0.25 Zr, 0.04 C max, 0.25 Si max, 0.50 others max (total), bal Cu

ing is not recommended. Material thick enough to require multipass welds develops a minimum yield strength of 345 MPa (50 ksi), as-welded. Single pass welds develop a minimum yield strength of 275 MPa (40 ksi) aswelded. This value can be raised to 345 MPa (50 ksi) by a postweld heat treatment: 1 h at 480°C (900 OF)

Characteristics


Typical Uses. Heat exchange tubing, tube sheets, water boxes, ferrules, seawater pipe

Full properties of the spinodally decomposed condition can he obtained by furnace or still air cooling through the temperature range of 760 to 425°C (1400 to 795 "F) from a soaking temperature of 900 to 1065 °C (1650 to 1950 OF)

General Corrosion Resistance. In seawater, C71900 resists both general and localized attack. Corrosion rate is low-generally less than 0.1 mm/yr, or less than 4 mils/yrin seawater flowing at velocity around 1.8 mls (6 ftls). Welding does not have an adverse effect on corrosion resistance; and the alloy appears to be immune to stress-corrosion cracking in seawater Formability. C71900 can be cold worked in a manner similar to that for C71500, although C71900 has higher tensile and yield strengths at any given reduction. C71900 is readily hot worked from a starting temperature of 1040 to 1065 °C (1905 to 1950 OF), but hot working should not be continued below 840°C (1545 "F) because ofreduced ductility. About 25 % more extrusion pressure is required in comparison with practice for C71500. Because of microsegregation, cast billets should be homogenized 3 to 4 h at 1040 to 1065 °C (1905 to 1950 OF) before being extruded Joining. Properties for soldering, brazing, and all forms of arc welding are excellent. Resistance welding normally is not used. Oxyfuel gas weld-

C71900: Typical mechanical properties Yield strength

Condllion

MPa

ksi

at 0.2% offset MPa ksI

Heattreated(a) Half-hard temper(b) Hardtemper(c) Springtemper(d)

600 730 780 835

87 106 113 121

365 685 740 800

'Thll'lile strength

53

99 107 116

so mm (2 in.), %

EIongalionln

Hardness, HRB

32 14 8 6

87 100 100 101

(a)Spinodallydecomposedby air coolingfrom 900 °C (1650 "F). (b) Spinodallydecomposed.then cold rolled 20%. (c) Spinoda1ly decomposed.then cold rolled 37%. (d) Spinodally decomposed. thencold rolled60%


C72200 (83Cu-16.5Ni-O.5Cr) Commercial Names. Previous trade names. Copper-nickel, chromiumbearings; CA722; Common name. Cupronickel with Cr Chemical Composition. Composition Limits. 15.00 to 18.00 Ni, 0.30 to 0.70 Cr, 0.50 to 1.00 Fe, 0.40 to 0.90 Mn, 0.03 Si max, 0.03 Ti max, 0.03 C max, 0.5 others max (total), bal Cu

Formability. Has good properties for cold working and hot forming Joining. Properties for gas-shielded arc welding are excellent. Properties are good for soldering, brazing, shielded metal arc welding. and all types of resistance welding; oxyfuel gas welding properties are fair


Characteristics

Annealing. Temperature range is 730 to 815°C (1345 to 1500 OF)

Typical Uses. Condenser and heat exchanger tubing, saltwater pipe

Hot Working. Temperature range is 900 to 1040 °C (1650 to 1905 OF)

C72500 (88.2Cu-9.5Ni-2.3Sn) Commercial Name. Previous trade names. Copper-nickel. tin-bearing; CA725; Common name. Cupronickel with Sn

Chemical Composition. Composition Limits. 0.05 Pb max, 0.6 Fe max, 0.2 Mn max. 8.50 to 10.50 Ni, 1.80 to 2.80 Zn, 0.2 others max (total), balCu

Characteristics

Recommended Heat Treating Practice Annealing. Temperature range is 650 to 800°C (1200 to 1470 "F) Hot Working. Temperature range is 850 to 950 °C (1560 to 1740 "F)

C72500: Typical mechanical properties Yield strength 0.5 % extension

Typical Uses. Relay and switch springs, connectors. lead frames, control and sensing bellows, brazing alloy

General Corrosion Resistance. Alloy has excellent resistance to corrosion in seawater

Machinability. 20% that of C36000 (free-cutting brass) Formability. Has excellent capacity for cold working and hot forming by blanking, coining, drawing, forming, bending, heading, upsetting, roll threading, knurling, shearing, spinning. squeezing, stamping, and swaging Joining. Properties are excellent for soldering. brazing, and resistance spot and butt welding. Properties are good for gas-shielded are, shielded metal are, and resistance seam welding; properties for oxyfuel gas welding are fair

Temper

Thnsllestrength MPa ksl

under load MPa ks\

Elongation

0.2% offset MPa ks\

in SOmID (2 In.). %

Hardness, HRB

35 18 6 3 2 1 1

42 71 78 85 88 90 99

Flat products, 1 mm (0.04 In.) thick Annealed(a) Quarter hard Halfhard Hard Extrahard Spring Superspring

380 450 490 570

600 625 770

55 65 71 83 87 91 112

Wire, 2 mm (0.08 in.) diameter Annealed(a) . 415 60

150 365 450 515 555 570 570

22 53 65 75 81 83 83

170

25

150 400 475 555 590 620 740

22 58 69 81 86 90 108

(a) Grain size. 0.015 mm

C74500 (65Cu-25Zn-10Ni) Commercial Name. Nickel silver. 65-10


Chemical Composition. Composition Limits. 63.50 to 68.50 Cu. 9.00 to 11.00 Ni, 0.10 Pb max, 0.25 Fe max, 0.5 Mn max. 0.5 others max (total). balZn

ties are poor

Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 122. Bar: B 122, B 151. Rod: B 151. Wire: B 206; (Government) Flat products: QQ-C-585. Bar: QQ-C-585. Rod, shapes, flat wire: QQ-C-586. Wire: QQ-W-321

Characteristics Typical Uses. Hardware. rivets. screws, slide fasteners, optical, optical parts. Miscellaneous: etching stock, hollowware. name plates, plater's bars

Formability. Cold working properties are excellent; hot forming properJoining. Soldering and brazing properties are excellent. Properties are good for oxyfuel gas. resistance spot and resistance butt welding; gas metal arc and resistance seam welding properties are fair. Not recommended: shielded metal arc welding


Wrought Copper /379

C74500: Typical mechanical properties Temper

Tensile strength MPa k.sI

Yield streugthta) MPa k.sI

Elongation in SOmm!2ln.), %

HRF

Hardness HRB

HR30T


Flat products, 1 mm (0.04 in.) thick 05070 05050 05035 05025 05015 Hoo HOI H02 H04 H06 Wire,2 mm (0.08 in.) diameter

340 350 365 385 415 415 450 505 590 655

49 51 53 56 60 60 65 73 86 95

05070 05050 05035 05025 05015 Hoo(IO%) HOI (20%) H02(37%) H04(6O%) H06(75%) H08(84%)

345 360 385 400 435 450 495 585 725 825 895

50 52 56 58 63 65 72 85 105 120 130

125 130 140 160 195 240 310 415 515 525

18 19 20 23 28 35 45 60 75 76

49 46 43 40 36 34 25 12 4 3

67 71 76 80 85

22 28 35 42 52 60 70 80 89 92

30 34 38 44 51 55 63 70 76 78

285

41

295 310 345 380 405

43 45 50 55 59

50 48 45 40 35 25 10 7 5 3 1

(a) At 0.5% extensionunderload

C74500: Microstructure. Cold-rolled sheet, 2.5 mm (0.10 in.) thick, annealed at 650 to 700°C (1200 to 1290 OF). Longitudinal section shows equiaxed crystallized grains of a solid solution containing twin bands. Etchant; 60 g FeCls' 20 g Fe(NOs)s, 2000 mL Hp.100x

C75200 (65Cu..18Ni..17Zn) Common Name. Nickel-silver 65-18 Chemical Composition. Composition Limits. 63.00 to 66.50 Cu, 16.50 to 19.50 Ni, 0.1 Pb max, 0.25 Fe max, 0.50 Mn max, 0.50 others max (total), bal Zn Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 122. Bar: B 122, B 151. Rod: B 151. Wire: B 206; SAE J463; Government QQ-C-585. Bar: QQ-C-585, QQ-C-586. Rod, shapes, flatwire: QQ-C-586. Wire: QQ-W-321

Characteristics Typical Uses. Hardware, rivets, screws, table flatware, truss wire, zippers, optical goods, camera parts, core bars, templates. Miscellaneous: base for silver plate, costume jewelry, etching stock, hollowware, nameplates, radio dials Machinability. 20% that of C36000 (free-cutting brass) Formability. Cold working properties are excellent; hot forming properties, poor

380 I Heat Treater's Guide: Nonferrous Alloys Joining. Soldering and brazing properties are excellent; properties are good for oxyfuel gas, resistance spot and resistance butt welding; gas metal arc and resistance seam welding properties, fair. Not recommended: shielded metal arc welding

C75200: Typical mechanical properties

'Thmper


'ThnslJe strength ksI MPa

Yield strength(a) MPa IIsI

Eiongationin SO mm(11o.), ...

IIardneos

HRF

ORB IIR30T

Flat products. 1 mm (0.04 in.) thick 08035 08015 HOI H02 H04


400 415 450 510 585

58 60 65 74 85

170 205 345 427 510

25 30 50 62 74

40 32 20 8 3

170 415

25 60

42 20

170 205 450 550 620

25 30 65 80 90

45 35 16 7 3

85

09

40 55 73 83 87

65 72 75

Rod. 13 mm (O.Sln.) diameter 08035 H02(20%)

385 485

56 70

78

Wires,2 mm (0.08 in.) diameter 08035 08015 HOI H02 H04

400 415 505 590 710

58 60 73 86 103

(a) At 0.5% extension under load

C75400 (65Cu-20Zn-15Ni) knurling, shearing, spinning, squeezing, swaging. Hot forming properties are poor

Common Name. Nickel-silver, 65-15 Chemical Composition. Composition Limits. 63.50 to 66.50 Cu, 14.00

Joining. Soldering and brazing properties are excellent; properties are

to 16.00 Ni, 0.10 Pb max, 0.25 Fe max, 0.50 Mn max, 0.50 others max (total), bal Zn

good for oxyfuel gas resistance spot and resistance butt welding; gas metal arc and resistance seam welding properties are fair. Not recommended: shielded metal arc welding

Characteristics Typical Uses. Camera parts, optical equipment, etching stock, jewelry



Annealing. Temperature range is 600 to 815°C (1110 to 1500 "F)

Formability. Cold working properties are excellent-Processes include blanking, drawing, forming, bending, heading, upsetting, roll threading,

C75400: Typical mechanical properties of sheet or strip, 1 mm (0.04 ln.) thick 'ThnslJe 'Iemper

MPa

ks1

Yield strength(a) lIsi MPa

08070 08050 08035 08025 08015 HOO HOI H02 H04 H06

365 380 395 405 420 425 450 510 585 635

53 55 57 59 61 62 65 74 85 92

125 130 145 165 195 240 340 425 515 545

strength


18 19 21 24 28 35 49 62 75 79

Elongation in SOmm (1 In.)....

43 42 40 37 34 30 21 10 3 2

Hordness HRF HR30T

69 73 79 82 89 60HRB 70HRB 80HRB 87HRB 90HRB

27 33 41 46 53 55 63 70 75

77


285

295 305 325 360 370

41

43

44 47 52

54

Wrought Copper I 381

C75700 (65Cu-23Zn-12Ni) Common Name. Nickel-silver, 65-12 Chemical Composition. Composition Limits. 63.50 to 66.50 Cu, 11.00 to 13.00 Ni, 0.05 Pb max, 0.25 Fe max, 0.50 Mn max, 0.50 others max (total), bal Zn

Formability. Cold working properties are excellent-processes include blanking, drawing, forming, bending, etching, heading, upsetting, roll threading, knurling, shearing, spinning, squeezing, swaging. Hot forming properties are poor

Characteristics

Joining. Soldering and brazing properties are excellent; properties are good for oxyfuel gas, resistance spot and resistance butt welding. Gas metal arc and resistance seam welding properties are fair. Not recommended: shielded metal arc welding

Typical Uses. Slide fasteners, camera parts, optical parts, etching stock, nameplates



Annealing. Temperature range is 600 to 825°C (1110 to 1520 "F)

Specifications (U.S.and/or Foreign). (ASTM) Bar, rod: B 151. WIre:B 206; (Government) Wire: QQ-W-321

C75700: Typical mechanical properties of sheet or strip, 1 mm (0.04 in.) thick 'Iensllestrength 'Iemper

MPa

ksi

YIeldst">ngth(a) MPa ksi

OS070 OS050 OS035 OS025 OS015 HOO HOI H02 H04 H06

360 370 385 405 420 415 450 505 585 640

52 54 56 59 61 60 65 73 85 93

125 130 145 165 195 240 310 415 515 545

Elongation ln

18 19 21 24 28 35 45 60 75 79

50 IDDl (2 ln.), Ili

HRF

48 45 42 38 35 32 23 11

69 73 78 82 88

4 2

Shoarstrength ksi

Hardness HRB HRJOT

22 30 37 45 55 60 70 80 89 92

MPa

27 33 38 44 51 55 63 70 75 77

285

41

295 305 325 360 385

43 44 47 52 56


C77000 (55Cu-27Zn-18Ni) Common name. Nickel-silver, 55-18


Chemical Composition. Composition Limits. 53.50 to 56.50 Cu, 16.50 to 19.50 Ni, 0.10 Pb max, 0.25 Fe max, 0.50 Mn max, 0.50 others max (total), bal Zn


Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 122. Bar: B 122, B 151. Rod: B 151. Wire: B 206; SAE J463; (Government) Flat products: QQ-C-585. Bar: QQ-C-585, QQ-C-586. Rod, shapes, flat wire: QQ-C-586. Wire: QQ-W-321

C77000: Typical mechanical properties Thnsilestrength MPa ksi

Yield strength(a)

Characteristics

'Iemper

Typical Uses. Optical goods, springs, resistance wire

Flat products,1 mm (0.04 In.) thick OS035 415 60 185 H04 690 100 585 H06 745 108 620 H08 795 115 Wire, 2 mm (0.08 in.) diameter OS035 415 60 H08 (68%) 1000 145

Machinability. 30% that ofC36000 (free-cutting brass) Formability. Properties are good for cold working by blanking, forming, bending, shearing; hot forming properties are poor Joining. Soldering and brazing properties are excellent; properties are good for oxyfuel gas, resistance spot and resistance butt welding; gas metal arc and resistance seam welding properties are fair. Not recommended: shielded metal arc welding

(a}At 0.5% extension under load

MPa

ksi

27 85 90

Elongation ln 50 IDDl (210.), Ili

HRF

40

90

3 2.5

2.5 40 2

Hardness HRB HRJOT

55 91 % 99

77 80 81


C78200 (65Cu-25Zn-8Ni-2Pb) Chemical Composition. Composition Limits. 63.00 to 67.00 Cu, 1.50 to 2.50 Pb, 7.00 to 9.00 Ni, 0.35 Fe max, 0.50 Mn max, 0.10 others max (total), bal Zn

Characteristics Typical Uses. Key blanks, watch plates, watch parts Machinability. 60% that of C36000 (free-cutting brass) Formability. Cold working properties are good; hot forming properties, poor. Commonly fabricated by blanking, milling, drilling Joining. Soldering properties are excellent; brazing properties, good. Generally not recommended: oxyfuel gas, are, and resistance welding


C78200: Typical mechanical properties of 1 mm (0.04 in.) thick sheet

Thmper

Thnsile strength MP. lui

Yield strength(.) MP. lui

05035 05015 HOI H02 H03 H04 H06

365 405 425 475 540 585 625

160 185 290 400 435 505 525

53 59 62 69 78 85 91

(a>At 0.5% extension under load

23 27 42 58 63 73 76

Ekmgatkm inSOmm (2in.), %

40 32 24 12 5 4 3

Hardness, HRB

78HRF 85HRF 65 78 84 87 90

Shear strength MP. Ioii

275 295 305 325 350 370 400

40 43 44 47 51 54 58

Copper Casting Alloys C81300 Commercial Names. Previous trade name. CA813; Common name. Beryl-

Applications

Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involing beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits

Typical Uses. Higher-hardness electrical and thermal conductors


Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease.

Solution Heat Treating. Temperature range is 980 to 1010 °C (1800 to

lium-copper

ChemicalComposition. Composition Limits. 98.5 Cu min, 0.10 to 0.20 Be, 0.6 to 1.0 Co. (Cu + sum of named elements shall be 99.5% minimum.)

1850 oF)

Aging. Temperature is 480°C (900 "P) Stress-Relieving. Temperature is 260 °C (500 OF)

C81400 Commercial Names. Previous trade name. Beryllium-eopper 7OC,CA814; Common name. Be-modified chrome copper

ChemicalComposition. Composition Limits. 98.5 Cu min, 0.6 to 1.0 Cr, 0.02 to 0.10 Be

Specifications (U.S. and/or Foreign). RWMA Class 11

Applications Typical Uses. Electrical parts that meet RWMA Class 11 standards. The beryllium content of this alloy ensures that the chromium content will be kept under control during melting and casting, thus allowing the production of chrome copper castings of consistently high quality

Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryl-

lium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits

Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 1000 to 1010 °C (1830 to 1850 OF)

Aging. Temperature is 480°C (900 oF)

C81500 Commercial Names. Previous trade names. Chromium-copper, CA815; Common name. Chrome copper Chemical Composition. Composition Limits. 98.0 to 99.6 Cu, 0040 to 1.50 Cr, 0.015 Pb max, 0.04 P max, 0.15 max other (total)

Consequence of Exceeding Impurity Limits. Elements that contribute to hot shortness must be avoided. Because of the high solution temperatures

necessary to develop the desired mechanical properties, elements that enter into solid solution must be held to close limits

Applications

buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits

Typical Uses. Electrical and/or thermal conductors used as structural


members in applications requiring greater strength and hardness than that of cast coppers C80100 to C81100

Solution Heat Treating. Temperature range is 1000 to 1010 °C (1830 to

Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and

1850 OF)

Aging. Temperature is 480°C (900 oF)


C81800 (97Cu-1.5Co-1 Ag-0.4Be) Commercial Names. Previous trade name. Beryllium-copper alloy SOC, CA818 Chemical Composition. Composition Limits. 0.30 to 0.55 Be, 1.4 to 1.7 Co, 0.8 to 0.12 Ag, 0.15 Si max, 0.20 Ni max, 0.10 Fe max, 0.10 Al max, 0.10 Sn max, 0.002 Pb max, 0.10 Zn max, 0.10 Cr max, bal Cu Consequence of Exceeding Impurity Limits. Generally, electrical conductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening Specifications. RWMA Class III

Typical Uses. The silver content of C81800 provides an improved surface conductivity over other RWMA Class III alloys. Typical uses are resistance welding electrode tips and holders and arms Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with

300

Q)

lIBrdnes8, HRB

20

52 70 40 96

12 25

6

(a)At 0.2%offset. (h) In 50 mm (2 In.). (c)Aged2 h at 480 °C (900oF).(d)Solutiontreated at 900 to 950°C (1650to 1750oF).(e) Aged3 h at 480 °C (900°F)

300

250 al :I:

~

c:

200

~

r r>

150

100

/

/

1/ /

:I:

C82000: Aging curves for cast and solution-treated C82000

I

425-480°C

o

1/

/400°C


~

V

/

V

370°C/

/ 540°C

/

/ 1/

2

3

4

5

6

7

8

Aging lime, h

C82200 (98Cu-1.5Ni-O.5Be) Commercial Names. Previous trade name. Beryllium-copper alloy 3OC, CA822; Common name. Beryllium-copper casting alloy 30C, 35C, or 53B

Chemical Composition. Composition Limits. 0.35 to 0.8 Be, 1.0 to 2.0 Ni, 0.15 Si max, 0.20 Co max, 0.10 Fe max, 0.10 AI max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max, bal Cu

Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 900 to 955°C (1650 to 1750 oF)

Aging. Temperature range is 445 to 455 °C (835 to 850 oF)

Consequence of Exceeding Impurity Limits. Generally, electrical conductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening

Specifications (U.S. and/or Foreign). RWMA Class III

Applications Typical Uses. Seam welder electrodes,projection welder dies, spot welding tips, beam welder shapes: water-cooled holders, arms bushings for resistance welding, clutch rings, brake drums

Precautions In Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffmg under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits

C82200: Typicalmechanical properties Thmper

As-cast Castandaged(c) TBOO(d) TFOO(d)(c)

'Iensilestrengtb MPa ksi

345 450 310 655

50 65 45 95

YIeldstrengtb(a) lis; MPa

170 275 85 515

25 40 12 75

E1oogaoon(b). 'J>

Hardness, HRB

20 15 30 7

55 75 30 %

(a)Al 0.2% offset.(h) In 50 mm (2 In.). (c)Aged 3 h al480 °C (900 "P), (d)Solutiontreatedat 900 to 955°C (1650to 1750oF)


C82400 (98Cu-1.7Be-O.3Co) Commercial Names. Previous trade name. Beryllium-copperalloy 165C, CA824; Common name. Beryllium-copper casting alloy 165C Chemical Composition. Composition Limits. 1.65 to 1.75 Be, 0.20 to 0.40 Co, 0.10 Ni max, 0.20 Fe max, 0.15 AI max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max, bal Cu Consequence of Exceeding Impurity Limits. Generally, electricalconductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening

lium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits

Specifications (U.S.and/or Foreign). Government QQ-C-390 (CA824)


Applications

Solution Heat Treating. Temperature range is 790 to 815°C (1450 to 1500 oF)

Typical Uses. C82400 was developed for use in marine service as a corrosion-resistant. pressure-tight casting material. Its lower beryllium content compared to C82500 makes this alloy the least expensive of the commercial high-strength beryllium-copper alloys. When its hardness is relatively low, C82400 exhibits greater-than-normal toughness. Typical uses include various parts for the submarine telephone cable repeater system and hydrophone, molds for forming plastics, safety tools, plunger tips for die casting, cams, bushings, bearings, valves, pump parts, and gears Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryl-

Aging. Temperature is 345 °C (650 oF)



Yield streogth(a) MPa ksi

As-cast Castandaged(c) TBOO(d) 1FOO(d)(c)

485 690 415 1070

275 550 140 1000

70 100 60 155

E1ongation(b), %

Hardness

15 3 40 1

78HRB 21HRC 59HRB 38HRC

40 80 20 145

(a)At 0.2% offset. (b) In 50 mm(2 in.). (c) Aged 3 h at 345°C (650 oF). (d) Solution treatedat 800 to 815 °C (1475 to 1500 oF)

C82500 (97.2Cu-2Be-O.5Co-O.25Si) Commercial Names. Previous trade name. Beryllium-copper 2OC, CA825; Common name. Standard beryllium-copper casting alloy Chemical Composition. Composition Limits. 95.5 Cu min, 1.90 to 2.15 Be, 0.35 to 0.7 Co, 0.20 to 0.35 Si, 0.20Ni max, 0.25 Fe max, 0.15 AI max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max. Available with or without 0.02 to 0.10% Ti added as a grain refiner Consequence of EXceedingImpurity Limits. Generally, electrical conductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening Specifications (U.S. and/or Foreign). (AMS) Investment castings: 4890; (Government) Sand castings: QQ-C-390, MIL-C-19464 (class 2); centrifugal castings: QQ-C-390; precision castings: MIL-C-1l866 (composition 17), MIL-C-17324; investment castings: MIL-C-22087; (Other) ICI-Cu-2-10780

Applications Typical Uses. Molds for forming plastics, die casting plunger tips, safety tools, cams, bushings, bearings, gears, sleeves, valves, wear parts, structural parts, resistance welding electrodes and inserts, holders, and structural members Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryl-

Iium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits

Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 790 to 800°C (1450 to 1475 OF) Aging. Temperature is 345 °C (650 oF)



As-cast Castandaged(c) TBOO(d) 1FOO(d)(c)

515 825 415 1105

75 120 60 160

Yield streogth(a) MPa ksi 275 725 170 1035

40 105 25 150

Eiongaoon(b), %

Hardness

15 2 35 1


(a) At 0.2% offset. (b) In 50 nun (2 in.), (c) Aged 3 h at 345°C (650 "F), (d) Solution treatedat 790 to 800 °C (1450 to 1475 oF)

Copper Casting Alloys /387

C82500 (beryllium-copper alloy 21C): Agingcurves for solution-treated alloy

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C82600 (97Cu-2.4Be-O.5Co) Commercial Names. Previous trade name. Beryllium-copper 245C; Common name. Beryllium-copper casting alloy 245C Chemical Composition. Composition Limits. 2.25 to 2.45 Be, 0.35 to 0.7 Co, 0.20 to 0.35 Si, 0.20 Ni max, 0.25 Fe max, 0.15 Al max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max, bal Cu Consequence of EXceedingImpurity Limits. Generally, electricalconductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening Specifications (U.S. and/or Foreign). Government QQ-C-390

Applications Typical Uses. C82600 is intermediate in beryllium content between C82500 and C82800. It exhibits better fluidity, castability, and hardness than C82500 and better toughness and lower cost than C82800. C82600 is used primarily to produce molds for plastic parts. In pressure castings, the lower pouring temperature results in longer tool life than for similar castings of C82500 Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with

these limits. is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits

Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 790 to 800°C (1450 to 1475 OF) Aging. Temperature is 345 °C (650 "F)



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80 120 70 165


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50 105 30 155

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(a) At 0.2% offset. (b) In 50 mm (2 in.).(c) Aged 3 h at 345°C (650 "F), (d) Solution treated at 790 to 800 °C (1450 to 1475 oF)


C82800 (96.6Cu-2.6Be-O.5Co-O.3Si) Commercial Names. Previous trade name. Beryllium-copper alloy 275C, CA828; Common name. Beryllium-copper casting alloy 275C

Chemical Composition. Composition Limits. 94.8 Cu min, 2.50 to 2.75 Be, 0.37 to 0.7 Co, 0.20 to 0.35 Si, 0.20 Ni max, 0.25 Fe max, 0.15 Al max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max Consequence of Exceeding Impurity Limits. Generally, electrical conductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening Specifications (U.S.and/or Foreign). (Government) QQ-C-390, MILT-16243, MIL-C-19464 (Class IV); Other ICI-Cu-2-10785

a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits

Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 790 to 800°C (1450 to 1475 OF)

Aging. Temperature is 345 °C (650 "F), See adjoining figure

.Applications Typical Uses. C82800 is a special-purpose, high-fluidity casting alloy developed for molds for forming plastics and other applications where the casting process should replicate finest detail with maximum fidelity and the resultant part must exhibit maximum hardness and wear resistance for a cast beryllium-copper alloy. Typical uses are molds for forming plastics, cams, bushings, bearings, valves, pump parts, sleeves, and precision cast parts for the communications, textile, aerospace, business machine, firearm, instrument, ordnance, and other industries Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating

C82800: Typical mechanical properties of sand cast test bars Thmper

Thnslle strength MPo ksI

Yieldstrength!o) MPo ksi

As-cast Cast and aged(c) TBOO{d) TFOO(d)(c)

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C86700 Commercial Names. Previous trade name. CA867; Common names. Leaded high-strength yellow brass; 80,000 psi tensile manganese bronze Chemical Composition. Composition Limits. 55.0 to 60.0 Cu, 1.0 to 3.0 AI, 1.0 to 3.0 Fe, 0.5 to 1.5 Pb, 1.0 to 3.5 Mn, 1.0 Ni max, 1.5 Sn max, 30.0 to 38.0 Zn. Ingot for remelting specifications may vary from the ranges shown Copper and Zinc Specifications. In reporting chemical analyses by the use of instruments such as spectrograph, x-ray, and atomic absorption, copper may be indicated as balance. In reporting chemical analyses ob-

tained by wet methods, zinc may be indicated as balance on those alloys with over 2% Zn Specifications (U.S. ancIJor Foreign). ASTM Centrifugal, B 271; ingot, B 30; sand, B 584, B 763

Applications Typical Uses. High-strengthfree-machiningmanganese bronze valve stems

Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)

C86800 Commercial Names. Previous trade name. CA868; Common name. Nickel-manganese bronze

max, bal Zn. Ingot for remelting specifications may vary from the ranges shown

Chemical Composition. Composition Limits. 53.5 to 57.0 Cu, 2.0 Al max, 1.0 to 2.5 Fe, 0.20 Pb max, 2.5 to 4.0 Mn, 2.5 to 4.0 Ni, 1.0 Sn

Copper and Zinc Specifications. In reporting chemical analyses by the use of instruments such as spectrograph, x-ray, and atomic absorption,

392/ Heat Treater's Guide: Nonferrous Alloys copper may be indicated as balance. In reporting chemical analyses obtained by wet methods, zinc may be indicated as balance on those alloys with over 2% Zn

Typical Uses. Marine fittings and propellers

Specifications (U.S. and/or Foreign). (ASTM) Die, B 176; (Govern-


ment) Sand, QQ-C-390; valves, WW-V-1967

Applications

Stress-Relieving. Temperature is 260°C (500 oF)

C87300 (formerly C87200) Commercial Names. Trade name. Everdur, Herculor, Navy Tombasi1; Common name. Silicon bronze, 95-1-4, 92-4-4,89-6-5

Applications Typical Uses. As a substitute for tin bronze where good physical and

max, 0.25 Zn max, 0.20 Fe max, 3.5 to 4.5 Si, 0.8 to 1.5 Mn

corrosion resistance are required. Bearings, bells, impellers, pump and valve components, marine fittings, statuary and art castings

Cu + Sum of Named Elements. 99.5 min


Specifications (U.S.and/orForeign). (ASTM) Centrifugal, B 271; ingot, B 30; sand, B 585, B 763; SAE J 461, J 462; Government QQ-e-390, WW-V-1967; Military MIL-C-1l866 (composition 19); MIL-C-22229; (Other) Ingot code number 50DA

Stress-Relieving. Temperature is 260°C (500 oF)

Chemical'Composition. Composition Limits. 94.0 Cu min, 0.20 Pb

C87600 Commercial Names. Common names. Low-zinc silicon brass, CA876

Applications

ChemicalComposition. Composition Limits. 88.0 Cu min, 0.50 Pb

Typical Uses. Valve stems

max, 4.0 to 7.0 Zn, 0.20 Fe max, 3.5 to 5.5 Si, 0.25 Mn max

Cu + Sum of Named Elements. 99.5 min

Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 oF)

Specifications (U.S. and/or Foreign). (ASTM) Ingot, B 30; sand, B 584, B 763; (Other) Ingot code number 500D

C8761 0 Commercial Names. Common name. Silicon bronze

Applications

Chemical Composition. Composition Limits. 90.0 Cu min, 0.20 Pb

Typical Uses. Bearings, bells, impellers, pump and valve components,

max, 3.0 to 5.0 Zn, 0.20 Fe max, 3.0 to 5.0 Si, 0.25 Mn max

Cu + Sum of Named Elements. 99.5 min Specifications (U.S. and/or Foreign). (ASTM) Ingot: B 30; (Other) Ingot code number 500E

marine fittings, corrosion-resistant castings


Copper Casting Alloys /393

C87500, C87800 (82Cu-4Si-14Zn) Commercial Names. Trade name. Tombasil; Common name. Silicon brass, 82-4-14

Chemical Composition. Composition Limits. C87500: 79.0 min Cu, 0.50 Pb max, 12.0 to 16.0 Zn, 0.50 Al max, 3.0 to 5.0 Si. C87800: 80.0 to 83.0 Cu, 0.25 Sn max, 0.15 Pb max, 0.15 Fe max, 0.15 Mn max, 0.15 Al max, 3.75 to 4.25 Si, 0.01 Mg max, 0.25 max others (total), bal Zn, but As, Sb, and S not to exceed 0.05 each, and P not to exceed 0.01 Specifications (U.S. and/orForeign). (ASTM) C87500: ingots, B 30; centrifugal castings, B 271; sand castings, B 584. C87800: die castings, B 176; SAE J 462; Government C 87500: sand castings, QQ-C-390; invest-

ment castings, MlL-C-22087 (composition 4). C87800: die castings, MILB-15894 (class 3); (Other) Ingot code number 500T

Applications 'TYpical Uses. Bearings, gears, impellers, rocker arms, valve stems, brush holders, bearing races, small boat propellers

Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 oF)

C87900 Commercial Names. Common names. Silicon yellow brass, CA879 ChemicalComposition. Composition Limits. 63.0 Cu min, 0.25 Sn max, 0.25 Pb max, 30.0 to 36.0 Zn, 0.40 Fe max, 0.15 Al max, 0.8 to 1.2 Si, 0.15 Mn max, 0.50 Ni (including Co) max, 0.05 S max, 0.01 P max, 0.05 As max, 0.05 Sb max. Total named elements shall be 99.5% minimum Copper and Zinc Specifications. In reporting chemical analyses by the use of instruments such as spectrograph, x-ray, and atomic absorption, copper may be indicated as balance. In reporting chemical analyses obtained by wet methods, zinc may be indicated as balance on those alloys

with over 2% zinc. In determining Cu min, copper may be calculated as Cu +Ni

Specifications (U.S. and/or Foreign). (ASTM) Ingot: B 30; die: B 176; Government MlL-B-15894; SAE J461, J462; Ingot code number 5000

Applications 'TYpical Uses. General-purpose die-easting alloy having moderate strength


C92200 (88Cu-6Sn-1.5Pb-4.5Zn) Commercial Names. Common name. Navy "M" bronze, steam bronze, 88-6-1.5-4.5

Chemical Composition. Composition Limits. 86.0 to 90.0 Cu, 5.5 to 6.5 Sn, 1.0 to 2.0Pb, 3.0to 5.0Zn, 1.0Nimax, 0.25 Fe max, 0.05 Pmax. (1.5 P max for continuous castings), 0.05 S max, 0.005 Si max, 0.25 Sb max

Specifications (U.S.amI/or Foreign). ASTMB 584, B 61, B 271, B 505, B 30; SAE J462 (C92200); Government CA922, QQ-B-225 (Alloy number I), MlL-B-1654I, MIL-B-15345; (Other) Ingot code number 245

Applications Typical Uses. Component castings of valves, flanges and fittings, oil pumps, gears, bushings, bearings, backing for babbitt-lined bearings, pressure-containing parts at temperatures up to 290°C (550 "F), and stresses up to 20 MPa (3 ksi)


C92200: BrinellHardness

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Sintering Copper-Based Materials

Production Sintering of Bronze


Sintering Time and Temperature. Typical sintering furnace temperatures for bronze range from 815 to 860°C (1500 to 1580 "F); total sintering time within the hot zone may range from 15 to 30 min, depending on the furnace temperature selected. required dimensional change. and most importantly. the presence of an optimum alpha grain structure. Sintering atmospheres should be protective and reducing to facilitate sintering. Reduction of the copper oxides that may surround each copper powder particle and reduction of tin oxide formation allow for increased diffusion rates. Consequently, faster sintering rates and more homogeneous structures can be obtained. Dimensional Change. Effective sintering is essential. because the homogeneity of the sintered structure affects the resultant secondary forming and operational characteristics of the finished part. A typical sintering/dimensional change pattern is shown in an adjoining Figure. which illustrates the relationship of a "medium growth" copper-tin system as a function of total time in the furnace hot zone. Absolute sintered dimensional characteristics typically are unique to a specific source of copper and tin powders. For example. sintered dimensional consistency may be obtained by blending two or more base copper powders that exhibit different growth characteristics and/or by use of tin powders that also exhibit different growth characteristics. Generally, copper-tin blends composed of relatively coarse powder sinter to higher growth values than a blend composed of finer powders. After powder blends have been tested and adjusted to provide an approximation of target dimensions. final adjustments are made during production sintering to obtain dimensional precision. Factors affecting the ultimate. or peak, dimensional values include physical characteristics of the constituents and compacted density. Control of sintered dimensions in premix systems is achieved by manipulating sintering time and/or temperature.

Dimensional change in an elemental bronze blend (90Cu10Sn) as a function of time and temperature. Sintered in hot zone at 845°C (1555 OF) in dissociated ammonia atmosphere +3.0

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Production Sintering of Brass and Nickel Silvers Sintering temperatures for standard brasses range from 760 to 925 °C (1400 to 1700 "F), Temperature selection depends on the brass alloy being sintered and the mechanical properties desired after sintering. Lower brasses with higher zinc contents and lower melting points are sintered at the lower temperature. Generally. a starting temperature of 100°C (180 "F) below the solidus temperature (as determined from any copper-zinc binary alloy constitutional diagram) is suitable. Nickel silver may be sintered at 870 to 980°C (1600 to 1800 "F), Currently. only one base alloy is used for the manufacture ofPIM structural parts; it has nominal composition of 64Cu-18Ni-18Zn. The leaded alloy composition contains 1.5% Pb. Sintering characteristics are similar to those of the brasses; therefore. responses to sintering parameters that affect dimensional and mechanical properties of brass are equally applicable to nickel silver. Sintered Properties. Dimensional and mechanical properties of brasses and nickel silvers are primarily affected by compact density and the

amount of time at temperature, as well as the sintering temperature itself. As mentioned above, other elements that affect dimensional and mechanical properties usually are not added to powders. However. sintered properties, especially dimensional change. may be effectively controlled by manipulation of sintering time at the appropriate temperature. Each alloy exhibits unique dimensional characteristics-a 90Cu-IOZn brass compacted at 414 MPa (30 tsi) and sintered for 30 min at 870°C (1600 oF) may shrink 0.5%, while a 70Cu-30Zn brass similarly treated may shrink 2.5%. Figures show typical property relationships that can be controlled through manipulation of time at temperature. The leaded brasses shown in Figures (80Cu-20Zn and 70Cu-30Zn) are commonly used for structural parts fabrication. Densities shown are "average" for compacting lubricated prealloyed powders containing 0.375% lithium stearate and 0.375% zinc stearate at 414 MPa (30 tsi). As shown, close dimensional control may be obtained with a minimum reduction in mechanical properties after 15 min at temperature. Ductility is increased for subsequent forming operations,

Sintering Copper-Based Materials /413 such as sizing, cold re-pressing for densification, or coining, by increasing sintering time. Atmosphere protection is required for sintering brasses and nickel silvers to prevent oxidation and to ensure effective sintering. Use ofIithium stearate as the base lubricant allows the use of most common sintering atmospheres over a wide range of dew points. Although dry hydrogen or dissociated ammonia provides the best sintering atmosphere, comparable properties can be obtained with nitrogen-based or partially combusted hydrocarbon gas atmospheres. When sintering, compacts should be protected from direct impingement of furnace flame curtains and atmosphere gases by partially or fully covering loaded trays to minimize zinc loss. Because it has a high vapor pressure at standard sintering temperature (boiling point of pure zinc is 906 "C, or 1663 OF), zinc may be lost to the atmosphere as it diffuses through to the particle surfaces. Loss of excessive surface zinc results in a change in surface composition. In the case of brasses, pink copper or zinc-depleted areas are apparent. Although superficial zinc losses do not adversely affect sintered properties, surface finish is diminished; finished parts may be rejected because of color differences. Q)

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70Cu-30Zn: Properties vs. Sintering Times. Effect of varying sintering time on properties of prealloyed 70Cu-30Zn leaded brass (nominal 1.5% Pb). Lubricant: 0.375% lithium stearate and 0.375% zinc stearate. Compaction pressure; 414 MPa (30 tsi). Green density: 7.3 g/cm 3 • Sintering temperature and atmosphere: 870°C (1600 OF) in dissociated ammonia

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Furnace Design. A variety of protective sintering tray arrangements can be. used, including graphite trays with full covers and graphite base plates with steel covers, for example. Sintering of brasses on open belts is not common practice for several reasons; for example, overheating may melt brass parts that may fuse to the mesh belt. Also, excessive heat and direct impingement of flame curtain gas through the mesh may impair effective sintering due to oxidation and premature partial lubricant removal. Direct exposure to the sintering atmosphere may also cause objectionable surface dezincing. Conversely, extremely gastight protective sintering setups should be avoided, because lubricant decomposition products may not be completely volatilized. Excessive residual lubricant within the compact inhibits sintering; consequently, mechanical properties are adversely affected. Typically, compacts with excessive internal lubricant residuals may not be salvaged by additional passes through a full sintering cycle. To avoid or minimize the deleterious effect of residual lubricants, covered tray setups should facilitate free venting oflubricant gases to the flowing furnace atmosphere.

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80Cu-20Zn: Tensile Properties. Effect of lubricants and sintering time at temperature on tensile properties, sintered density, and dimensional change of brass compacts

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80Cu-20Zn: Properties vs. Sintering Times. Effect of varying sintering time on properties of prealloyed 80Cu-20Zn leaded brass (nominal 1.5% Pb). Lubricant: 0.375% lithium stearate and 0.375% zinc stearate. Compaction pressure: 414 MPa (30 tsi). Green density: 7.6 g/cm 3 • Sintering temperature and atmosphere: 870°C (1600 OF) in dissociated ammonia


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Magnesium Alloys

Heat Treating Magnesium Alloys Magnesium alloys usually are heat treated either to improve mechanical properties or as a means of conditioning for specific fabricating operations. The type of heat treatment selected depends on alloy composition and form (cast or wrought), and on anticipated service conditions. Solution heat treatment improves strength and results in maximum toughness and shock resistance. Artificial aging (precipitation heat treatment) after solution treatment gives maximum hardness and yield strength, but with some sacrifice oftoughness. As applied to castings, artificial aging without prior solution treatment or annealing is a stress-relieving treatment that also somewhat increases tensile properties. Annealing of products lowers tensile properties considerably and increases ductility, thereby facilitating some types offabrication. Modifications of these basic treatments have been developed for specific alloys, to obtain the most desirable combinations of properties. For example, increasing the aging time for some magnesium alloy castings considerably increases yield strength (although with some sacrifice of ductility). Also, combinations of solution treating, strain hardening, and artificial aging are applied to alloy HM2lA sheet to improve mechanical properties over those attainable by solution treating and artificial aging alone. For certain magnesium alloys, development of properties depends almost entirely on heat treatment. In magnesium-zirconium alloys, however, the extremely pronounced grain-refining effect of the zirconium also plays a very important role in improving mechanical properties. The mechanical properties of most magnesium casting alloys can be improved by heat treatment. Casting alloys can be grouped into seven general classes of commercial importance on the basis of composition:

• • • • •

Magnesium-aluminum-manganese (example: AMl00A) Magnesium-aluminum-zinc(examples:AZ63A, AZ81A, AZ91C, AZ92A) Magnesium-zinc-zirconium (examples: ZK51A, ZK61A) Magnesium-rare earth metal-zinc-zirconium (examples:EZ33A, ZFAIA) Magnesium-rare earth metal-silver-zirconium, with or without thorium (examples: QE22A, QH21A) • Magnesium-thorium-zirconium, with or without zinc (examples: HK31A, ZH62A, HZ32A) • Magnesium-zinc-copper (example: ZC63A)

In most wrought alloys, maximum mechanical properties are developed through strain hardening, and generally they are either used without subsequent heat treatment or merely aged to a T5 temper. Occasionally, however, solution treatment, or a combination of solution treatment with strain hardening and artificial aging, will substantially improve mechanical properties. Wrought alloys that can be strengthened by heat treatment are grouped into five general classes according to composition:

• • • • •

Magnesium-aluminum-zinc (example: AZ80A) Magnesium-thorium-zirconium (example: HK31A) Magnesium-thorium-manganese (examples: HM21A, HM31A) Magnesium-zinc-zirconium (example: ZK60A) Magnesium-zinc-copper (example: ZC71A)

Types of Heat Treatment Commonly used heat treatments for wrought and cast alloys and the tempers on which they are based are listed in Table 1 and Table 2. Individual datasheet articles on each ofthe alloys named in Table 1 follow this introduction. Annealing. Wrought magnesium alloys in various conditions of strain hardening or temper can be annealed by being heated at 290 to 455°C (550 to 850 OF), depending on alloy, for one or more hours (Table 3). This procedure usually will provide a product with the maximum anneal that is practical. Because most forming operations on magnesium are at elevated temperature, the need for fully annealed wrought material is less than with many other metals. Stress Relieving of Wrought Alloys. Stress relieving is used to remove or reduce residual stresses created in cold and hot working, shaping and forming, straightening, and welding. Table 4 gives recommended stress-relieving times and temperatures. When extrusions are welded to hard-rolled sheet, the lower stress-relieving temperature and longer time should be used to minimize distortion; for example, use 150°C (300 "F) for 60 min rather than 260 °C (500 "F) for 15 min. Stress Relieving of Castings. Machining of castings to close dimensionallimits, the necessity of avoiding warpage and distortion, and the desirability of preventing stress-corrosion cracking in welded magnesiumaluminum casting alloys make it mandatory that castings be substantially free from residual stresses. Although magnesium castings do not normally contain high residual stresses, the low modulus of elasticity of magnesium alloys means that comparatively low stresses can produce appreciable elastic strains.

Table1 Heat treatments commonly applied to magnesium alloys Alloy

Heal lrealmenl(a)

Casting alloys AMlOOA

1\l.63A AZSIA AZ9lC AZ92A EZ33A EQ2lA HK3IA HZ32A QE22A QH2lA

WFA3A WE54A ZC63A ZE4IA ZE63A ZH62A ZK5IA ZK6lA

T4. T5. T6. T61(b) T4.T5.T6 T4 T4.T6 T4.T6 TS T6 T6 T5 T6 T6 T6 T6 T6 TS T6(c) TS TS T4,T6

Wrought alloys AZSOA HM2IA HM3IA ZC7IA

ZK60A

T5 TS, 1'8.1'81(d) TS F,T5.T6 TS

(a) Indicated by temper designations (see Table), (b) Same as T6 except aged for longer time to increase yield strength. (e) Thermal treatment must include hydriding. (d) Mill modification of1'8 to

improve mechanical properties

418/ Heat Treater's Guide: Nonferrous Alloys Residual stresses may arise from contraction due to mold restraint during solidification, from nonuniform cooling after heat treatment, or from quenching. Machining operations also can result in residual stress and require intermediate stress relieving prior to final machining. Weld repairs may introduce severe stresses and should be followed by some type ofheat treatment to prevent subsequent movement and cracking. See Table 5 for postweld heat treatments. The following heat treatments for castings will provide stress relief without significantly affecting mechanical properties:

Table 2 Basic temper designations for magnesium alloys ElqIlanation

Designation

As-fabricated Annealed,recrystallized(wroughtproductsonly) Strainhardened(wroughtproductsonly) Strainhardenedonly Strainhardenedand partiallyannealed Strainhardenedand stabilized Solutionheat treated;unstabletemper Heat treatedto producestabletempersother thanF, 0, or H Annealed(castproductsonly) Solutionheat treatedand cold worked Solutionheat treated Artificiallyaged only Solutionheat treatedand artificiallyaged Solutionheat treatedand stabilized Solutionheat treated,cold worked,and artificiallyaged Solutionheat treated,artificiallyaged,and coldworked Artificiallyaged and cold worked

F

o H

HI H2 H3 W

T 1'2

Solution Treating and Aging. Schedules for solution treating and aging of magnesium alloys are summarized in Table 6. In solution treating of magnesium-aluminum-zinc alloys, parts should be loaded into the furnace at approximately 260°C (500 OF) and then raised to the appropriate solution-treating temperature slowly, to avoid fusion of eutectic compounds and resultant formation of voids. The time required to bring the load from 260 °C (500 "F) to the solution-treating temperature is determined by the size of the load and by the composition, size. weight, and section thickness of the parts, but 2 h is a typical time. All other heat-treatable magnesium alloys can be loaded into the furnace at the solution-treating temperature. For alloy HK3IA, it is important to bring the load to temperature as rapidly as possible to avoid grain coarsening. During aging, magnesium alloy parts should be loaded into the furnace at the treatment temperature, held for the appropriate period. and then cooled in still air. As indicated in Table 6, there is a choice ofartificial aging treatments for some alloys; results are closely similar for the alternative treatments given.

Table 3 Annealing temperatures for wrought magnesium alloys Annealingtemperafureta) Alloy

AZ31B AZ3IC AZ6IA AZSOA HIGIA HM2IA HM3IA ZK60A

Original temper

F,HIO.HII,H23,H24,H26

345 345 345 385 400 455 455 290

F F

F,T5,T6 H24 T5,T8,T81 T5 F,T5,T6

650 650 650 725 750 850 850 555

1'3 T4 TS T6 T7 1'8 1'9 TIO

Note: For moreinformationon the designationsoutlinedhere, seeVolume2 oftheASM Handbook series

Table 4 Recommended stress-relieving treatments for wrought magnesium alloys Sbeet

Alloy

AZ31B AZ3IB-F AZ6IA AZ6IA-F AZSOA-F AZSOA-T5 HK3IA HM2IA-T5 HM2IA-TB HM2IA-TBI HM3IA-T5 ZC7IA-T5 ZK60A-F ZK60A-T5

Annealed Thmperature TIme, OF min OC

Bard rolled Thmpemture 'lime, OF -c min

345

650

120

150

300

60

345

650

120

205

400

60

345

230

650

450

60

290

555

30

370 400

700 750

30 30

180

Extrusionsand forgings Thmperature 'lime, OF OC min

260

500

15

260 260 205

500

500 400

15 15 60

370

700

30

430 330 260 150

800 625 500 300

60 60 15 60

Note: Stressrelievingafterwelding, to prevent stress-corrosion cracking,is necessaryonly for alloys thatcontainmorethan 1.5%aluminum

(a) Tune at temperature. I h or more

Table 5 Postweld heat treatments for magnesium alloy castings Alloy

Weldingrod

AZ63A

AZ63Aor AZ92A(a)

AZSIA AZ91C

AZ92AorAZIOI AZ92Aor AZI OJ

AZ92A

AZ92A

EQ21A EZ33A HIGIA HZ32A QE22A QH21A WE43A WE54A ZC63A ZE4IA ZH62A ZK5IA

EQ21A EZ33A HK3IA(g) HZ32A(g) QE22A QH21A WE43A WE54A ZC63A ZE4IA(g) ZH62A(g) ZK5IA(g)

Thmperbeforeweldlng

F F T4 T40rT6 T4

Desiredtemper after welding

T4

T4 T6 T4 T6 T4 T4

T40rT6 T4 T40rT6 T40rT6 ForT5 T40rT6 ForT5 T40rT6 T40rT6 T40rT6 T40rT6 T40rT6 ForT5 ForT5 ForT5

T4 T6 T6 T5 T6 T5 T6 T6 T6 T6 T6 T5 T5 T5

T6

Postweklbeat treatment

12h at385 ±6 °C (725± 100F)(b) 12hat385 ±6 °C (725± 100F)(b), plus5 hat220 °C (430°F) 0.5 h at 385± 6 °C (725± 10oF) 0.5h at 385± 6 °C (725± 10oF),plus5 hat 220°C (430oF) 0.5h at415 ±6 °C (775± 10°F)(c) 0.5 hat415±6°C(775± IO°F)(c) 0.5 hat415±6°C(775 ±1O°F)(c),plus4hat215°C(420°F)or 16hatI70°C(340°F) 0.5hat41O±6°C(765± IO°F)(c) 0.5hat41O±6 °C(765 ± IO°F)(c),plus4 h at 260°C (500°F) or5 h at220°C (430°F) I h at 505± 6 °C (940± 10oF),quench,16h at 205°C (400oF) 2 h at 345°C (6500F)(d), and/or5 h at215 °C (420oF),or 24 h at 220 °C (430oF) 16hat205°C(4OO°F)(e) 16hat315°C(600°F) I hat51O±6°C(950± 10°F), quench,16hat205 °C(4OO°F) I hat51O±6°C (950± IO°F),quench, 16hat205°C(4OO°F) I hat510±6°C(950± IO°F),quench,16hat205 °C (400°F) I hat51O±6°C(950± 10°F), quench,16h at 205°C(4OO°F) I hat425±6°C(795± 10°F), quench,16h at 205°C (400°F) 2 hat330 °C (6250F)(f) 12h at 250°C(480 0F)(f) 2 h at 330°C (625oF), plus 16h at 175°C (350oF)

(a) AZ63Arod must be usedfor weldingAZ63Ain theF temperbecause12h at385 °C (725 "F) causesgermination in welds madewith AZ92Arod:AZ92A rod normallyis usedfor weldingAZ63Ain the T4 orT6 conditionunlessAZ63Arod is requiredby specifications. (b)Preheatto260°C (500°F); heat to specifiedtemperatureat no more than83 0C/h(150 °FIb).(c) Usecarbon dioxideor sulfurdioxide atmosphere.(d) Heatingfor2 h at 345°C (650 "F) resultsin slightlossofcreepstrength.(e) Alternativetreatment: I h at315 °C (600oF),plus 16h at 205°C (400 "F). (f)Alternativetreatment: 2 h at 330°C (625 oF),plus 16 It at 175°C (350 oF).(g) Or EZ33A

Magnesium Alloys /419 Reheat Treating. Under normal circumstances, when mechanical properties are within expected ranges and the prescribed heat treatment has been carried out, reheat treating is seldom necessary. However, if the microstructures of heat-treated castings indicate too high a compound rating, or if the castings have been aged excessively by slow cooling after solution treating, reheat treating is called for. Most magnesium alloys can

be reheat treated with little danger of germination (excessive grain growth). When reheat treating of alloy HK31A is necessary, however, the castings should be checked carefully for evidence of germination. To prevent germination in Mg-AI-Zn alloys, solution reheat-treating time should be limited to 30 min (assuming proper solution treatment of thick sections during prior heat treatment).

Table 6 Recommended solution-treating and aging schedules for magnesium alloy castings and wrought alloy ZC71A For castings up to 50 mm (2 in.) in section thickness; heavier sections may require longer times at temperature. Solutiontreallng!c) Maximum temperature

Aging!a) Alloy

Final temper

Temperature

Temperature

°C,±6(b)

Magnesium-aluminum-zinc castings(d) AM100A T5 230 T4 T6 T61 26O(f) AZ63A T5 T4 T6 AZS1A T4 AZ91C T5 168(g) T4 T6 AZ92A T5 260 T4 T6 Magnesium-zinc-mpper castings ZC63A(k) T6 Magnesium-zirconium castings EQ21A(k) T6 EZ33A T5 175 HK3IA(m) T6 HZ32A T5 315 QE22A(k) T6 QH21A(k) T6 WE43A(k) T6 WE54A(k) T6 ZE41A T5 330(n) ZE63A(P) T6 ZH62A T5 330 plus: 177 ZKS1A T5 177(q) ZK61A T5 150 T6 Wrought products ZC71A(k) T5 180 ZC7IA(k) T6

°F,±10(b)

'Dme,b

450

5

500(f)

335(g)

500

·C,±6(b)

°F,±10(b)

Time,b

°C

425(e) 425(e) 425(e)

795(e) 795(e) 795(e)

16-24(e) 16-24(e) 16-24(e)

435 435 435

810 810 810

385 385 415(e)

725 725 775(e)

10-14 10-14 16-24(e)

390 390 418

735 735 785

415(e) 415(e)

775(e) 775(e)

16-24(e) 16-24(e)

418 418

785 785

168(h)

335(h)

16(h)

410(j) 41O(j)

765(j) 765(j)

16-24(j) 16-24(j)

415 415

775 775

218

425

5

440

820

4-8

445

830

200

390

16

520

965

4-8

530

985

200

390

16

565

1050

2

570

1060

205

400

16

525 525 525 527

970 970 970 970

4-8 4-8 4-8 4-8

540 540 535 535

1000 1000 995 995

205 205 250 250

400 400 480 480

8 8 16 16

480

900

10-72

490

910

140

285

48

500(r)

930(r)

2(r)

500

930

130

265

48

430

800

4-8

435

810

180

355

16

°C,±6(b)

°F,±1O(b)

'Dme,b

230 218

450 425

5 25

218(f)

425(f)

5(f)

4(f)

16(g)

4

350

16

600

16

625(n)

2(n)

625 350 350(q) 300

2 16 12(q) 48

355

Aging after solutiontreating 'fimperature

OF

16

(a) Agingto theT5temperis done fromtheas-fabricated(I) condition.(b) Exceptwherequoteddifferently. (c) Aftersolutiontreatmentand beforesubsequentaging.castingsare cooledto roomtemperature by fast fan cooling,except where otherwiseindicated.Use carbon dioxide,sulfurdioxide,or 0.5 to 1.5%sulfurhexafluoridein carbon dioxideas a protectiveatmosphereabove 400 °C (750 "F), (d) For solutiontreating,Mg-AI-Znalloys areloadedinto !he furnaceat 260 °C (500 "P) and broughtto temperatureovera 2-hperiodat a uniformrateof temperatureincrease.(e) Alternativetreatrnenr, to prevent germination(excessivegraingrowth):6 h at415 ±6 °C (775± 10°F), 2 h at352±6 °C (665± 10oF),lOh at415 ±6 °C (775± 10oF).(f) Alternative treatment: 5 hat230±6 °C (450± 10°F).(g)Alternative treatment:4 h at 215±6 °C (420± 10"F), (b) Alternativetreatment: 5 to6 h at215 ±6 °C (420± 10 "F), (j)Alternativetreatment, to preventgermination(excessivegraingrowth):6 h at41O±6 °C (765± 10 "F), 2 h at 352 ± 6 °C (665± 10 "F), 10h at 410 ± 6 °C (765± 10 "F), (k) Quenchfromsolution-treating temperatureeitherin waterat 65°C (150oF)or in other suitablemedium.(m)AlloyHK31Acastings must beloadedinto!hefurnacealreadyat temperatureand broughtbackto temperature as quicklyas possible.(n)Thistreatmentisadequatefor developmentof satisfactoryproperties;it may be followedby 16 h at 177± 6 °C (350± 10oF)to providevery slightimprovements inmechanicalproperties.(p) AlloyZE63Amustbe solutiontreatedin a specialhydrogenatmospherebecauseits mechanicalproperties are developedlhroughhydridingofsomeofits alloyingelements.Hydridingtimedependsonsectionthickness;asaguide, 6.4mm(0.25in.)sectionsrequireapproximatelylOb, and 19mm (0.75in.)sections requireabaut72 h. Followingsolutiontreatment, ZE63Ashouldbequenchedin oil, waterspray,or air blast.(q)Alternativetreatment: 8 h at 218± 6 °C (425± 10oF).(r)Alternativetreatment: 10 h at480 ± 6 °C (900± 10oF)


Effects of Major Variables Casting size and section thickness, relation of casting size to volume capacity of the furnace, and arrangement of castings in the furnace are mechanical considerations that can affect heat-treating schedules for all metals. Section Size and Heating Time. No general rule exists for estimating time of heating per unit of thickness for magnesium alloys. However, because of the high thermal conductivity of these alloys, combined with their low specific heat per unit volume, parts reach soaking temperature quite rapidly. The usual procedure is to load the furnace and to begin the soaking period when the loaded furnace reaches the desired temperature. The heat-treating times given in Table 5 have been found to be satisfactory for normal furnace loads and for castings of moderate section thickness. In the heat treating of magnesium alloy castings with thick sections (occasionally as low as 25 mm, or 1 in., but usually over 50 mm, or 2 in.), a good rule is to double the time at the solution-treating temperature. For example, the usual solution treatment for AZ63A castings is 12 h at about 385°C (725 "F), while 25 h at about 385°C is suggested for castings with section thicknesses greater than 50 mm (2 in.). The best way to determine whether additional solution-treating time is required is to cut a section through the thickest portion of a scrap casting and examine the center of the section microscopically: if heat treatment is complete, this examination will reveal a low compound rating. Heat-Treating Time and Temperature. As demonstrated by the data in Fig. 1 to 4, the mechanical properties of magnesium alloys can be varied within wide limits by varying the heat-treating times and tempera-

tures. The effect ofquenching media on properties is an example of another important consideration. See Table 7.

Solution-treating temperature. OF

Fig. 1 Tensile properties as function of solution treating temperature. Tensile properties as functions of solution-treating temperature. Data were obtained from test bars of casting alloy QE22A-T6 machined from 25 mm (1 in.) diam cast specimens. The bars were held at temperature for 4 h

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Sources Information in this introduction and in the 24 datasheet articles that follow is from three volumes in ASM International's Handbook Series: • Properties and Selection: Nonferrous Alloys and Special-Purpose Materials, Vol 2, 10th ed. • Heat Treating, Vol 4, 10th ed. • Metallography and Microstructures, Vol 9, 10th ed.

Table 7 Effectof quenching medium on average tensile properties ofQE22A-T6 Queochlogmedlum

Stillair(c) Airblast(c) Waterat65°C (150°F)(c) 30%glycolatroomtemperature(d)

Thnslle strength ksI MPa

232 250 270 269

33.6 36.2 39.2 39.0

Yieldstrength!.) ksI MPa

158 182 190 190

22.9 26.4 27.5 27.5

EIoogallon(b),

....

3.8 3.5 3.0 3.0

(a) AI 0.2%offset.(b) In 50mrnor2 in. (c)Properties determined on barsmachined from25 mrn(l

in.)diarnseparately castspecimens. (d)Properties determined on barsmachined fromcastings


Magnesium Alloys /421

Fig. 2 Tensile properties as functions of aging time and temperature. Tensile properties of alloy QE22A- T6 as functions of aging time and temperature. Data were obtained from test bars of casting alloy QE22A-T6 machined from 25 mm (1 in.) diam cast specimens


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'iii c

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HK31A-T6: Postweld heat treatments for magnesium alloy castings

Alloy

Welding rod

AZ63A AZ63Aor AZ92A(a)

AZ8IA AZ92Aor AZIOI AZ91C AZ92Aor AZIOI

'Iemper

Desired

before welding

temperafter

F

T4

12hat385±6 °C(725± 10 0F)(b)

F

T6

T4 T40rT6

T4 T6

T4

T4

12hat385 ±6 °C (725± 10 0F)(b),plus5 h at 220 °C (430 oF) 30 min at 385 ± 6 °C (725± 10oF) 30 min at 385 ± 6°C (725± 10 "F), plus5 h at 220°C (430 OF) 30 min at 415±6 °C (775± 1O°F)(c)

T4

T4

30minat415±6 °C (775± 1O°F)(c)

welding

T40rT6

T6

AZ92A

T4 T40rT6

T4 T6

EQ21A

EQ21A

T4orT6

T6

EZ33A

EZ33A

ForT5

T5

HIOIA HK3IA(g) T40rT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T4orT6

T6 T5 T6

QH21A

T6

T4orT6

WE43A WE43A

T40rT6

T6

WE54A WE54A

T40rT6

T6

ZC63A

T40rT6

T6

ForT5 ForT5 ForT5

T5 T5 T5

ZC63A

ZE4IA ZE4IA(g) ZH62A ZH62A(g) ZK5IA ZK5IA(g)

HK31A-T6: Creep properties of sand castings Properties determined using separately cast test bars. 'Thnsile stressresulting intotalextension(a) of TImeunder

30minat415 ±6 °C (775± 1O°F)(c), plus4h at215 °C (420 oF)or 16hat 170°C (340°F) 30minat41O±6 °C (765± 1O°F)(c) 30minat41O±6 °C(765 ± 10°F)(c),plus4h at 260 °C (500 OF) or 5 h at 220°C (430oF) I h at 505 ±6°C (940± 10oF),quench,16h at 205°C (400 OF) 2 h at 345°C (650 °F)(d),and/or5 h at 215 °C(420°F), or24h at 220 °C (430°F) 16h at 205°C (400°F)(e) 16hat 315°C (600 oF) I hat 510 ± 6 °C (950± 10OF), quench, 16h at 205°C (400 "F) I h at 510 ± 6 °C (950± 10 "F), quench, 16h at 205°C (400 "F) I hat 510 ± 6 °C (950± 10 "F), quench, 16h at 205°C (400OF) I hat 510 ± 6 °C (950± 10OF), quench, 16h at 205°C (400oF) I h at 425 ± 6°C (795± 10 "F), quench, 16hat205 °C (400°F) 2 hat330 °C(625 0F)(f) 12hat 250°C (480°F)(f) 2 hat330 °C(625 oF),plus 16hat 175°C(345 oF)

(a) AZ63A rod must be used for welding AZ63A in the F temper because 12 h at 385°C (725 OF) causes germination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZ63A in the T4 orT6 condition unless AZ63Arod is required by specifications.(b)Preheatto 260 °C (500 "F): heat to specifiedtemperatureat no more than 83 0C/h(150 °FIh).(c)Use carbondioxide or sulfur dioxide atmosphere, (d) Heating for 2 h at 345°C (650 "P) results in slight loss of creep strength.(e) Alternativetreatment: I hat315°C(6oo°F), plus 16hat205 °C(4OO°F). (f)Alternative treatment:2 h at 330°C (625 oF),plus 16h at 175°C (345 OF). (g) Or EZ33A

0.1%

0.2%

0.5%

1.0%

ksi

MPa

ksi

MPa

ksI

MPa

ksi

41 I 10 40 100 39 37 1000 At 260 °C (500 oF)

6.0 5.8 5.6 5.4

71 68 66 63

10.3 9.8 9.5 9.1

103 103 103 97

15.0 15.0 15.0 14.0

llO llO llO 109

16.0 16.0 16.0 15.8

I 36 10 30 100 24 21 1000 At 290 °C (550 oF)

5.25 4.4 3.5 3.1

69 59 43 29

10.0 8.6 6.3 4.2

97 88 67 47

14.0 12.7 9.7 6.8

107 100 84 52

15.5 14.4 12.2 7.6

54 31 17

7.8 6.4 4.5 2.5

85 66 43 22

12.3 9.5 6.3 3.2

43 33 20 8

6.2 4.75 2.9 1.1

72 50 24 10

10.4 7.2 3.5 1.4

85 60 28 II

12.3 8.7 4.1 1.55

30 16 7 4

4.4 2.3 1.0 0.63

41 22 9 5

6.0 3.2

load,h

AZ92A

QH21A

Postweld heattreatment

MPa

At 205 °C (400 oF)

I 10 100 1000 At 315 °C (600 oF) I 29 10 22 15 100 1000 6 At 350 °C (600 oF) I 10 100 1000

44

4.15 3.25 2.15 0.94

(a)Total extensionequals initialextension plus creep extension

1.3

0.72

Cast Magnesium Alloys I 443

HZ32A A magnesium-zirconium alloy Chemical Composition. Composition Limits. 1.7 to 2.5 Zn, 2.5 to 4.0 Th, 0.10 rare earths max, 0.50 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), bal Mg Consequence of Exceeding Impurity Limits. More than 0.1% rare earths causes a loss in creep resistance Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4447; (ASTM) Sand castings: B 80; UNS M13320; (Government) Sand castings: QQ-M-56, Mll..-M-46062; (Foreign) Elektron ZTl. (British) BS 2970 MAG8. (German) DIN 17293.5105

Mechanical Properties Tensile Properties. T5 temper, tensile strength is 185 MPa (27 ksi); yield strength is 90 MPa (13 ksi); elongation is 4% in 50 mm (2 in.) Hardness. 55 HB See Table for typical tensile properties of HZ32A-T5 sand castings at elevated temperatures. See Figure for typical stress-strain curves for sand cast test bars

Fabrication Properties A weldable casting alloy, using gas-shielded metal arc process and H232A or EZ33A rod. Rating of process: "Fair." Stress relief is required after welding castings with heavy sections

Characteristics Product Forms. Sand castings Applicationsrrypical Uses. Sand castings used in the artificially aged condition (T5 temper), with moderate strength and an optimum combination of properties for medium- and long-time exposure at temperatures above 260°C (500 OF). Castings are pressure tight, and under long-time exposure can withstand higher stresses and higher temperatures than any other commercially available magnesium alloy

HZ32A-T5. Typical stress-strain curves for separately sand cast test bars

Recommended Heat Treating Practice HZ32A is typically heat treated to T5 temper (artificially aged only). When treated, castings are in F condition (as-fabricated)

Aging. Castings are treated at 315

± 6°C (600 ± 10 "F) for 16 h

For postweld heat treatment, see Table in datasheet for HK3l A

HZ32A·T5: Typical tensile properties of sand castings at elevated temperatures Testing temperature

-c

·F

24 93 150 205 260 315 370

75 200 300 400 500 600 700


Yield strength ksi MPa

200 180 150 115 97 83 69

105 97 83 69 63 55 48

Elongation in SOmm(2in.),%

140 20

24·C

120

15

100

29 26 22 17 14 12 10

15 14 12 10 9 8 7

6 15 23 33 33 28 29

149 ·C

I

'"

c,

-"

260 ·C I 316 ·C

10 tl

'--371 ·C

~

e'"

I

en

tl

~

'0;

c

60

~

I

427 ·C

40

20 H + - - t - - - t - - - t - - - - j

0.4

'0;

204 ·C

:2 80

0.8 Strain, %

1.2

e'" en

~

'0;

c

.HZ32A-T5: Microstructure. Sand castings. Intergranular MgTh compounds: Bunches of acicular compound (dark gray) and small areas of massive M94Th. The precipitate within matrix grains is not Visible. 2% nital, 250x


QE22A A magnesium-zirconium alloy Chemical COlT'lposition. Composition Limits. 2.0 to 3.0 Ag, 1.75 to 2.5 Nd-rich rare earths, 0.4 to 1.0 Zr, 0.1 Cu max, 0.01 Ni max, 0.3 max other (total), bal Mg .

Consequence of Exceeding Impurity Limits. Zr content below 0.5%

ApplicationsfTypical Uses. Sand and permanent mold castings used in the solution-treated and artificially aged condition (T6 temper), with high yield strengths at temperatures up to 200 °C (390 OF). Castings have excellent short-time elevated-temperature mechanical properties and are pressure tight and weldable

may result in somewhat coarser as-cast grains and lower mechanical properties


Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4418C;

Tensile Properties. T6 temper, tensile strength is 260 MPa (38 ksi); yield strength is 195 MPa (28 ksi); elongation is 3% in 50 mm (2 in.)

(ASTM) Sand castings: B 80. Permanent mold castings: B 199. Investment castings: B 403; UNS M18220; (Government) Sand castings: QQ-M-56B. Sand and permanent mold castings: MIL-M-46062B. Permanent mold castings: QQ-M-55; (Foreign) Elektron MSR-B. (British) DTD 5055. (French) MSR-B AECMA MG-C-51. (German) DIN 17293.5164

Characteristics

Hardness. 65 to 85 HB See Tables for typical tensile properties of QE22A sand castings at various temperatures, and for long time creep properties of QE22A sand castings. See Figures for effect of temperature on strength of QE22A sand castings, for effect of temperature on elastic modulus of QE22A sand castings, and for short-time, creep-rupture properties of QE22A sand castings

Product Forms. Sand castings, permanent mold castings, investment

Fabrication Properties

castings

A weldable casting alloy. Welding is with gas-shielded arc process using QE22A rod. Process rating is "Good"

QE22A: Postweld heat treatments for magnesium alloy castings

QE22Ais typically heat treated to T6 temper (solution treating and artificial aging)


Alloy

Weldingrod

A7f>3A

A7f>3Aor AZ92A(a)

AZ8IA AZ91C

AZ92A

AZ92Aor AZIOI AZ92Aor AZIOI

AZ92A

Temper

Desired

beCore welding

temper after

F

T4

12 h a1385±6 °C(725± 10 0F)(b)

F

T6

T4 T4orT6

T4 T6

T4

T4

12 h at 385 ± 6 °C (725 ± 10 0F)(b),plus 5 h al220 °C(430°F) 30 min at 385 ± 6 °C (725 ± 10 oF) 30 min al385 ± 6 °C (725 ± 10°F), plus 5 h al220 °C(430°F) 30minaI415±6°C(775± 1O°F)(c)

T4

T4

30 min al415 ±6 °C (775 ± 10°F)(c)

T40rT6

T6

T4 T4 or T6

T4 T6

30minal415 ±6 °C (775 ± 10°F)(c), plus4h at 215 °C(420°F) or 16halI70°C(34O°F) 30 min a141O±6 °C (765 ± 10°F)(c) 30 min a1410±6 °C (765 ± 10 °F)(c), plus4h al 260 °C (500 oF) or 5 h al220 °C (430 oF) I h at 505 ± 6 °C (940 ± 10 "F), quench, 16 h at 205°C (400 oF) 2h at 345 °C (650 °F)(d), andlor 5 h at 215°C (420 oF), or 24 haI220°C(430°F) 16haI205°C(4OO°F)(e) 16 h al315 °C (600 oF) I hat 510±6°C(950± 1O°F),quench,16hal 205°C(400 oF) I haI510±6°C(950± 10°F),quench,16hat 205°C (400 oF) I haI51O±6°C(950± 10°F),quench, 16hat 205°C(400 oF) I haI51O±6°C(950± 1O°F),quench,16hal 205°C(400 oF) I hat425±6 °C(795 ± 10 oF),quench, 16 h at 205°C (400 oF) 2 h al330 °C (625 0F)(t) 12 h al250 °C (480 0F)(t) 2 h at 330°C (625 oF), plus 16 h at 175°C (345 oF)

welding

EQ2IA

EQ21A

T4 or T6

T6

EZ33A

EZ33A

ForT5

T5

HK3IA HZ32A QE22A

HIOIA(g) HZ32A(g) QE22A

T40rT6 ForT5 T40rT6

T6 T5 T6

QH21A

QH21A

T40rT6

T6

WE43A

WE43A

T40rT6

T6

WE54A

WE54A

T40rT6

T6

ZC63A

ZC63A

T40rT6

T6

ZE41A ZH62A ZK5IA

ZE4IA(g) ZH62A(g) ZK5IA(g)

ForT5 ForT5 ForT5

T5 T5 T5

Solution Heat Treating. QE22A is treated to T6 condition at 525 ± 6 °C Postweldheat treatment

(a) A7f>3A rod must be used for welding AZ63A in the F temper because 12 h at 385°C (725 "F) causes germination in welds made with AZ92A rod: AZ92A rod nonna1ly is used for welding A7f>3A in the T4 orT6 condition unless AZ63A rod is required by specifications. (b) Preheat to 260 °C (500 "F); heal 10specified temperature at no more than 83 0C/h (150 °PIh).(c) Use carbon dioxide or sulfur dioxide atmosphere. (d) Heating for 2 h al345 °C (650 "F) results in slight loss of creep strength. (e)Altemalivetreatment: 1 haI315°C(6OO°F), plus 16hat205°C(4OO°F). (t)A1temative treatment: 2 h at 330 °C (625 OF),plus 16hat 175 °C(345 oF). (g) OrEZ33A

(970 ± 10°F) for 4 to 8 h. Maximum treatment temperature is 540°C (1000 oF) Castings are quenched from solution treating temperature in water heated to 65°C (150 OF), or in some other suitable medium.

Aging after Solution Treatment. Castings are treated at 205 ± 6 °C (400 ± 10 oF) for 8 h Note: After solution treatment and before aging, castings are cooled to room temperature by fast fan cooling, except where otherwise indicated, use carbon dioxide, sulfur dioxide, or 0.5 to 1.5% sulfur hexafluoride in carbon dioxide as protective atmospheres when furnace temperatures exceed 400°C (750 oF) See Table for postweld treatments of castings

QE22A: Long-time creep properties of sand castings TIme under load,h

Thosile stressresulting in creepexlensioD(a) oC 0.05%

MPa

ksi

0.1%

MPa

0.2%

IIsI

MPa

IIsI

0.5% ksi

MPa

1.0% ksi

MPa

At 150°C (300 oF) 10 100 1000

150 21.6 120 17.4 90 13.0

140 20.5 105 15.5

165 23.8 125 18.0

150 21.7

At 205°C (390 oF) 10 100 1000

83 55

12.0 8.0

105 15.0 73 10.6

87 55

12.6 8.0

105

32 16

4.7 2.3

40

15.0

72 10.5

110 16.0 78 11.3

At 250 °C (480 oF) 10 100 1000

32 17

4.7 2.5

41 26

10

(a) Does not include initial extension

6.0 3.7 1.4

22

5.8 3.2

26

3.8

Cast Magnesium Alloys /445

QE22A: Typical tensile properties of sand castings at various temperatures -c

Testinglemperature ·F

20 100 205 300

Tensile strength ksl

Yieldstrength ksl

MPa

68 212 392 572

263 235 193 83

MPa

38.1 34.1 28.0 12.0

208 193 166 69

30.2 28,0 24.0 10

QE22-T6: Effect of temperature on the elastic modulus of sand castings

QE22A-T6: Effect of temperature on the strength of sand castings LIVE GRAPH

o

LIVE GRAPH

Click here to view

Temperature, ·F 200 400

600 300 r---n----,r-----n---,.,..---,

60 40

'8

£

300

~

20

o

-100

"".

6 en :::>

:;

4

'8 E

c: - 2 ,~ c

o

100

200

300

o

~

400

Temperature, ·C

190 t-------"o".r-----==f"'-""""=--j-------I---..::;::::",~

28 21

~

:2, 180 }------+-----t=""""-=-t----1---.:.:::::l 26

~

1;;

~ 110 t------i-----t-----j-------I---=~

25

---l

104

.

~

23

--=::l

22 105

Time,s

QE22A-T6: Microstructure. Sand casting. Massive MggR compound is present at the boundaries of grains of magnesium solid solution, resulting from partial solution and coalescence of the magnesium-didymium eutectic. 100x

LIVE GRAPH

Click here to view

Click here to view

160

24 22

:2

140

~'

.!!

~ 120

~

26 5%

0..

~' .~

24

150·C (300·F)

160 t - - - - - - i - - - - - t - - - - - j - - - - - - - I - - - - - l

LIVE GRAPH 180

29

103

- 8 '[1

'"o

.~

QE22A-T6: Short-time creep-rupture properties of sand castings

-L

600

r---

E

5

10
5000 h), and they are pressure tight and weldable

Mechanical Properties Tensile Properties. T6 temper, tensile strength is 250 MPa (36.3 ksi); yield strength is 162 MPa (23.5 ksi), elongation is 2% See Figure for effect of test temperature on tensile properties. See Table for elevated temperature properties of sand cast specimens

448/ Heat Treater's Guide: Nonferrous AUoys Hardness. 75 to 95 HB Corrosion Resistance. ASlM B 117 salt fog test. 0.1 to 0.2 mg/cm2/day

WE43: Elevated-temperatureraroperties taken from specimens of sand cast 25 mm (1 in.) thick pate 'ThII temperature OF


OC

A weldable casting alloy. Welding is with gas-shielded metal arc process, using WE43 rod

200


250 300

WE43A is typically heat treated to T6 temper (solution treated and artificially aged)

Solution Heat Treating. WE43A is treated at 525 ± 6 °C (970 ± 10 oF) for 4 to 8 h. Maximum treatment temperature is 535°C (995 OF) Castings are quenched from the solution treating temperature in water heated 65°C (150 "F), or in some other suitable medium

150

YOW!lI'smodulus

GPa

10'pst

47 39 36 36

6.8 5.7 5.2 5.2

300 390 480 570

Alloy

1\'Zf)3A

10mper belo", WeldiDgrod weldiDg

AZSIA AZ91C

1\'Zf)3Aor

AZ92Aor AZIOI AZ92Aor AZIOI

WE43: Effect of test temperature on the tensile properties

120

300 (43.5)

--

.i,

250 (36.25)

(29)

~

150 (21.75)

=

~

1"-0...

-I---..

IV

100 (14.5)

-,

\.

205°C

Vi II>

15

100 260°C

~

~

~

'iii c:

'iii c:

10 ~

315°C

~

50

1L-_ _----JL...-_ _---'

0.2

0.4

---'

--1.

0.6

0.8 Strain. %

---l...

1.0

--'0

- L -_ _

1.2

1.4

452/ Heat Treater's Guide: Nonferrous Alloys ZE41 A-T5: Typical tensile properties of sand castingsat elevated temperatures Properties determined on separately cast test bars,

'Il>sling lemperature "C OF 93

ISO 205 260 315

200 300 400 500 600

'Thmlle s1reogth Ml'II ksJ

'ThosiJe yields1rength MPa ksJ 138 130

106

28,0 25,0 20,5 15.4

82

11,9

69

193 172 141

114

88

20,0 18,8 16.5 12,7 10,0

EIougolion in SOmm(2ln.),'"

8 12 31 40 45

ZE63A A magnesium-zirconium casting alloy Chemical Composition. Composition Limits. 5.5 to 6.0 Zn, 2,1 to 3.0 rare earths, 0.40 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other

See Table for postweld heat treatments of castings

(total), bal Mg

Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4425; UNS M16630; (Government) Sand castings: MIL-M-46062B; (Foreign) Elektron ZE63A. (British) DTD 5045

ZE63A: Postweld heat treatments for magnesium alloycastings

Characteristics

Alloy

Product Forms. Sand and investment castings

AZfJ3A AZ63Aor AZ92A(a)

Applicationsf1\tpical Uses. Sand and investment castings used in solution-heat-treated and artificially aged condition (T6 temper). Especially useful in thin-section castings for applications requiring high mechanical strength and freedom from porosity. Special heat treatment in hydrogen is required to develop properties


AZSIA AZ91C

Tensile Properties. T6 temper, tensile strength is 300 MPa (44 ksi);

Weldingrod

AZ92Aor AZI0l AZ92Aor AZLOI

yield strength is 190 MPa (28 ksi); elongation is 10% in 5,65 fA

Hardness. 60 to 85 HB See Tables for typical tensile properties at various temperatures, and for creep properties of ZE63A sand castings

Fabrication Properties A weldable casting alloy. Welding is with gas-shielded arc process, using ZE63A rod, Process rating: "Very good." Welding must precede heat treatment

Recommended Heat Treating Practice Alloy is typically heat treated to T6 temper (solution treating and artificial aging) The alloy must be solution treated in a special hydrogen atmosphere because its mechanical properties are developed through hydriding some of its alloying elements, Hydriding time depends on section thickness; as a guide, 6.4 mm (0.25 in.) sections require about 10 h; 19 mm (0.75 in.) sections require about 72 h. Following heat treatment, the alloy should be quenched in oil, water, spray, or air blast

Solution Heat Treating. ZE63A is treated at 480 ± 6 °C (900 ± 10 oF) for 10 to 72 h. Maximum treatment temperature is 490°C (910 "F) Aging after Solution Treating. Castings are treated at 140 ± 6 °C (285

± 10 "F) for 48 h

'Thmper Desired before lemperafter welding welding F

T4

12 h a1385± 6 °C (725 ± LO 0F)(b)

F

T6

T4 T40rT6

T4 T6

T4

T4

12 hat 385 ±6 °C (725± LO°F)(b),plus 5 h at 220°C (430 oF) 30 minat 385 ±6 °C (725 ± 10°F) 30 min at 385 ± 6°C (725 ± 10 "F), plus 5 h at 220 °C (430 oF) 30 minat 415 ±6 °C(775 ± LO°F)(c)

T4

T4

30 minat415 ±6 °C (775 ± LO°F)(c)

T40rT6

T6

30 min at 415 ±6 °C (775 ± LO°F)(c),plus 4h at215 °C (420 oF) or 16hat 170°C (340°F) 30 min at4LO±6 °C (765 ± LO°F)(c) 30 min at4LO±6 °C (765± LO°F)(c),plus 4 h at 260°C (500 oF) or 5 h at220°C (430°F) Ihat505±6°C(940±10°F),quench,16h at 205°C (400 oF) 2hat345 °C (650 °F)(d), and/or 5 h at215 °C (420 oF), or24 h at 220°C (430 oF) 16haI205°C(400°F)(e) 16hat315 °C (600 oF) 1 hat510±6°C(950±10°F),quench,16h at 205°C (400 oF) 1 hat510±6°C(950± 10°F), quench, 16h at 205°C (400 oF) 1 hat510±6°C(950± LO°F),quench, 16h al205 °C (400 oF) 1 hat5LO±6°C(950± LO°F),quench, 16h at 205°C (400 oF) 1 hat425±6°C(795±LO°F),quench,16h at 205 °C (400°F) 2 h al330 °C (625 0F)(f) 12 h at 250 °C (480°F)(f) 2 h at 330°C (625 oF),plus 16h at 175°C (345 oF)

AZ92A

AZ92A

T4 T40rT6

T4 T6

EQ21A

EQ21A

T40rT6

T6

EZ33A

FZ33A

ForT5

T5

HK3IA HK31A(g) HZ32A HZ32A(g) QE22A QE22A

T4orT6 ForT5 T40rT6

T6 T5 T6

QH21A

QH21A

T40rT6

T6

WE43A

WE43A

T40rT6

T6

WE54A

WE54A

T40rT6

T6

ZC63A

ZC63A

T40rT6

T6

ForT5 ForT5 ForT5

T5 T5 T5

ZE41A ZE41A(g) ZH62A ZH62A(g) ZKSIA ZKSIA(g)

PosIweldheallreotmenl

(a) AZfJ3Arod must be used for welding AZfJ3A in the F temper because 12 h at 385°C (725 "F) causes germination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZfJ3Ain the T4 or T6 condition unless AZfJ3Arod is required by specifications. (b) Preheat to 260 °C (500 "F); heat to specified temperature atno more than 83 0C/h (150 °FIh). (c) Use carbon dioxide or sulfur dioxide atmosphere. (d) Heating for 2 h at 345°C (650 oF) results in slight loss of creep strength. (e) Alternative treatment: I h at 315°C (600 oF), plus 16 h at 205 °C (400°F), (f) Alternative treatment: 2h at 330°C (625 oF), plus 16h at 175°C (345 oF), (g) Or FZ33A


ZE63A: Typical tensile properties of sand castings at various temperatures

ZE63A: Creep properties of sand castings Stress

MPa

ksI

0.15%

0.2%

0.25%

Thoe, h,toreach totaIextension(a) of 0.3% 0.5% 0.75% 1.0% 2.0%

3.0%

4.0%

At 100 °C (212oF) 46 25 6.7 62 9.0 77 11.1 92 13.3 At 150°C (300oF) 39 5.7 70 46 6.7 20 54 7.8 62 9.0 70 10.1 77 11.1

650 120

1440 480 30

530 156 8 5

960 135 IS

20 100 l50

1250 280 1400

912 50 35 12 5

720 335 135 35

840 1200 350 550 90 145

200

920 290

350

'Iensile strength ksi MPa

Thsting temperature

-c

OF

41.9 34.1 27.1 19.0

289 235 187 131

68 212 300 390

'Iensile yield strength MPa

ksI

173 131 111

25.1 19.0 16.1 14.1

97

390

(a)Totalextensionequalsinitialextension pluscreepextension

ZH62A A magnesium-zirconium alloy Chemical Composition. Composition Limits. 5.2 to 6.2 Zn, 1.4 to 2.2 Th, 0.50 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), balMg Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4448; (ASTM) Sand castings: B 80; SAE J465. Former SAE alloy number: 508; UNS M16620; (Government) Sand castings: QQ-M-56, MIL-M-46062; (Foreign) Elektron 1£6. (British) BS 2970 MAG9. (German) DIN 1729 3.5102. (French) AIR 3380 1£6

Characteristics

ZH62A: Postweld heat treatments for magnesium alloy castings

Alloy

Weldingrod


AZ8IA

Product Forms. Sand and permanent mold castings ApplicationslTypical Uses. Sand and permanent mold castings used in artificially aged condition (T5 temper) for room-temperature service. Highest in yield strength of all magnesium

AZ92Aor AZlOl AZ91C AZ92Aor AZlOl

'Iemper before welding

temperafter

F

T4

12hat385 ±6 DC (725± 10°F)(b)

F

T6

T4 T40rT6

T4 T6

T4

T4

12hat385 ±6 DC (725± 100F)(b), plus5 h at220DC (430oF) 30minat385± 6 DC (725± 10oF) 30minat385 ± 6 DC (725± 10oF), plus5 h at220DC (430oF) 30 minat415±6 DC (775± IO°F)(c)

T4

T4

30 minat415±6 DC (775± IO°F)(c)

T40rT6

T6

30minat415±6 DC (775± lO°F)(c),plus4h at215 °C(420°F)orI6hat 170DC (340OF) 30minat410±6 DC (765± lO°F)(c) 30minat410±6 DC (765± lO°F)(c), plus4h at260DC (500oF)or 5 h at220DC (430oF) I h at505± 6 DC (940± 10OF), quench, 16h at205DC (400OF) 2h at345DC (650°F)(d), and/or5h at215DC (420oF), or 24h at220DC (430oF) 16h at205DC (400°F)(e) 16hat315°C(600°F) 1hat510±6°C(950± LO oF),quench, i6h at205DC (400OF) 1hat 510±6°C(950± 10°F),quench,16h at205DC (400OF) 1h at510±6°C(950± 10oF),quench, 16h at205DC (400OF) 1hat510±6°C(950± 10°F),quench,16h at205DC (400OF) 1h at425± 6 DC (795± 10oF),quench, 16h at205DC (400OF) 2hat330°C(625 0F}(f) 12h at250DC (4800F)(f) 2h at330°C (625°F),plus 16hat 175DC (345oF)

Desired

welding

AZ92A

AZ92A

T4 T40rT6

T4 T6

EQ21A

EQ21A

T40rT6

T6

EZ33A

EZ33A

ForTS

T5

HK3IA HK31A(g) HZ32A HZ32A(g) QE22A QE22A

T40rT6 ForTS T40rT6

T6 T5 T6


QH21A

QH21A

T40rT6

T6

A weldable. casting alloy. Welding properties are "poor." Process is gasshielded arc method, using EZ33A or ZH62A rod. Castings should be heat treated after welding

WE43A

WE43A

T40rT6

T6

WE54A

WE54A

T40rT6

T6

ZC63A

ZC63A

T40rT6

T6

ForTS ForTS ForTS

T5 T5 T5

Mechanical Properties Tensile Properties. T5 temper, tensile strength is 240 MPa (35 ksi); yield strength is 150 MPa (22 ksi); elongation is 4% in 50 mm (2 in.) Hardness. 70 HB See Figures for distribution of tensile properties of ZH62A-T5 cast test bars, and for microstructure ofZH62A-T5

Recommended Heat Treating Practice ZH62A is typically heat treated in F condition (as-fabricated) to T5 temper Aging. Alloy is treated at 330 °C (350 ± 10 "F) for 16 h

± 6 °C (625 ± 10 "F) for 2 h, plus 177 ± 6

See Table for postweld heat treatment of ZH62A castings

ZE4IA ZE41A(g) ZH62A ZH62A(g) ZK51A ZK51A(g)

Postweld beattreatment

(a) AZ63Arod must be used for weldingAZ63Ain the F temperbecause12h at 385 DC (725oF) causes genninatlonin welds made with AZ92A rod: AZ92A rod nonna11y is used for welding AZ63AintheT4 orT6 conditionunlessAZ63Arodisrequiredbyspecifications. (b)Preheat to 260 DC (500oF);heattospecifiedtempemtureat nomorethan830C/h(150°FIh).(c)Usecarbondioxide or sulfurdioxideatmosphere. (d) Heatingfor 2 h at 345 DC (650 oF)resultsin slightloss of creep strength. (e)Alternativefreatment: 1hat315 DC (600OF), plus16hat 205DC (400OF). (f)Alternative lreabnent: 2 h at 330DC (625oF),plus 16h at 175DC (350oF).(g)OrEZ33A


ZH62A-T5: Distribution of tensile properties for separately cast test bars of ZH62A-T5

15

~ ~

.-----------------~

49 tests 101-------------.",.----------1

48 tests

50 tests

(;

Q;

-g

51-------

:>

z

o' - - - - ' - - - - = 250 (36)

260 (38)

275

290

(40)

(42)

305 (44)

Tensile strergth, MPa (ksi)

165 (24)

180 (26)

195 (28)

Yield strength, MPa (ksi)

4

6

8

10

Elongation in 50 mm (2 in.), %

ZH62A-T5: Microstructure. ZH62A-T5 sand casting. Characteristic lamellar, or filigree, form of eutectic magnesium-thoriumzinc compound at the boundaries of grains of magnesium solid solution. 2% nltal, 250x

ZK51A A magnesium-zirconium alloy Chemical Composition. Composition Limits. 3.6 to 5.5 Zn, 0.50 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), bal Mg Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4443; (ASTM) Sand castings: B 80; SAE J 465. Former SAE alloy number: 509; UNS M1651O; (Government) Sand castings: QQ-M-56A, MIL-M-46062; (Foreign) Elektron Z5Z. (British) BS 2970 MAG4. (French) AIR 3380 Z5Z

Characteristics Product Forms. Sand castings

Hardness. 62 HB or 72 HRE See Tables for tensile properties of ZK51A-T5 at elevated temperatures, and for creep properties of ZK51A-T5 sand castings See Figure showing microstructure ofZK51A-T5

Fabrication Properties A weldable, casting alloy. Welding properties are poor. Process used: Gasshielded arc method, with E33A or ZH62A rod. Castings should be heat treated after welding

ApplicationslTypical Uses. Sand castings used in artificially aged condition (T5 temper), with high yield strength and good ductility. This alloy is suggested for highly stressed parts that are small or relatively simple in design. Solution treatment is not required

Alloy in F (as-fabricated) condition. is typically heat treated to T5 (artificially aged) temper


Aging. ZK51A-F is treated at 177 ± 6 °C (350 ± 10 "F) for 2 h

Tensile Properties. T5 temper, tensile strength is 205 MPa (30 ksi); yield strength is 140 MPa (20 ksi); elongation is 3.5% in 50 rum (2 in.)

See Table for postweld heat treating of castings


An alternative treatment: 8 h at 220 ± 6°C (425 ± 10 OF)


ZK51A-T5: Creep properties of sand castings

ZK51 A-T5: Typical tensile properties of sand castings at elevated temperatures

Properties determined using separately cast test bars.

Properties determined using separately cast test bars. TIme under

laad,h A195 °C (200 oF) 1 10 100 1000 At 150°C (300 oF) 1 10 100 1000 At 205 °C (400 oF)

0.1% MPa ks!

Tensile stress resulting in totalexteusiontej of 0.2% 0.5% MPa ksl MPa ksi

1.0% MPa ksl

Testing temperature OF °C



275 205 160 115 83 55

180 145 115 90 62 41

Elongation in 50mm(2In.), %

47 46 42 37

6.8 6.6 6.1 5.4

85 83 76 68

12.3 12.0 11.0 9.8

138 20.0 131 19.0 125 18.1 114 16.5

25 95 150 205 260 315

43 43 41 34

6.3 6.2 6.0 5.0

74 71 68 63

10.7 10.3 9.9 9.1

112 105 99 86

ZK51A: Postweld heat treatments for magnesium alloy castings

1 10 100 1000 At 260 °C (500 oF)

38 33 23 14

1 10 100 1000

28 16 7 6

5.5 4.8 3.4 2.1 4.1 2.3 1.0 0.84

67 56 41 23 39 23 12 7

9.7 8.1 6.0 3.3 5.6 3.4 1.8 1.0

104 91 74 37 55 35 21 10

16.3 15.2 14.3 12.5

Alloy

15.1 13.2 10.7 5.4 8.0 5.1 3.0 1.4

75 200 300 400 500 600

Welding rod

AZ63A AZ63Aor AZ92A(a) 66 43 25 12

9.5 6.2 3.6 1.7

(a) ToW extensionequals initialextensionpluscreepextension

ZK51 A: Microstructure. ZK51 A-T5 sand castings. Fine, degenerate eutectic magnesium-zinc compound at the grain boundaries. The grains of magnesium solid solution are essentially homogeneous.250x

AZ81A AZ92Aor AZ101 AZ91C AZ92Aor AZ101

40 30 23 17 12 8

8 12 14 17 16 16

Temper before welding

lemperafter welding

F

T4

12hat385±6°C (725± 10 0F)(b)

F

T6

T4 T40rT6

T4 T6

T4

T4

12h at385 ± 6 °C (725± 100F)(b), plus5 h at 220 °C (430oF) 30 min at385 ± 6 °C (725± 10 "F) 30 min ill385± 6 °C(725± 10 "F), plus5 h at220°C (430oF) 30 min at415±6 °C (775± 1O°F)(c)

T4

T4

30 min at415±6 °C(775± 1O°F)(c)

T40rT6

T6

30 min at415 ±6 °C(775± 1O°F)(c), plus4h at215 °C (420oF)or 16hat170°C (340°F) 30 minat41O±6 °C(765± 10 °F)(c) 30 min at41O±6 °C(765 ± 1O°F)(c),plus4h at 260°C (500oF)or 5 hat 220°C (430oF) I h at 505 ± 6 °C (940± 10"F), quench. 16h at 205 °C (400oF) 2 h at 345 °C (650°F)(d),andlor5 h at 215°C (420 oF),or24h at 220°C (430oF) 16h at 205°C (400°F)(e) 16hat315°C(600°F) I hat51O±6°C(950±1O°F),quench,16h at 205 °C (400oF) 1 hat51O±6 °C(950± IOOF),quench, 16h at 205 °C (400OF) 1 hat51O±6 °C(950± 1O°F),quench,16h at 205 °C (400oF) 1 hat51O±6 °C(950± 10°F),quench, 16h at 205°C (400oF) I 11 at425 ±6°C(795 ± 10°F),quench.16h at 205 °C (400oF) 2 h at 330 °C (6250F)(f) 12h at 250 °C (480°F)(O 2hat330 °C(625 oF),plus 16hat175 °C(345 oF)

Desired

AZ92A

AZ92A

T4 T40rT6

T4 T6

EQ21A

EQ21A

T40rT6

T6

EZ33A

EZ33A

ForT5

T5

HK31A HK31A(g) T40rT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T40rT6

T6 T5 T6

QH21A

QH21A

T40rT6

T6

WE43A WE43A

T40rT6

T6

WE54A

WE54A

T40rT6

T6

ZC63A

ZC63A

T40rT6

T6

ForT5 ForT5 ForT5

T5 T5 T5

ZE4IA ZE41A(g) ZH62A ZH62A(g) ZK51A ZK51A(g)

26 21 17 13 9 6

Postweld heat treatment

(a) AZ63Arod must beused for weldingAZ63A in the F temperbecause 12 h at 385°C (725 "P) causes germination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZ63A in theT4 orT6 conditionunlessAZ63Arod is requiredby specifications. (b)Preheatto 260 °C (500 "F); heat tospecifiedtemperatureat no more than83 0C/h(150 °FIh). (c)Usecarbondioxide or sulfur dioxide atmosphere.(d) Heating for 2 h at 345 °C (650 oF)results in slight loss of creep strength.(e)Alternativetreatment:I hat315°C(600°F), plus 16hat205°C(4OO°F). (l)A1temative treatment:2 h at 330 °C (625 oF),plus 16h at 175°C (345oF).(g) Or EZ33A


ZK61A A magnesium-zirconium alloy Chemical Composition. Composition Limits. 5.5 to 6.5 Zn, 0.6 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), bal Mg Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 80; SAE J465. Former SAE alloy number: 513; UNS M1661O; (Government) Sand castings: QQ-M-56B

Characteristics

ZK61A: Postweld heat treatments for magnesium alloy castings Temper Alloy

Welding rod


Product Forms. Sand castings Applicationsfrypical Uses. Simple, highly stressed castings of uniform cross section. High in cost. Intricate castings subject to microporosity and cracking due to shrinkage. Not readily welded. Sometimes used in the artificially aged condition (f5 temper) but usually in the solution-heattreated and artificially aged condition (f6 temper) to develop properties fully

Desired

temper after welding welding before

AZ8IA AZ92Aor AZIOI AZ91C AZ92Aor AZIOI

F

T4

l2hat385±6°C (725± 100F)(b)

F

T6

T4 T40rT6

T4 T6

T4

T4

12hat385 ±6°C (725± 100F)(b), plus5 h at 220°C (430°F) 30 minat385±6°C(725± 10°F) 30 minat 385± 6 °C(725± 10"F), plus5 h at 220°C(430°F) 30minat415±6 °C(775± 1O°F)(c)

T4

T4

30 minat415±6 °C(775± 1O°F)(c)

T40rT6

T6

30 minat415±6 °C(775 ± 1O°F)(c),plus4h at215 °C (420oF)or 16hat 170°C(340°F) 30 minat41O±6 °C(765± 1O°F)(c) 30minat41O±6 °C(765± 1O°F)(c),plus4h at 260°C (500oF)or 5 hat 220°C (430°F) I h at505± 6 °C (940± 10"F), quench,16h at 205°C (400oF) 2h at345 °C(650°F)(d),and/or5 hat215 °C (420°F),or24 h at 220°C (430oF) 16h at205°C (400°F)(e) l6hat315°C(600°F) I h at51O±6°C(950± 1O°F),quench,16h at 205°C (400oF) I h at51O±6°C(950± 1O°F),quench, 16h at205°C(4OO°F) I h at51O±6°C(950± 1O°F),quench, 16h at 205°C (400oF) I hat51O±6°C(950± 1O°F),quench, 16h at 205°C (400oF) I hat425 ±6°C (795± 1O°F),quench, 16h at 205°C (400oF) 2 h at330°C (6250F)(t) 12hat250°C(480°F)(t) 2hat330°C(625 OF), plus 16hat 175°C (345oF)

AZ92A

AZ92A

T4 T4orT6

T4 T6

EQ21A

EQ21A

T40rT6

T6

EZ33A

EZ33A

ForT5

T5

Castable alloy with limited weldability, Thorium or rare earth additions decrease porosity and improve weldability

HK3IA HK3IA(g) T40rT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T40rT6

T6 T5 T6


QH21A

QH21A

T40rT6

T6

Alloy (in F, as-fabricated condition) is typically heat treated to T4 (solution treated) and T6 (solution treated and artificially aged) tempers

WE43A WE43A

T40rT6

T6

WE54A WE54A

T40rT6

T6

ZC63A

T4orT6

T6

ForT5 ForT5 ForT5

T5 T5 T5

Mechanical Properties Tensile Properties. T6 temper, tensile strength is 310 MPa (45 ksi); yield strength is 195 MPa (28 ksi); elongation is in 50 mm (2 in.), 10%


Aging. Castings are treated to T5 temper at 150 ± 6 °C (300 ± 10 "F) for 48h Solution Heat Treating. Castings are treated at 500 ± 6 °C (930 ± 10 "F) for 2 h. Maximum treatment temperature is 502°C (935 "F) Alternative treatment: 10 h at 480 ± 6 °C (900 ± 10 "F)

Note: After solution treating and before aging, castings are cooled to room temperature by fast fan cooling, except where otherwise indicated. Use carbon dioxide, sulfur, dioxide, or 0.5 to 1.5% sulfur hexafluoride in carbon dioxide as practice atmospheres if furnace temperatures exceed 400 °C (750 OF)

ZC63A

ZE4IA ZE4IA(g) ZH62A ZH62A(g) ZK5IA ZK5IA(g)

Postweld heattreatmenl

(a) AZ63Arod must be used for weldingAZ63Ain the F temperbecause 12h at 385°C (725 "F) causes germination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZ63AintheT4 orT6 conditionunlessAZ63Arodisrequiredbyspecifications. (b)Preheatto260 °C(500 "F); heattospecified temperature atnomorethan83°CIb(150°FIb). (c)Usecarbondioxide or sulfur dioxideatmosphere. (d) Heatingfor 2 h at 345°C (650 "F) results in slight lossof creep strength.(e)Altemativetreatment: I h at 315°C (600 "F), plus 16hat 205 °C (400 "F), (fj Altemativetreatment: 2 h at330°C (625 "F), plus 16h at 175°C (345 "F), (g) OrEZ33A

Artificial Aging. Castings are treated at 130 ± 6 °C (265 ± 10 "F) for 48 h See Tabie for postweld heat treatments

ZK61A: Microstructure. Segregation of zinc-zirconium-iron compound in a ZK61A-F sand casting. This compound and Zr 2Zn a form under similar conditions; the two can be distinguished by etching with 10% HF,which attacks Zr ~na but not zinc-zirconiumiron. 250x

Titanium Alloys

Heat Treating Titanium Alloys Titanium and titanium alloys are heat treated in order to: • Reduce residual stresses developed during fabrication (stress relieving) • Produce an optimum combination of ductility, machinability, and dimensional and structural stability (annealing)

• Increase strength (solution treating and aging) • Optimize special properties such as fracture toughness, fatigue strength, and high-temperature creep strength

Alloy Types and Response to Heat Treatment The response of titanium and titanium alloys to heat treatment depends on the composition of the metal and the effects of alloying elements on the a-p crystal transformation of titanium. In addition, not all heat treating cycles are applicable to all titanium alloys, because the various alloys are designed for different purposes. Alloys Ti-5AI-2Sn-2Zr-4Mo-4Cr (commonly called Ti-17) and Ti-6AI-2Sn-4Zr-6Mo are designed for strength in heavy sections; Ti-6AI-2Sn-4Zr-2Mo and Ti-6AI-5Zr-0.5Mo-O.2Si, for creep resistance; Ti-6AI-2Nb-lTa-lMo and Ti-6AI-4V-ELI. for resistance to stress corrosion in aqueous salt solutions and for high fracture toughness; Ti-5AI-2.5Sn and Ti-2.5Cu, for weldability; and Ti-6AI-6V-2Sn, Ti-6Al-4V, and Ti-lOV-2Fe-3Al, for high strength at low-to-moderate temperatures. Alloy Types. Based on the types and amounts of alloying elements they contain, titanium alloys are classified as a, near-a, a-p, or p alloys. The response of these alloy types to heat treatment is briefly described below. Alpha and near-alpha titanium alloys can be stress relieved and annealed, but high strength cannot be developed in these alloys by any type of heat treatment (such as aging after a solution beta treatment and quenching). Near-a alloys are alloys with predominantly a stabilizer, plus limited p stabilizers (normally, 2% or less). The commercial p alloys are, in reality, metastable p alloys. When these alloys are exposed to selected elevated temperatures, the retained p

Table 1 Summary of heat treatments for a-p Ti alloys Heallrealmenl designation Duplexanneal

Heallrealment cycle

Solutiontreatat 50-75°C (90-135oF) belowTp(a),air cool and age for 2-8h at 540-675°C (1000-1250 oF) Solutiontrealandage Solutiontreatat-4O °C (70 oF) below Tp,waterquench(b)and age for 2-8h a1535-675 °C (995-1250oF) Betaanneal Solutiontreat ai-15°C (30 "F) above Tp,aircoolandstabilizeat 650-760°C(1200-1400 oF) for 2 h Betaquench Solutiontreatat-15°C (30 oF) above Tp,waterquenchand temperat 650-760°C(1200-1400oF) for2 h Recrysta1lization anneal 925°C (1700"F) for4 h, cool at 50 °CJh(90°FIb)to 760°C (1400"F), air cool Millanneal lX-~ hot workplus annealat705 °C (1300 oF) for30 min to several hoursand air cool

Microstructure Primarya, plus

Widmanstlinen lX-~ regions

Primary a, plustempered lX' or a P-lX mixture Widmanstatten lX-~ colony microstructure Temperedri Equiaxed n wilh ~ at grainboundary triplepoints Incompletely recrystallized lX wilha smallvolumefraction ofsmall~ particles

(a)Tpis Ihe ~ transustemperature fortheparticularalloyinquestion.(b)In moreheavily~-stabilized alloyssuchasTi-6AI-2Sn-4Zr-6MoorTi-6AI-6V-2Sn, solutiontreatment isfollowed by air cooling. Subsequentagingcausesprecipitation of lX phaseto forman lX-~ mixture

phase decomposes and strengthening occurs. For p alloys. stress-relieving and aging treatments can be combined, and annealing and solution treating may be identical operations. Alpha-beta alloys are two-phase alloys and, as the name suggests, comprise both a and p phases at room temperature. These are the most common and the most versatile of the three types of titanium alloys. Phase compositions, sizes, and distributions can be manipulated by heat treatment within certain limits to .enhance a specific property or to attain a range of strength levels. A summary of typical heat treatments for a-/3 titanium alloys is given in Table 1. Beta transus temperatures for various commercial titanium alloys are listed in Table 2. When the heat treatment involves heating near the p transus, the transus temperature of each heat in a lot must be accurately determined.

Table 2 Beta transformation temperatures of titanium alloys Betatramus

Alloy Commercially pureTi,0.25 02 max Commercially pure'Il,0.40 Oz max a or near-a aUoys Ti-5Al-2.5Sn Ti-8Al-IMo-tV Ti-2.5Cu(lMl230) TJ-6Al-2Sn-4Zr-2Mo Ti-6Al-5Zr-0.5Mo-O.2Si (lMl685) Ti-5.5Al-3.5Sn-3Zr-lNb-0.3Mo-0.3Si (lMl829) TJ-5.8A1-4Sn-3.5Zr-0.7Nb-0.5Mo-0.3Si (IMI 834) Ti-6Al-2Cb-lTa-0.8Mo Ti-0.3Mo-O.8Ni rncode12) a-Jlalloys Ti-6Al-4V Ti-6Al-7Nb (IMI 367) Ti-6Al-6V-2Sn (Co + Fe) Ti-3Al-2.5V Ti-6A1-2Sn-4Zr-6Mo TJ-4Al-4Mo-2Sn-0.5Si (lMl550) TJ-4A1-4M0-4Sn-0.5Si (lMl551) Ti-5Al-2Sn-2Zr-4M0-4Cr(1i-17) Ti-7A1-4Mo TJ-6A1-2Sn-2Zr-2Mo-2Cr-0.25Si Ti-8Mn JI or near-jl alloys TJ-13V-llCr-3A1 Ti-lI.5Mo-6Zr-4.5Sn (BetaIll) Ti-3A1-8V-6Cr-4Zr-4Mo (BetaC) Ti-l0V-2Fe-3A1 Ti-I5V-3A1-3Cr-3Sn (a)±20. (b)±30. {c)±35.(d)±50

"C,±15

°F,:lZ5

910 945

1675 1735

1050 1040 895 995 1020 1015 1045 1015 880

1925 1900 1645 1820 1870 1860 1915 1860 1615

l000(a) 1010 945 935 940 975 1050 900 1000 970 800(c)

183O(b) 1850 1735 1715 1720 1785 1920 1650 1840 1780 1475(d)

720 760 795 805 760

1330 1400 1460 1480 1400

+

+


Stress Relieving

Table 3 Recommended stress-relief treatments for titanium and titanium alloys Parts can be cooled from stress relief by either air cooling or slow cooling.

Titanium and titanium alloys can be stress relieved without adversely affecting strength or ductility. Table 3 presents combinations of time and temperature that are used for stress relieving titanium and titanium alloys. The rate of coolingfrom the stress-relievingtemperatureis not critical. Uniformity of cooling is critical, however, particularly in the temperature range from 480 to 315°C (900 to 600 "F), Oil or water quenching should not be used to acceleratecooling because this can induce residual stresses by unequal cooling. Furnace or air cooling is acceptable. Weldments. The temperatures used for stressrelievingcomplex weldments of a or a-~ alloys should be near the high ends of the ranges given in Table3.

Annealing The annealing of titanium and titanium alloys serves primarily to increase fracture toughness, ductility at room temperature, dimensional and thermalstability, and creepresistance.Many titaniumalloys are placed in service in the annealed state. Because improvement in one or more properties is generallyobtained at the expense of some other property, the annealing cycle should be selected according to the objective of the treatment. Common annealing treatments are: • • • •

Mill annealing Duplex annealing Recrystallizationannealing Beta annealing

Recommended annealing treatments for several alloys are given in Table 4. Either air or furnace cooling may be used, but the two methods may result in different levelsof tensile properties. If distortion is a problem, the cooling rate should be uniform down to 315°C (600 "F), It may be difficult to prevent distortion of close-tolerance thinsections duringannealing.

'ThmperalW'e

Alloy

Commercially pure11 (all grades) a or near-a titanium alloys 11-5AI-2.5Sn 11-8AI-IMo-IV 11-2.5Cu (IMl230) 11-6A1-2Sn-4ZJ"-2Mo 11-6AI-5ZJ"-0.5Mo-O.2Si (IMl685) 11-5.5Al:3.5Sn-3ZJ"-1Nb-0.3Mo-O.3Si (IMl829) Ti-5.8AI-4Sn-3.5ZJ"-0.7Nb-0.5Mo-O.3Si (IMl834) Ti-6Al-2Cb-lTh-0.8Mo Ti-O.3Mo-O.8Ni (11Code 12) a-p titanium alloys Ti-6AI-4V 11-6AI-7Nb (IMl367) 11-6Al-6V-2Sn (Cu+ Fe) Ti-3AI-2.5V 11-6AI-2Sn-4ZJ"-6Mo 11-4AI-4Mo-2Sn-O.5Si (IMl550) 11-4AI-4M0-4Sn-0.5Si (IMl551) 11-5Al-2Sn-4Mo-2ZJ"-4Cr (11-17) 11-7AI-4Mo 11-6A1-2Sn-2Zr-2Mo-2Cr-0.25Si Ti-8Mn Por near-jl titanium alloys 11-13V-11Cr-3Al 11-l1.5Mo-6ZJ"-4.5Sn (BetaTIl) 11-3AI-8V-6Cr-4ZJ"-4Mo (BetaC) 11-IOV-2Fe-3Al 11-15V-3Al-3Cr-3Sn

Time,

-c

OF

h

480-595

900-1100

0.25-4

540-650 595-705 400-600 595-705 530-570 610-640 625-750 595-650 480-595

1000-1200 1100-1300 750-1110 1100-1300 980-1050 1130-1190 1160-1380 1100-1200 900-1100

0.25-4 0.25-4 0.5-24 0.25-4 24-48 1-3 1-3 0.25-2 0.25-4

480-650 500-600 480-650 540-650 595-705 600-700 600-700 480-650 480-705 480-650 480-595

900-1200 930-1110 900-1200 1000-1200 llOO-1300 1ll0-129O 1ll0-129O 900-1200 900-1300 900-1200 900-1100

1-4 1-4 1-4 0.5-2 0.25-4 2-4 2-4 1-4 1-8 1-4 0.25-2

705-730 720-730 705-760 675-705 790-815

1300-1350 0.0833-0.25 1325-1350 0.0833-0.25 1300-1400 0.167-0.5 1250-1300 0.5-2 1450-1500 0.0833-0.25

Table 4 Recommended annealing treatments for titanium and titanium alloys Temperature Alloy

Commercially pure11(all grades) a or near-a titanium alloys Ti-5AI-2.5Sn 11-8AI-IMo-IV 11-2.5Cu (IMl230) Ti-6AI-2Sn-4ZJ"-2Mo 11-6AI-5ZJ"-0.5Mo-O.2Si (IMl685) Ti-5.5AI-3.5Sn-3ZJ"-1Nb-0.3Mo-O.3Si (IMl829) 11-5.8AI-4Sn-3.5ZJ"-O.7Nb-O.5Mo-O.3Si (IMl834) 11-6A1-2Cb-lTa-0.8Mo a-p titanium alloys 11-6AI-4V 11-6A1-7Nb (IMl367) 11-6A1-6V-2Sn (Cu+ Fe) 11-3AI-2.SV 11-6AI-2Sn-4ZJ"-6Mo 11-4AI-4Mo-2Sn-O.SSi (IMlSSO) 11-4AI-4M0-4Sn-O.5Si (IMlSSl) 11-SAI-2Sn-4Mo-2Zr-4Cr (11-17) 11-7Al-4Mo 11-6AI-2Sn-2ZJ"-2Mo-2Cr-0.25Si 11-8Mn Por near-jl titanium alloys 11-13V-11Cr-3AI 11-11.5Mo-6ZJ"-4.SSn (BetaTIl) 11-3AI-8V-6Cr-4ZJ"-4Mo (BetaC) 11-10V-2Fe-3Al 11-1SV-3Al-3Cr-3Sn

°C

OF

Time, h

Cooling method

650-760

1200-1400

0.10-2

Air

720-845 790(a) 780-800 9OO(b) (c) (c)

1325-1550 1450(a) 1450-1470 165O(b) (c) (c)

0.167-4 1-8 0.5-1 0.5-1

Air Air or fumace Air Air

(c)

(c)

790-900

1450-1650

1-4

Air

705-790 700 70S-81S 6S0-76O (c) (c) (c) (c) 70S-79O 70S-81S 6S0-76O

1300-1450 1300 1300-1S00 1200-1400 (c) (c) (c) (c) 1300-14S0 1300-1S00 1200-1400

1-4 1-2 0.7S-4 0.S-2

Air or furnace Air Air or furnace Air

1-8 1-2 O.S-1

Air Air (d)

70S-79O 690-760 790-81S (c) 790-81S

1300-14S0 0.167-1 Air or water 127S-14OO 0.167-1 Air or water 14S0-1S00 0.25-1 Air or water (c) 14S0-1S00 0.0833-0.25 Air

(a) Forsheetand plate,followby 0.25 h at 790 °C (l4S0°F), then air cool.(b) Forsheet,followby 0.25 h at790 °C (14S0"F), thenaircool (plus2 h atS9S°C, or 1100OF, then air cool,in certainapplications). Forplate.followby 8 h atS9S °C (1100"F), then air cool.(c)Not normallysuppliedor usedin annealedcondition(seeThble3). (d)Furnaceor slowcoolto S40°C(1000oF),then air cool

Titanium and Titanium Alloys /461

Solution Treating and Aging A wide range of strength levels can be obtained in a-~ or ~ alloys by solution treating and aging. With the exception of the unique Ti-2.5Cu alloy (which relies on strengthening from the classic age-hardening reaction of Ti2CU precipitation similar to the formation of Guinier-Preston zones in aluminum alloys), the origin of heat-treatingresponsesoftitanium alloys lies in the instability of the high-temperature ~ phase at lower temperatures. Heating an a-~ alloy to the solution-treating temperature producesa higher ratio of ~ phase.This partitioningof phases ismaintained by quenching; on subsequentaging, decompositionof the unstable ~ phase occurs, providing high strength. Commercial ~ alloys, generally supplied in the solution-treatedcondition, need only be aged. Time/temperaturecombinationsfor solution treating are given in Table 5. A load may be charged directly into a furnace operating at the solutiontreating temperature. Although preheating is not essential, it may be used to minimize the distortion of complex parts. Solution treating of titanium alloys generally involves heating to temperatureseither slightly above or slightly below the ~ transus temperature. The solution-treating temperature selected depends on the alloy type and practical considerations briefly described below. Beta alloys are normally obtained from producers in the solutiontreatedcondition. If reheating is required, soak timesshouldbe only as long as necessary to obtain complete solutioning. Solution-treating temperatures for ~ alloys are above the ~ transus; because no second phase is present, grain growth can proceed rapidly. Alpha-Beta Alloys. Selection of a solution-treatment temperature for a-~ alloys is based on the combination of mechanical properties desired after aging. A change in the solution-treating temperature of a-~ alloys

alters the amounts of ~ phase and consequently changes the response to aging (see Table 6). Near-Alpha Alloys. Like the a-~ alloys, solution treatment above the ~ transus provides optimum creep resistance at the expense of reduced ductility and fatigue strength. To obtain the best combination of creep strength and fatigue strength, the solution temperaturemust be very close to but below the transus, so that only 10 to 15%of primary (untransformed) a remains. Quenching. The rate of cooling from the solution-treatingtemperature has an important effect on strength. If the rate is too low, appreciable diffusion may occur during cooling, and decomposition of the altered ~ phase during aging may not provide effective strengthening. For alloys relatively high in ~-stabilizer content and for products of small section size, air or fan cooling may be adequate; such slow cooling, where allowed by specified mechanical properties, is preferred because it minimizes distortion. Beta alloys are generally air quenched from the solution-treatingtemperature. Water, a 5% brine, or caustic soda solution is preferred for quenching a-~ alloys because these quenchants provide the cooling rates necessary to prevent the decomposition of the ~ phase obtained by solution treating, in order to provide maximumresponse to aging.The need forrapid quenching is further emphasized by short quench-delay requirements. Depending on the mass of the sections being heat treated, some a-~ alloys can tolerate a maximumdelay of? s, whereasmore highly ~-stabilized alloys can tolerate quench delay timesof up to 20 s. The effectof quenchdelays on Ti-6AI-4V bar is shown in Fig. 1.

Table 5 Recommended solution-treating and aging (stabilizing) treatments for titanium alloys Alloy

a ornear-a alloys TI-8Al-IMo-IV TI-2.5Cu (lMJ230) TI-6Al-2Sn-4Zr-2Mo TI-6Al-5Zr-O.5Mo-O.2Si (lMJ685) TI-5.5Al-3.5Sn-3Zr-INb-O.3Mo-0.3Si (lMJ 829) TI-5.8Al-4Sn-3.5Zr-O.7Nb-O.5Mo-O.3Si (lMJ 834) a-ll alloys TI-6AI-4V TI-6Al-6V-2Sn (Cu + Fe) TI-6Al-2Sn-4Zr-6Mo TI-4AI-4Mo-2Sn-O.5Si (lMJ 550) TI-4Al-4Mo-4Sn-O.5Si (lMJ 551) TI-5Al-2Sn-2Zr-4Mo-4Cr TI-6Al-2Sn-2Zr-2Mo-2Cr-025Si Pornear-p alloys TI-13V-IICr-3Al TI·II.5Mo-6Zr-4.5Sn (Beta III) TI-3Al-8V-6Cr-4M0-4Zr(Beta C) TI-IOV-2Fe-3Al TI-15V-3Al-3Cr-3Sn

Solution temperature OF -c

Solution tlme,h

CooUngrate

°C

OF

tlme,h

565-595 390-410 465-485 595 540-560 615-635 625

1050-1100 735-770 870-905 1100 1005-1040 1140-1175 1155

8-24 (step I) 8(step 2) 8 24 2 2

900-1100 1300-1400 900-1100 1075-1125 915-950 915-950 1075-1125 900-1100

4-8 2-4 4-8 4-8 24 24 4-8 4-8

800-900 900-1100 850-1000 925-975 950-1100

4-100 8-32 8-24 8 8-24

Aging temperature

980-1010{a) 795-815

1800-1850(a) 1465-1495

I 0.5-1

Oil or water Air orwater

955-980 1040-1060 1040·1060 1020(b)

1750-1800 1905-1940 1905-1940 1870(b)

I 0.5-1 0.5-1 2

Air

955-970(c)(d) 955-970 885-910 845-890 890-910 890-910 845-870 870-925

1750-1775(c)(d) 1750-1775 1625-1675 1550-1650 1635-1670 1635-1670 1550-1600 1600-1700

I I I I 0.5-1 0.5-1 I I

Water Water Water Air Air Air Water

480-595 705·760 480-595 580-605 490-510 490-510 580-605 480-595

775-800 690·790 815-925 760-780 790-815

1425-1475 1275·1450 1500-1700 1400-1435 1450-1500

0.25-1 0.125-1 I I 0.25

Air orwater Air orwater Water Water Air

425-480 480·595 455-540 495-525 510-595

Oil Air oroil

Oil

Air

Aging

(a) For certainproducts. use solution temperature of890°C (1650 "F) for Ih.then air cool orfaster. (b) Temperature should be selected from transus approachcurve togive desired a content. (c) For thin plate orsheet. solution temperature can be used down to890 °C (1650 "F) for 6to 30min; then water quench. (d) This treatment isused to develop maximum tensile properties in this alloy


Table 6 Variation oftensile properties ofTi-6AI-4V bar stock with solution-treating temperature Solution-treating lempemture

"C

845 870 900

925 940

OF

1550 1600 1650 1700 1725

Room-lempemlnre tensile propel1ies(a) Thnsile strength YIeld strength(b) MPa ksi ksi MPa

1025 1060 1095 1Il0 1140

149 154 159 161 165

980 985 995 1000 1055

142 143 144 145 153

Elongation

in4D, %

18 17 16 16 16

Fig. 1 Effects of quench delay on tensile properties of li-6AI-4V bar. Bar, 13 mm (0.5 in.) in diameter, was solution treated 1 h at 955°C (1750 OF), water quenched, aged 6 h at 480°C (900 OF), and air cooled

LIVE GRAPH

.

Q.


1400

:

w~

m~

~

g, l!! t----r-'----:7'f-----=-.......c-t-----;..-:::l30 m 40

0.05

0.15

0.1

I

0>

wi

~

E -

~ C

600

.>

C

~ '0

I

300K 3)( 10-4/s

800 -

c:

100

!

I

54o11----~+_--~'c7''F__---____l80 ~ III

High Purity Titanium I 465

LIVE GRAPH

LIVE GRAPH

~

~I i

20 ;;:

100

140 160 180 Hardness, HV (5 kg load)

40

~

i

i

60


200

220

(b)

LIVE GRAPH

60 0

A

Click here to view ~ 500

::
c Ql 50 -v; 40

~ .~

~

30 ~

0 D

Of-

20

Ternary Binary

•

1o

II

o

120

100

~

::J

o


200

220

(e)

Pure Titanium: Effect of impurities on Vickers hardness. Titanium ingots having dilute carbon, nitrogen and oxygen impurity levels were cold rolled to 1 mm (0.040 in.) thick sheet, mechanically cleaned, 1000 DC vacuum annealed, cold rolled to 0.5 mm (0.020 in.), and finally were annealed for 1 h at 700 DC in vacuum. Treatment gave an average equiaxed grain size of 0.020 to 0.025 mm

s

240

~ 220

,~gen

~

e 200 Q;

./

.0

E 180 c

~

:l

~

c

/

160

'E

~ 140 ~

Ql

tj 120

s

100

r

o

g

V 0.1

.......

-

v ......
-

- T 12

80 -300

-150

0 150 Temperature, °C

300

§ 0

>-

450

Ti-8ll : Typical heat treatments Heat ......tment Stressrelief Millannealing Solutiontreating Aging Duplexannealfor thicksections(a) 1ststage stabilization Duplexannealforsheet lst stage (mill anneal) 2nd stage

Thmperature

Cooling method

Time. h

OC

of

600-700 760-790 980-1010 565-595

1ll0-1290 1400-1455 1795-1850 1050-1100

900-1010 600-745

1650-1850 1110-1375

760-790 600-790

1400-1455 1ll0-1455

0.25-4 Air orslowcool 1-8 Air orfurnacecool 1 Oilor waterquench Air coot

Ti-8AI-l Mo-l V: Environments known to produce

Organic compounds Methylalcohol(anhydrous)

Air orfurnace cool Aircool

Methylchloroform Ethylalcohol(anhydrous) Ethyleneglycol Trichloroelbylene Trichlorofluoroethane Salts Hotsalt:chlorideandother halidesalts/residues SeawaterlNaOsolution

(a)Treatmentfor goodcreep strength

Ti-8AI-l Mo-l V: Effect of hydrogen content on hardness Pro<essingfcondlllon Asreceived, millannealed As received, millannealed Annealedat 870°C (1600oF) in vacuum,8 h, furnacecooled Annealed at 870°C (1600"P) in vacuum, 8 h, furnacecooled

Thlckn... Hydrogen, Hardness, mm In. ppm HRC 17 17 17 17

0.673 0.673 0.673 0.673

(twice) Annealedat 870°C (1600"F), hydrogenated, 8 h, furnacecooled 17 0.673 Annealed at 1065°C (1950"F) in vacuum, 4 h, furnacecooled 15 0.597

Thmperature, °c

Medium

Air cool Air cool

1-8

7

36 36 33 33

39 21

33 -30

14-21 14-21 5

see

Environment

TI-6Al-4V, grade2TI, Grade4TI, TI-4Al-3Mo-1V,Ti-3Al-8V-6Cr-4Zr-4Mo (BetaC), TI-13V-11Cr-3Al, TI-5Al-2.5Sn 370 TI-6Al-4V,TI-5Al-2.5Sn, TI-13V-11Cr-3Al TI-5Al-2.5Sn RT NoalloysotherthanTI-8Al-1Mo-1V RT 370,620, 815 TI-5Al-2.5Sn TI-5Al-2.5Sn, TI-6Al-4V,TI-13V-llCr-3Al 788 lIT

230-430

370 340

Mostcommercialalloysexcept grades1,2,7,11,12, and9 Unalloyed Ti (with oxygencontent>0.3%) Ti-2.5AI-lMo-llSn-5Zr-n.2Si(IMl-679), Ti-3Al-11Cr-13V,TI-5AI-2.5Sn, TI-8Mn, n6Al-4V,TI-6Al-6V-2Sn, Ti-6Al-2Nb-ITa, TI-4Al-3Mo-1V,TI-6AI-2Sn-4Zr-6Mo TI-13V-l1Cr-3Al TI-6Al-4V

RT 288 35,340 300-500

Ti-5Al-2.5Sn, Ti-11.5Mo-6Zr-4.5Sn (Betaill) No alloysotherthanTI-8Al-1Mo-1V Ti-5Al-2.5Sn No alloysotherthanTi-8Al-1Mo-1V

RT

Mercury(liquid) Ag-5Al-2.5Mn (bracealloys) Miscellaneous Distilledwater Chlorinegas 10%HCI Moltenchloridelbromide salts

Alloywas received in the hot rolled and mill annealedcondition.Chemicalcompositionwas 7.92 wt%Al,0.03wt%C,0.15wt%Fe,H asindicated,0.98 wt%Mo,0.01wt%N, 0.11wt% 0, and 1.01 wt%V

Othertitanium alloys withknown suoceptibillty

Ti-8ll : Turning parameters for annealed material Thol IIllIlerial

Rough turning Brazedcarbide(C2) Throwawaycarbide(C2) High-speedsteel (M, T5,T15) Finish turning Brazedcarbide(C3,C2) Throwawaycarbide(C3,C2) High-speed steel (M3, T5,TI5)

Thol

Depthorcnt

Feed

Speed

geometry(a)

mm

In.

mmfrev

In./rev

mfmin

.rm

A,E,F A,E,F B,D,E,F

2.5-6.35 2.5-6.35 2.5-6.35

0.10-0.25 0.10-0.25 0.10-0.25

0.25-0.38 0.25-0.38 0.25-0.38

0.010-0.015 0.010-0.015 0.010-0.015

21-42 46-60 73-22O(b)

70-140 150-200 240-72O(b)

A,C A,C C,E,F

0.635-2.5 0.635-2.5 0.635-2.5

0.025-n.10 0.025-0.10 0.025-n.1O

0.13-0.25 0.13-0.25 0.13-0.25

0.005-0.010 0.005-0.010 0.005-0.010

27-47 50-56 73-183(b)

90-155 165-185 240-6OO(b)

(a) See accompanyingtablefor toolgeometrycodes. (b) Thesehigh speedswould be loweredif slowerfeedsand deepercuts aremade withhigh-speedsteelcutters

Alpha and Near-Alpha Alloys I 501

Ti-8AI-1Mo-1V: Effect of solution temperature on hardness. Alloy was supplied in the form of 64 mm (2.5 in.) square bar stock. Chemical composition was 7.6 wt% AI, 0.022 wt% C, 0.06 wt% Fe, 0.005 wt% H, 1.1 wt% Mo, 0.008 wt% N, 0.09 wt% 0, and 1.1 wt% V. Hardness measurements were made on 13 mm (0.5 ln.) cubes in the plane normal to the rolling direction. Cube surfaces had been ground at least 1.3 mm (0.050 ln.) and mechanically polished. Hardness was also determined for Jominy bar that had been sectioned along the center line and surface ground. Specimens were solution treated in air for 1 h, followed by brine quench

Solution temperature, OF 1600 1800 2000 1400

1200

150

45 ST 6 STA (24 h, 80°C) .. Percent bet o

40 0

125 100

0::

:c

gOJ 35

75

c

Bela transus

"E til :c 30

0>'!. '"5 >

~

Ol

50

0

25 25


0

600

1000 800 Solution temperature, "C

1200


Ti-811: Forging pressure. Forging pressures at 10% upset reduction with 4340 steel presented for comparison

----

700 600

100

til

'(ij

60

0.300

~

~

c

'0,

40

Ti-8AI-1Mo-1va~

(; 200

u,

:>

0

'iii

g

"iii

0.5 E Q)

0

o

15

0-

0 0

o

0.5

1

1.5

2

-0.5

2.5

Concentration of HCI, 0/0

-1 0.01

0.1

1

10 /1 Alcm

, Annealing temperature, OF

800

900 1000 1100 1200 1300 1400 1500 1600

30

25

oa: J:

• • • • • • • • • •

gf 20 Q) c

"E

Spedlkallon

Deslgnatbn

UNS

Desaiplion

Fe

AI

R56210

H

6

Mo

N

0

Nb

0.8-8

Other

1h

balTt

2

USA AWSAS.16-70 MILT-9046J

ERI'i-6Al-2Cb-lTa-IMo COdeA-3

WeldFillMet ShStrpPItAnn

5.5-6.5 5.5-6.5

0.15 0.25

0.005 0.0125

0.5-1.5 0.5-1

0.012 0.03

0.1 0.1

1.5-2.5 1.5-2.5

0.15-1.5 0.5-1.5

CO.04;balTt CO.05; Of 0.4; balTi

Ti-6AI-2Nb-1Ta-O.8Mo: Commercial compositions Composition, WI% Speclllcalion

Deslgnalion

Deseription

AI

Fe

H

Mo

N

Nb

0

5.5-6.5

0.25

0.0125

0.5-1

0,03

1.5-2.5

0.1

Other

USA RMI Timet

RMI6AI-2Cb-lTa-lMo TIMEfAL6-2-1

0.5-1.5

C 0.05; bal Tt

Ti-6211: Summary of heat treatment and microstructure of the Widmanstatten-type structure

Ti-6211: Corrosion rates in specific media Concenlration,

'IOmperalure,

Corrosion rate,

Heattreatment

Medlum

%

"C

nnnJyr

Widmanst§tten (1+ ~ Widmanst§llen ex+~ Widmansl§llen ex + ~ Coarse,blockyprimaryex in fine Widmanst§nen ex + ~ matrix Fine Widmansllltten ex+~ WidmanstlUten ex+ ~

Ferricchloride Hydrochloric acid

10 0.5 10.0 5

Boiling Boiling Boiling Boiling

nil 0.020 1.07 0.051

Fine Widmansllltten ex+ ~ (same as No.5 exceptfor prior ~ grainsize) Widmansl§nen ex+ P(same asNo.6 exceptforprior ~ grain size) Temperedmartensite

Ti-6211: Forging process temperatures

I. 2. 3. 4.

As-received Anneal:950°C,6h,AC+700°C,2h,AC Anneal:900°C,6h,AC+700°C,2h,AC Anneal:IOW°C, Ih;FCin 10°Csteps, holding 4hateachstept0980°C, AC+ 700°C, 2h,AC 5. Anneal: 1050°C,2h,AC+700°C,2h,AC 6. Anneal:1050°C, 2h, AC + 950°C, 6h, AC+700°C,2h,AC 7. Anneal: 1050°C,4Omin,AC+700°C,2h,AC 8. Anneal: 1050°C,4Omin,AC+950°C,6h, AC+700°C,2h,AC 9. Anneal:10S00C,40 min,WQ + 800°C, I h, WQ + 500 °C,2h,AC 10. Anneal;1050°C,4Omin,WQ+700°C,2h, AC 11. Anneal:800°C, 40 min, WQ+500°C,2h,AC 12. Anneal:9S00C,40 min,WQ+500°C,2h,AC

Mkrostruclure

Temperedmartensite Widmanst§tten ex+ P Widmanst§nen ex+ ~ + martensite

Hydrochloricacid +0.1 % FeCI)

MelIIltemperalure Process

Conventional forging Betaforging

°C

OF

940-995 1040-1120

1725-1825 1895-2050


Ti-6211: Effect of heat treatment on impact strength of 25 mm (1 in.) rolled plate Thst

Condition

dlm:lion

As-rolled

L T L T L T L T L T L T L T L T

uannealed: 870°C (1600 oF), 1h,AC u-p annealed,aircooled:990°C (1815"F), 1h,AC u-p solutiontreated,quenched:990°C (1815 oF), 1 h, WQ u-p solutiontreated,aged:990 °C (1815 oF), 1 h, WQ + 595°C (1100oF), 2 h,AC

Pannealed, aircooJed:1035°C (1900oF), 1 h,AC Psolutiontreated,quenched:1035°C (1900 oF), 1 h, WQ Psolutiontreated,aged: 1035°C (1900oF), I h, WQ + 595°C (1100oF), 2 h, AC

lOmBeyield

Chorpy V-nolch impacl

strength at RT MPa ksI

toughness at -62 °C(-80 OF) J /l·1hf

701.9 723.9 683.9 740.5 673.6 717.0 697.7 747.4 744.6 819.8 699.1 712.9 759.8 744.6 807.4 801.1

101.8 105.0 99.2 107.4 97.7 104.0 101.2 108.4 108.0 118.9 101.4 103.4 110.2 108.0 117.1 116.2

Drop weighl tear energy al 0 (32 oF)

-c

23.5 23.0 29.2 32.2 32.5 28.2 27.8 32.2 25.5 29.0 33.0 28.2 30.5 26.8 24.0 23.2

31.8 31.2 39.6 43.6 44.0 38.2 37.7 43.6 34.5 39.3 44.7 38.2 41.3 36.3 32.5 31.4

J

/l·1hf

3072 2909 3312 3858 3471 3072 3471 3312 2828 2583 3549 2665 3072 3072 2336 2909

2266(a) 2146(a) 2442 2846 2560 2266 2560 2443 2086 1905 2618 1966 2266 2266 1723 2146

Note: All valuesaverageof two testsexceptdrop weight tear values,which areindividualresults.(a)In a separatestudy on thissameheal, thefollowingresults wereobtained:3232 J (2384 ft ·Ibf) and 2418J (1784 ft ·Ibf) T direction

Ti-6211: Effect of oxygen content on ~ transus temperature. The ~ transus temperature increases in a linear manner with oxygen content at an approximate rate of 13 "O (23 OF) per 0.1 wt% oxygen. Sample ~-annealed: heated to 1065 °e (1950°F) for 2 h in a vacuum, followed by a moderate cooling rate in a helium atmosphere.

LIVE GRAPH

Click here to view

Ti-6211: Effect of oxygen content on grain size. Grain size is reduced by a factor of three when the oxygen content is increased from 0.075 to 0.290%. The grain size is more sensitive to oxygen content in low levels up to about 0.2% oxygen, beyond which further addition of oxygen does not significantly alter the ~ grain size. Sample ~-annealed: heated to 1065 "O (1950 OF) for 2 h in a vacuum, followed bv a moderate coolino rata in ~ hAliJ 1m ",t.....",,-I- , re.

1000

3. 5

1820

2. 8

E E

l!f

2. 1

'iii

c

'ii! Cl

~

o

1.4


\

\ ~

\

~I

-...a..;.;

120

Ullimate tensile strength

.I

Il

~"'i I

60o As rolled 950

140 ~ £ 130

.

~

.!-

70 Oa-

975

Ti-6211: Tensile strengths vs. solution treatment. Quenched plate, 25 mm (1 ln.) plate solution treated, 1 h, water quenched as 25 by 150 by 150 mm (1 by 6 by 6 in.) specimen blanks. Each data point is an average of two tests.

2000

I

I

/'

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o ~

VI

~ 380

'E lU

I

370

31. 5

uI VI

Q)

I

uI

c: ~ 30.0

.:

/

./

28.5

I

o

V

I

I

360

-:

LIVE GRAPH

33. 0

/'

27. 0

0.1 0.2 Oxygen content, wt%

o

0.3

0.1 0.2 Oxygen content, wt%

0.3

Ti-6211:Tensile strengths vs. solution treatment. Air-cooled plate. Solutiontreated tensile properties of plate specimens air cooled or furnacecooled fromvarioussolutiontemperatures. Specimens were25 mm (1 in.) plate solutiontreated 1 h, as 25 by 150 by 150 mm (1 by 6 by 6 in.) specimenblanks.Each data point is the averageof two tests.

LIVE GRAPH

1600

1700

1800

1100

1000 lU

n,

950

:2 sO 0, 900 c

I

j

I

i

I

i I

i

i

i

--

0 .

--

-

---

0

.. 'l

I I

I

-•

I

~

(jj 85 0

--

800

.....lZ...

~

:

900

•

o

1000

950

r

o

•

Tensile yield strength 0

I-

:

850

•

0

-+

!

700 As rolled

..


~

..... f:

0

750

i I

-.e

0-

L.

~

2200

2100

i

I I

1050

Click here to view

Solution temperature, of 1900 2000

'I

I

1050 1100 Solution temperature.

2300

L AC from solution temperature AC from solution temperature FC from solution temperature to 1650 °c (900 of). AC FC from solution temperature to 1650 °c (900 of), AC T AC from solution temperature AC from solution temperature FC from solution temperature to 1650 °c (900 of), AC FC from solution temperature to 1650 °c (900 of). AC I

-1 50 _ - 140 -

-----= 1 -1 20 -

I

I

I

I

1150

1200

1250

-1 10

1300

°c

Ti-6211: Effect of quench delay on tensile properties. 25 mm (1 in.) plate; 1095 °C (2000 OF), 1 h, delay (in air), water quenchedas 25 by 150 by 150 mm (1 by 6 by 6 in.) specimen blanks.Eachdata point is an averageof two tests. 1100

0

"-

•

..

1000 lU

c, :2 900 sO

rnc ~

(jj

:

. "

40

L L T T

150

Ultimate tensile strength ~

:

800

==: 700

Tensile yield strength

S

LIVE GRAPH

30

140

~

130

]1 sO

rn

120 ~ (jj 110

c Q)

~ 20 Q) n,

0

.. • ..

L L T T

--

10 100

600 60 80 70 Quench delay, s

•

~

~

..•-


90 50

°

Elongation in 25 mm (1 In.)


Reduction of area

90

100

0 40

50

60

70 80 Quench delay. s

90

100


Ti-6211: Effect of aging temperature on tensile strengths. 25 mm (1 in.) plate; 1095 °C (2000 OF), 1 h, 70 s delay (in air), water quench + age, 2 h, air cooled 25 by 150 by 150 mm (1 by 6 by 6 in.) specimen blanks. Each point is an average of two tests.

Ti-6211: Effect of annealing temperature on yield strength. Effect of annealing temperature on yield strength and ductility of WidmansUitten a + p material, annealed 40 min, water quenched + 500°C (930 OF), 2 h, AC.

LIVE GRAPH

Temperature, of

800

1000

1000

1200

1400

1600 0

LIVE GRAPH

900

a~

0, c

. ~: °

0

:2

800

iii 700

•

o

0

120

"

~

.>
Mo N

3.5-4.5

0.04

Other

Sn

Zr

1.5-2.5

1.5-2.5

00.08-0.13; bal Ti

TI-17 TIMETAL17

TIMEf

Ti-17: Typical STA tensile properties 'IenslJe yield

24 93 205 315 370

Ultimate tensile strength MPa ksl

strength

'Iemperature "C OF 75 200 400 600

700

MPa

ksi

1035-1075 930-1000 795-860 760-825 700-760

150-170 135-145 115-125 110-120 100-110

1105-1240 1035-1105 930-1000 930-1000 860-930

Ti-17: Typical STA notch tensile properties 'Iemperature OF °C 24 93 205 315 370

75 200 400 600 700

Notched tensile strength(a) MPa ksi 1380-1515 1450-1515 1380-1450 1275-1345 1275-1345

200-220 210-220 200-210 185-195 185-195

Reduction Elongation, '1>

160-180 150-160 135-145 135-145 125-135

Stress

OF

MPa

ksi

205

400

315

600

425

805

480 510

900

999 982 979 965 948 896 793 482 482

145 142.5 142 140 137.5 130 115 70 70

950

20-45

30-45 30-45 30-45 30-45

Ti-17: Typical STA creep properties 'Iemperature OF °C NTSjUTS 1.3 1.4 1.4 1.4 1.4

Ti-17:Creep-rupture of a-p processed forging Temperature

'1>

8-15 8-15 8-15 8-15 8-15

205

400

315

600

425

805

Stress

(a)K,=4.0

°C

orarea,

MPa

ksi

nmeto O.2'1>,h

793 814 690 724 745 241 310 345 414

115 118 100 105 108 35 45 50 60

2200 400

1000 500 125 150 75 75 30

Ti-17: Recommended heat treatments nme, h 0,01 >671.9 793.6 0.1 >670.5 >721.5 8 >140 -16

Note: Spoolforgingswereheattreatedat 845·C (1555 "P) for 4 h, aircooled,then800 °C (1470"F) for 4 h, furnaceair cooled,and aged at 620 °C (l150 "F) for 8 h, air cooled

Treatment Double solution treat and age STI ST2

Age Solution treat and age ST Age Stress relief Beforemachining Other

Tempemture OF °C

Duration,

Cooling

h

method

860 800 620

1580 1470 1150

2 4

WQ

AC

8

AC

800 635

1470 1175

4 8

AC AC

550 480-650

1020 900-1200

4 1-4

AC AC or slowcool


Ti·17: Effectof agingtemperature on tensileyieldstrength. Alpha-beta processed disks heat treated at 855°C (1570 OF), 4 h, AC, 800 °C (1470 OF), 4 h, water quench (WO) or oil quench (00) or fan air cool (FAC)

LIVE GRAPH

Click here to view

Aging temperature, of 1200

1100

1300 180

1250

170 1150 160

lU

00;

a-

.>l

::i:. 1050 s:

wa/oa

0> c ~

1ii u

iii

150

950

>= 850

~ c

----"""-25 mm -50mm ----+--125-175 mm FAC -025mm -050mm -tJ.125-175mm

~

140

~ iii

>= 130 120

750

110

550

650 Aging temperature,

600

n-17: Effectof solution temperatures on tensile strengths. Alpha-beta processed disk forgings heat treated at 855°C (1570 OF), 4 h, AC + solution treated, 4 h, WO, 620°C (1150 °F), 8 h, AC

700

750

"c

Ti·17: Effectof solution treatmenton aged strength. Solution treated at indicated temperature for 4 h, WO, and aged at 635°C (1175 OF) for8 h


LIVE GRAPH Click here to view 1300 1400

1600 200

lU

a-

180

::i:

~ 1200

::i: 1300

~ N

~

.c

170

~

~

I

1600 200 190 ~

I

:

'i

180

0>

170 ~

e

1ii

1ii

u

iJ 1100

160

1100

~ s:

0> c

Ii)

Ii)

Beta-processed Alpha·bela processed

II

0 ;; 1200

0>

c

I

°

lU

a-

190

1300

Solution temperature, OF 1500 1400

1300 1400

160 iii

>=

>= 150

150

1000

1000

700

750 800 850 Solution temperature, °c

900

700

Temperature, of 1480 1500 1520 1540 1560 1580 1600 1620 1640 80

in.) thick compact tension specimen from 457 mm (18 in.) diam x 50 mm (2 in.) thick disk forging. Indicated solution temperature plus 785°C (1445 OF), 4 h, WO + 620°C (1150 OF), 8 h

70

-;,60/-----f----+-----cf--+------1 ";(9~ 50 -;; l3m '" m c c .£:

.£:

~ ~~ B 401-------+-----,.+----+----::1 B ~

~

~

1124 MPa (163 ksi) YS

~a

~

I

~

MPa (165 ksl)'--'YS 20L..-_1137 _~ 800

825

900

Ti·17: Effectof solution temperature ontoughness. 25 mm (1

E ~ a::i:

~


~

---'-

--'20

875

900


Alpha-Seta Alloys /517

Ti-17:Continuous coolingtransformation cliagram. Solution treated at 930°C (1700 OF) for 30 min


100 0

I

I

j

- - -

JI

-

800

o °

PI

II

I !

600

~

-

-

_ ,_ p_tr~nsu~

-

~.

~Fine

G:ain boundary

'. i a layer

'\..

'-:-

Ol

c.

E 400

-

-

{ IX

L "Start

1

I

- z

.:

-

-

- : "- 1 500

Widmanstiilten IX plates LL

phase -

:

:

Finish

-

°PI ":'1 000 ::> ~

Ol

c.

E

I

~

II

,,

i I I

200 ~.

,

I

Undercooled p phase

o

I

1

10

~

a+ pmixture

i

I I

, I

~

i

- 500

I !

I

Time, s

Ti-17: Isothermal transformation diagram. Solution treated at 930°C (1700 OF)


1000

I I

Start Finish

i

LL

°ai -1000 :;

~

I

Ol

c.

I Undercooled p phase

E

400-,

~

I ! 01.-..

1

I'--

'--

--'-

I

--'-

--'

10 Time, S

Ti-6AI-2Sn-4Zr-6Mo Common Name. Ti-6246 UNS Number. R56260 Chemical Composition. Ti-6246 is a solid-solution-strengthened alloy that responds to heat treatment as a result of the beta-stabilizing effect of

its 6% molybdenum content. Silicon additions (0.08 wt%) improve creep resistance. As for all alpha-beta alloys, excessive amounts of aluminum, oxygen, and nitrogen can decrease ductility and fracture toughness. See Tables for specifications/compositions and for commercial compositions


Characteristics Phases and Structures. Special ingot melting practices must be employed, particularly during final melting, to minimize microsegregation of the beta-stabilizing element, molybdenum, which could result in "beta flecks." Forging and heat treating practices require special controls to minimize beta flecks, which could result in microregions of high strength and low fracture toughness. Beta flecks are less of a problem for Ti-6246 than for Ti-17. The microstructure of Ti-6246 is typically equiaxed primary a in a transformed ~ matrix; this can vary, depending on processing and heat treatment history. A microstructure with an optimum combination of strength, ductility, and toughness contains about 10% equiaxed a (primary a) plus a transformed ~ matrix with relatively coarse secondary a and aged ~

Beta Transus. 935°C (1715 oF). The 1020 °C transus in figures on p 520 is

final microstructure of forgings is developed by thermomechanical processing in forging manufacture tailored to achieve specific microstructural and mechanical-property objectives. Thermomechanical processes use combinations of subtransus and/or supratransus forging followed by subtransus thermal treatments to fulfill critical mechanical-property criteria. Final thermal treatments for forgings include two-step practices of solution treatments followed by quenching and aging. Solution treatment is subtransus at 870 to 900°C (1600 to 1650 OF), followed by water or oil quenching and/or fan air cooling for thin sections. Aging is conducted at 535 to 620 °C (995 to 1150 OF). Subtransus thermomechanical processes (forging and thermal treatment) for forgings achieve equiaxed a (20 to 40%) in transformed ~ matrix microstructures that enhance strength, ductility, and particularly low-cycle fatigue properties. Supratransus thermomechanical processes (~ forging followed by subtransus thermal treatments) achieve transformed, Widmanstatten a microstructures that enhance creep and fracture-related properties such as fatigue-crack growth resistance

suspect

Product Forms. Primarily billet and bars for forging stock Applications. Ti-6246 is designed to combine the long-term, elevatedtemperature strength properties of TI-6Al-2Sn4Zr-2Mo-0.08Si (fi-6242S) . with much-improved short-term strength properties of a fully hardened alpha-beta alloy. lt is used for forgings in intermediate-temperature sections of gas turbine engines, particularly in compressor disks and fan blades. This alloy is used at lower temperatures than Ti-6242S, but should be considered for long-term load-carrying applications at temperatures up to 400°C (750 OF) and short-term load-carrying applications at temperatures up to 540 °C (1000 oF)

General Corrosion Properties. Molybdenum addition greater than 4 wt% improve the corrosion resistance of titanium alloys in reducing media, and this effect is evidenced by the general corrosion of Ti-6246 in HCI solutions. The increase in reducing environment resistance is achieved, however, at the expense of oxidizing environment resistance. Because Ti-6246 is less resistant to oxidizing media than CP Ti, it is expected that pitting resistance would likewise suffer. This is indeed the situation observed for repassivation potentials, which represent conservative measures of anodic pitting below which pitting cannot be sustained

Crevice Corrosion. In contrast to the anodic breakdown associated with pitting, crevice corrosion is usually the result of acidification in the crevice region by oxidant depletion. Therefore, Ti-6246 should be very resistant to crevice corrosion due to its reducing environment resistance from molybdenum

Ti-6246: Forging process temperatures Process

Conventional forging Belaforging

-c

Metal temperature

845-915 955-1010

1555-1680 1750-1850

Forming. Ti-6246 may be formed similar to Ti-6AI-4V alloy, although the reported bend properties are somewhat inferior. The room-temperature minimum bend radius, for Ti-6246 ranges between 3.5 and 6.0 for solution treated or duplex annealed sheet. Hot forming and sizing of sheet may be accomplished in the 595 to 705°C (1100 to 1300 "F) range using the usual titanium forming techniques. If hot forming is performed in the 595 to 705 °C (1100 to 1300 OF) range, stress relief annealing would not ordinarily be required; limited cold forming is possible. Depending on property requirements, stress relief in the 595 to 705°C (1100 to 1300 "F) range is satisfactory Superplasticity. Flow stresses and strain rate sensitivity of a + ~ preforms indicate superplastic behavior (High-Temperature Deformation of Ti-6246, Titanium, Science and Technology, Vol2, DGM, 1985, P 745-752) Machinability. Machining practice for Ti-6246 in the as-forged condition is similar to that of annealed Ti-6AI4V and Ti-6AI-6V-2Sn. In the solution treated and aged condition, practice is similar to that of Ti-6Al-6V-2Sn in same type heat treated condition

Stress Corrosion Cracking. Resistance to stress-corrosion cracking in salt water is reported to be better after ~ forging than a-~ forging (WymanGordon Co., Project EM-06-1, Dec 1968). Duplex annealing also improves cracking resistance in salt water

Welding. Ti-6246 is very difficult to weld. Recommended filler metal is

Mechanical Properties. Typical room temperature hardness in the solution treated and aged condition (STA) ranges from 36 to 42 HRC. As-forged hardness is reported to be about 33 to 38 HRC. Adjoining Figures show the effects of treatments such as solution treating, aging, duplex annealing (DA) and triplex annealing (fA) on properties such as hardness and tensile strength


Fabrication Properties Forging. Ti-6246 can be fabricated into all forging product types, although closed die forgings and rings predominate. Ti-6246 is commercially fabricated on all types of forging equipment. Thrbine engine disks are frequently produced using hot die or isothermal forging techniques, resulting in near-net closed die forgings with reduced final machining. Ti-6246 is a reasonably forgeable alloy with unit pressures (flow stresses), forgeability, and crack sensitivity similar to the a-~ alloy Ti-6AI-4V. The

the same as the base alloy

Ti-6246 may be used in a number of heat treated conditions, which can be categorized as anneals, or solution treatment and aging (see Tables). As previously described, optimum combinations of strength, ductility, and toughness in forgings are obtained by superimposing the heat treatments on processing schedules, which result in a microstructure having about 10 vol% equiaxed primary a and a relatively coarse transformed ~ matrix. If relatively high fabrication temperatures are used, solution heat treatment on the low side of the range can be used. If moderate a-~ fabrication temperatures are used, double solution treatments-the first at a high temperature, the second at about 845°C (1555 °F)-should result in the desirable structure. Adjoining Tables and Figures provide information on such topics as typical heat treatment conditions, annealing temperatures, solution treatment conditions, hardenability, and effect of aging on transverse temperature properties of sheet.

Alpha-Beta Alloys /519

Ti 6246: Specifications and compositions Composition, wi % Specilkation

Deslgnation

UNS USA AMS4981B MlLF-83142A MlLF-83142A MlLT-9047G

R56260

Description

Fe

AI

H

Mo

6

Compll Comp11 Ti-6AI-2Sn-4Zr-6Mo

BarWrrFrgBil FrgAnn

FrglIT BarBUDA

N

Zr

2

4

1.75-2.25 1.75-2.25 1.75-2.25 1.75-2.25

3.5-4.5 3.6-4.4 3.6-4.4 3.6-4.4

6

5.5-6.5 5.5-6.5 5.5-6.5 5.5-6.5

5.5-6.5 5.5-6.5 5.5-6.5 5.5-6.5

0.15 0.15 0.15 0.15

Other

Sn

0

balTi C 0.04;OTO.4;YO.005; balTi CO.04;balTi CO.04;balTi CO.04;OTO.4;YO.005;balTi

0.15 0.15 0.15 0.15

0.0125 0.0125 0.0125 0.0125

AI

Fe

H

Mo

N

0

Sn

Zr

0.04 0.04 0.04 0.04

Ti 6246: Commercial compositions Designation

Description

KS6-2-4-6

BarFrgSTA

5.5-6.5

0.15

0.0125

5.5-6.5

0.04

0.15

1.75-2.25

3.5-4.5

balTi

Ti-6Al-2Sn-4Zr-6Mo

Bar

5.5-6.5

0.15 max

0.0125

5.5-6.5

0.04

0.15

1.8-2.2

3.6-4.4

CO.l max; balTi

RMI

Ti-6246 6Al-2Sn-4Zr-6Mo

BarBilS'D\

5.5-6.5

0.15

0.0125

5.5-6.5

0.04

0.15

1.75-2.25

3.5-4.5

CO.04;baITi

ThI.AlIVac Timet

TlMEfAL6-2-4-6

DA

5.5-6.5

0.15 max

0.0125 max

5.5-6.5

0.04 max

0.15 max

1.75-2.25

3.5-4.5

CO.04max;balTi

Specilkation Japan Kobe USA Astra Howmet MartinMar Oremet

Ti-6246: Rockwell hardness of different forging and treatment conditions

Ti-6246: Typical heat treatment conditions

Forging conditions

Heattreatmenl

treatment

IX-~ forge(Pt- 100of), AC + finish (~tl- 25 °f),AC IX-~ forge(Pt- 100of), AC + finish

885°C (1625of), I h, AC + 595°C (1100oF),8 h,AC 885°C (1625oF),I h, AC+ 705°C (1300oF),1 h, AC 885°C (1625of), I h, AC+ 595°C (l1OO°f),AC

(~I -

100°f),AC ~ forge (~, + 75 of), AC

39.3 38.4

MP.

ksi

MP.

ksi

%

10 to 20% primaryIX + STA(a) 10 to 20% primaryIX + STOA(b)

1118 1021 1152 1070 1049

162 148 167 155 152

1214

176 158 180 166 174

13 16 14 14 6.5

40 to 50%primaryIX + STA(a) 40 to 50%primaryIX + STOA(b) ~ forged+ STA(c)

1090

1242 1145 1201

Reduellon orarea, %

37 42 42 41 13

Ti-6246: Solution treatment conditions Thmperature Common Sheet Forgings

·C 870 870 845-900

·F 1600 1600 1555-1650

Duralion, b Up to I 0.25 Uptol

595-705 815-930 580-605 >650

1100-1300 1500-1700 1080-1120 >1200

'lime, b

Cooling

0.25-4 1 4-8

Air or slow cool Wateror oil quench AC

method

Ti-6246: Fracture toughness of forgings

(a) STA= 885°C (1625 of), I h, aircool + 595°C (1100 "F), 8 h, air cool. (b) STOA= 885°C (1625 "F), I h, air cool + 705°C (1300 "F), I h, air cool. (c) STA=985 °C(l805 "F), (Pt-15 "C), air cool +595 °C(l1OO°F},8h, air cool

Product

OF

(a)Seeseparatetablefor specifictemperaturesby productform.(b) The mostcommonlyusedaging temperatureis 595°C (1100oF)

Ultim.tetensile Elongation, strengtb

Condiuon

Stressrelief Solutiontrealing(a) Aging(b) Overaging

OC

39.9

Ti-6246: Typical variations in tensile properties with heat treatment/condition Thnsileyield strengtb

ThmperalUre

Heat

Hardness,HRC

Other

Cooling metbod WQ or OQ Quench(a) WQorOQ

(a) Solution treatmentof sheet may be followedby a stabilizationexposure of 0.25 h at 720 to 730 °C (1325 to 1345 oF)withan air cool priortoaging. Sheetmay beage hardenedto optimumproperties in as little as 2hat595 °C (1100 of) (air cooled)

ThnsUe yield strengtb Condition

MP.

ksI

IX+~forged

1116

IX+~forged+S'D\(a)

+STA(a) (10%primarya)

(50%primaryIX) IX + ~ forged+ anneaIed(b) (50%primaryIX) ~ forged+ STA(a)

UItbnate lensile streogtb

Elongation,

Kr
MPa'liii'ksI'1iii"

MP.

ksi

%

162

1213

176

13

34

31

1150

166

1240

180

14

26

23

1061

154

1130

164

13

26

23

1047

152

1199

174

7

57

52

(a) 885 °C(l625 OF), 1 h,AC+595 °C (1100oF),AC. (b) 705 °C(13OO°F),I h,AC

Ti-6246: Fracture toughness of STA forgings: two forging conditions and three specimen locations Fracture toughne.. (KI,) for material:

Specimen location Centertangential Outsidetangential Centerdiametral

IX+ 6 fO~ at 8BO ·C (1620 oF) MP. m ksi'liii" 28.28 24.47 26.49

25.74 22.27 24.11

IIfO~II0I0 OC (1850 .F) MPa ksI~ 21.81

19.85

21.45

19.52

Nole: Klcvalues determined with precracked three-pointnotched bend specimens.Heat treatment was at 870°C (1600 of) for 1 h, waterquench, then at 595 ·C (1100oF)for 8 h, air cool

520 I Heat Treater's Guide: Nonferrous Alloys Ti-6246: Annealing treatments Temperature

-c

'fiealment Solutionannea1 (SA) Duplexanneal Firsl stage (SA) Second stage (age) Triplexannea1 SA stage First age(a) Second age(a)

Ti-6246: Effect of aging on transverse tensile properties of sheet Cooling of

method

815-930

1500-1700

AC

815-930 540-730

1500-1700 1000-1345

AC AC

815-925 540-730(a) 540-730(a)

1500-1695 l000-1345(a) l000-I345(a)

AC AC AC

Tempemture

AgInglrealmenl(a) TIme,h

1 16 1 2 16 1 16 1 16

540

1000

595

1100

650

1200

705

1300

TYS

UTS

OF

°C

MPa 1648 1579 1489 1517 1461 1406 1296 1255 1158

Elongation,

ksi

MPa

ksI

....

239 229 216 220 212 204 188 182 168

1455 1420 1379 1386 1365 1337 1261 1220 1110

211 206 200 201 198 194 183 177 161

3 4 6 3 6 7 9 6 12

(a) Firstaginghigherthanthesecond

.

(a)Solutiontreatmentfor0.25 h, 870°C (1600 "F), air cooled

Ti-6246: Continuous cooling transformation and aging dlagram

Ti·6246: Continuous cooling transformation diagram

LIVE GRAPH

LIVE GRAPH


Solution annealed at 900°C for 20 min

1000

~

E Q)

I--

1000

c:=

800

M.

-,1500 ~

~

ll!

-11000 ~ E Q)

600

Q)

c.

E Q)

I--

a

-'1500 ~

a

i!!

.a

I--

~1000 ~

E Q)

400

a

200

0

i!!

:>

~

M,

~500

200

-,2000

13, = 1020 °C- ~

~ 800

i!!

I

400

Solution annealed at 1050 °C at 20 min

-i2000

13, = 1020 °C

i!! :>

600 ~ Q) c.


I--

.

-;500

0

1

10

2

10

10'

s 10

4

10

1

2

10

10

Time,s

Ti-6246: Effect of aging on Vickers hardness. Isothermal aging curves for alloy aged at 773 and 873 K after water quenching from the ~ field. Chemical composition: 5.48 wt% AI, 0.072 wt% Fe. 6.35 wt% Mo, 0.004 wt% N, 0.083 wt% 0, 1.94 wt% Sn, and 4.00 wt% Zr. Beta transus temperature was 1211 K. Alloy used was in the form of flat bar stock previously warm worked in the cx+~ field. Hardness determinations were obtained on electropolished specimens using a Zwick diamond pyramid hardness tester at a load of 10 kg

10' Time,s

4

10

s 10

Ti·6246: Tensile strength of duplex annealed sheet. Duplex annealed 870°C (1600 OF) 15 min. AC, 700°C (1290 OF), 15 min, AC

LIVE GRAPH

200

Temperature, OF 400 600 BOO


1500 200 /


1BO

500

'iii

""

160.r:-

ic:

e;,

c: 140 ~

~

en

C/)

900 Tensile yield

0

Click here to view Aged at 773 K

o Aged at 873 K

350L..-~_"'-~~"""'~~""""~~""""L....-.~"""'" 0.01

0.1

10 Time, h

120 100

600

LIVE GRAPH •

strength~

100

1000

200 400 Temperature.vc

600

Next Page Alpha-Beta Alloys I 521

Ti-6246: Tensile strength of triplex annealed sheet. Triplex annealed sheet, 855°C (15.70 OF), 15 min, FAC; 730°C (1345 OF) 15 min, AC; 595°C (1100 OF), 2 h, AC

Ti-6246: Hardenability. Variation of room-temperature tensile properties across a 150 mm (6 in.) section; solution treated 1 hat 870°C (1600 OF), WQ + aged 8 h, 595°C (1100 OF), AC

Temperature, of

200

400

600

800

8?

190

1000 1200 1400

1500

200

~ 170

1000

:2

~

Tensile yield strength

.;

s 160 m

c;, c

~

(jj

180

500 50

150 Out

0'---_ _-'--_ _-'-_ _--'_ _---'0

o

200

400

600

800

Temperature, °C

Center

Out

140L-........L_--'-_--'-_....l...-_-'--_.l-_'----' 4 -4 -3 -2 -1 0 1 2 3 Section location and dimensions, In,

Ti-6246: Microstructure. Forged at 870°C (1600 OF), solution treated 2 h at 870°C (1600 OF), air cooled, aged 8 h at 595°C (1100 OF), and air cooled. Elongated "primary" ex grains (light) in aged transformed p matrix containing acicular ex. Kroll's reagent (ASTM 192). 500x

Ti-6246: Microstructure. Bar forged at 870°C (1600 OF), solution treated 1 hat 870°C (1600 OF), water quenched, and aged 8 h at 595°C (1100 OF). The structure is similar to that in preceding microstructure, except that, as the result of water quenching, no acicular ex is visible. 2 mL HF, 10 mL HN03 , 88 mL H20 . 250x

Ti-6246: Microstructure. Forged at 870°C (1600 OF) solution treated at 915 °C (1680 OF), which reduced the amount of "primary" ex grains in the ex + p matrix. Kroll's reagent (ASTM 192). 500x

Ti-6246: Microstructure. Forged at 870°C (1600 OF) solution treated at 930 °C (1700 OF), which reduced the amount of ex grains and coarsened the acicular ex in the matrix. Kroll's reagent (ASTM 192).500x

Previous Page 522/ Heat Treater's Guide: Nonferrous Alloys

Ti-6246: Microstructure. Forged at 870°C (1600 OF) but solution treated at 955 °C (1750 OF), which is above the ~ transus. The resulting structure is coarse, acicular <X (light) and aged transformed ~ (dark). Kroll's reagent (ASTM 192). 500x

Ti·6246: Microstructure. Forging, solution treated 2 h at 955°C (1750 OF), above the ~ transus, and quenched in water. The structure consists entirely of <X/ (martensite). Kroll's reagent (ASTM 192). 50 Ox

Ti..6AI..4V Common Name. Ti64, 6AI-4V, 6-4 UNS Number. R56400 (normalinterstitial grade); R56401 (extra-lowinterstitial grade); R56402 (fillermetal) Chemical Composition. Effects of Impurities and Alloying. Ti64 is produced in a number of formulations, Depending on the application, the oxygen content may vary from 0.08 to more than 0.2% (by weight), the nitrogen content may be adjusted up to 0.05%, the aluminum content may reach 6.75%, and the vanadium content may reach 4.5%. The higher the content of these elements, particularly oxygen and nitrogen, the higher the strength. Conversely, lower additions of oxygen, nitrogen, and aluminum will improve the ductility, fracture toughness, stress-corrosion resistance, and resistance against crack growth ELI Grade. Ti-6AI-4V is available in ELI (extra-low interstitial) grades with high damage-tolerance properties, especially at cryogenic temperatures. The principal compositional characteristics are low oxygen and iron contents Ti·6AI-4V-Pd. A grade that has palladium additions (about 0.2 wt% Pd) for enhanced corrosion resistance. Sumitomo Titanium has produced this grade. See Tables for Ti64 and equivalents: specifications and compositions and commercial equivalents: compositions

Characteristics Product Forms. Ti-6AI-4V is available in wrought, cast, and powder metallurgy (PIM) forms, Properties vary depending on interstitial contents and thermal-mechanical processing Wrought Product Forms. Ti-6AI-4V is available in a wide range of wrought product forms Castings. Ti-6AI-4V of the same chemistry as for wrought materials has excellent casting characteristics. However, the high reactivity of titanium in the molten state requires suitable casting technology and has limited the

number of titanium foundries. In general terms, the mechanical and fatigue properties of castings will be slightly lower than for the wrought product, but fracture toughness, stress-corrosion resistance, and crack growth resistance will be comparable to that of annealed wrought Ti-6AI-4V PIM Products. The major reason for using the PIM products is to produce near-net shapes Applications. Designed primarily for high strength at low to moderate temperatures, Ti-6AI-4V has a high specific strength (strength/density), stability at temperatures up to 400°C (750 "F), and good corrosion resistance Aerospace Applications. Wrought Ti-6AI-4V is used extensively for turbine engine and airframe applications. Engine components include blades, discs, and wheels. Wrought forms are used for airframe components. Aerospace casting applications include the range from major structural components weighing more than 135 kg (300 Ib) each to small switch guards weighing less than 30 g (l oz). Wrought Ti64 is a useful material for surgical implants because of its low modulus, good tensile and fatigue strength, and biological compatibility. In the automotive industry, wrought Ti-6AI-4V is used in special applications in high-performance and racing cars where weight is critical, usually in reciprocating and rotating parts, such as valves, valve springs, connecting rods, and rocker arms.

Wrought Ti-6AI-4V applications include armaments, sonar equipment, deep-submergence craft, hydrofoils, and capsules for telephone-cable repeater stations. Casting applications include water-jet inducers for hydrofoil propulsion and seawater ball valves for nuclear submarines

Product Condition/Microstructure Annealed Condition. Although Ti-6AI-4V is commonly used in the mill-annealed condition, other annealing treatments are utilized. For example, annealing just above the beta transus, or annealing high in the <X + ~

Alpha-Seta Alloys I 523 phase field, creates a Widmanstiitten or lamellar a + ~ microstructure with good fracture toughness, stress-corrosion resistance, and crack growth resistance, and creep resistance. Recrystallization annealing of wrought alloy improves tensile ductility and fatigue performance Solution Treated, Quenched, and Aged Ti-6AI-4V Alloy. Solution-treated and quenched alloys may either have an acicular a'-martensite structure (quenched from above ~-transus) or mixed a' + a microstructure (quenched from 900-1000 0c) or mixed a" + a microstructure (quenched from 800-900 °C), of which the latter is exceptionally soft and ductile. They serve as starting conditions for subsequent aging treatments. Quenched components contain high residual stresses which may not be fully relieved upon aging at low temperatures. Such components may distort during machining. Ti-6AI-4V has excellent hardenability in sections up to about 25 mm (l in.) thick; strengths as high as 1140 MPa (165 ksi) may be achieved at aging temperatures between 300 and 600°C Lamellar Structures. Can be readily controlled by heat treatment. Slow cooling into the two-phase region from above the ~ transus leads to nucleation and growth of the a-phase in plate form starting from ~-grain boundaries. The resulting lamellar structure is fairly coarse and is often referred to as plate-like alpha. Air cooling results in a fine needle-like alpha phase referred to as acicular alpha. Certain intermediate cooling rates develop Widmanstiitten structures. Water-quenching from the ~-phase field followed by annealing in the (a + ~)-phase region leads to a much finer lamellar structure. Quenching from temperatures greater than 900°C (1650 OF) results in a needlelike hcp martensite (a'), while quenching from the 750 to 900°C (1380 to 1650 "F) temperature range produces an orthorhombic martensite (a'') Equiaxed Microstructures. Are obtained by extensive mechanical working (>75% reduction) the material in the (a + ~)-phase field, where the breakup of lamellar alpha into equiaxed alpha depends on the exact deformation procedure (e.g., see Figure). Subsequent annealing at about 700°C (1290 OF) produces the so-called "mill-annealed" microstructure, which gives a microstructure that is very dependent upon previous working. A more reproducible equiaxed structure is obtained by a recrystallization anneal of 4 h at 925°C (1695 OF) followed by slow cooling. The resulting structure is fairly coarse with an o-grain size of about 15-20 11m

that is welded in the ~ annealed/solution treated and aged condition followed by stress relieving. See Tables and Figures showing minimum and typical tensile properties, the effect of oxygen, the effect of texture, and the effect of processing

Fabrication Properties Forging. Ti-6AI-4V is supplied in several forging types, including open die (or hand) forgings. rings, closed die forgings, and precision forgings. It is more difficult to forge, as measured by flow stress and crack sensitivity, than most ferrous alloys (and all aluminum alloys), but is less difficult to forge than most nickel- and cobalt-base superalloys.

Ti-6AI-4V may be forged using either conventional (sub-B transus) or ~ (supra-B transus) forging techniques. Both techniques are used in combination with annealing and solution treating and annealing or aging thermal treatments. Other thermal treatments such as recrystallized annealing and/or ~ annealing or ~ solution treatment and annealing may be combined with conventional forging to achieve tailored properties. Conventional forging of Ti-6AI-4V predominates commercially because it achieves an equiaxed a in a transformed ~ matrix microstructure that is preferred for many applications. Beta forging of Ti-6AI-4V creates an acicular a microstructure that is preferred for service conditions where fracture-related and/or creep properties are highly critical Thermomechanical Processing. Thermomechanical processing is a key to obtaining selected microstructures in forging Ti-6AI-4Y. Several final treatments are available, such as annealing (A), solution treating, quenching (water, oil or air) and annealing or aging (STA or STAN). recrystallization annealing (RA), and beta annealing (BSTAN or BA).

See Tables and Figures for recommended forging temperatures; forging equipment and die temperatures; for forging properties (minimum room temperature) per composition, forging process, and heat treatment; for the effect of different thermomechanical processes; and for typical microstructures after working and annealing

Corrosion and Chemical Properties

Forming. Ti-6Al-4V typically is hot formed above 540°C (1000 OF). Normal production hot forming is usually at 650°C (1200 "F), but hot forming temperatures can be between 540 and 760 °C (1000 and 1400 "F), or even higher for superplastic forming. At 760°C (1400 "F), stresses are self-relieved

Although not as corrosion-resistant as commercially pure titanium alloys, Ti-6AI-4V has excellent corrosion resistance compared to other alloy systems. The exceptional corrosion resistance is due primarily to oxidefilm formation

Surface Treatment. Forming and bending must be done with sheet free of a case. If the sheet has a case on the surface, it will crack when bent. Residual a case must be removed with chemical cleaning before bending procedures can be used

Oxidation. The oxidation behavior of Ti-6AI-4V alloy is similar to that of unalloyed titanium. The reaction rate laws range from logarithmic (at 300-500 "C) to parabolic (500-750 "C) to linear (above 750°C) with increasing temperatures of oxidation

Bending. Bending properties of Ti-6AI-4V sheet vary with processing temperature. For production operations on mill annealed Ti-6AI-4V sheet, the room-temperature bend radius is essentially 6t. This bend radius will usually cover both longitudinal and long-transverse grain (sheet rolling) directions

Hydrogen Damage. Hydrogen damage of titanium and titanium alloys is manifested as a loss of ductility (embrittlement) and/or a reduction in the stress-intensity threshold for crack propagation. The damage is caused by hydrides, which form as hydrogen diffuses into the material during exposure with either gaseous or cathodic hydrogen. Because the phenomenon depends on both hydrogen diffusion and hydride formation, there may be a peak in hydrogen embrittlement as a function of temperature.

Alloy Ti-6AI-4V has moderate sensitivity to hydrogen damage

Typical Room Temperature Properties Room-temperature tensile properties are affected by heat treatment (microstructure), composition (oxygen content), and texture (primarily in sheet). Tensile strength can be changed by more than 200 MPa (30 ksi) by heat treatment and about 70 to 100 MPa (10 to 15 ksi) by oxygen content. Textured sheet can also exhibit variations on the order of200 MPa (30 ksi) as a function of direction Weldments. Failure is normally in the base metal. Generally, weld strength is higher and ductility is lower. The exception to this is material

Superplastic Forming. Superplastic forming performance is affected by several factors. Most procedures are based on Ti-6AI-4V sheet.

See Tables for forming temperatures Machining Properties. Based on a rating system in which AISI B1112 steel has a machinability rating of 100, the machinability of Ti-6AI-4V in the annealed condition is 22.

See Table for comparative machinability ratings of different metals Welding Processes. Ti-6AI-4V may be welded by a wide variety of conventional fusion and solid-state processes, although its chemical reactivity typically requires special procedures and precautions. In the United States, fusion welding is performed principally in inert-gas-shielded arc and high-energy beam welding processes.

See Tables for more information on: • Gas tungsten arc welding • Gas metal arc welding

524/ Heat Treater's Guide: Nonferrous Alloys • • • •

Plasma arc welding Electron beam welding Laser beam welding Resistance spot welding

Recommended Heat Treating Practice Annealing. Ti-6AI-4V is most commonly used in the fully annealed condition, often referred to as mill annealed. It has limited hardenability, but is sometimes used in the solution treated and aged (STA) condition. Using STA, strengths as high as 1110 MPa (160 ksi) can be achieved in section thicknesses up to 12.7 to 19 mm (0.5 to 0.75 in.) Damage tolerance properties are optimized (fracture toughness is maximized and the crack growth rate is minimized) by ~ annealing (BA), which provides a totally transformed ~ structure. This, however, results in reduced ductility (although the material would still have at least 5% elongation) and reduced fatigue strength. Beta annealing should not be used on sheet gages due to the possible incidence of a single prior ~ grain across the entire thickness. Improvements in fatigue performance can be achieved by water quenching from above the ~ transus temperature of 995 °C (1825 "F), This refines the transformed structure. Recrystallization annealing (RA) also increases damage tolerant properties. Fracture toughness and crack growth resistance are typically not quite as good as BA, but fatigue performance and ductility are improved. To maximize damage tolerance properties, the extra-low-interstitial (ELl) grade, which contains lower oxygen, should be used with both the recrystallization anneal and the ~ anneal. Another option for achieving improved damage tolerance over mill annealing is a duplex anneal, although this is not a common heat treatment. The first anneal of a duplex anneal is high in the a-~ phase field. On cooling, the ~ at temperature transforms to a lamellar a-~ structure, which improves damage tolerance properties. The higher the first anneal temperature, the higher the fracture toughness and crack growth resistance; fatigue strength diminishes until the anneal temperature exceeds the ~ transus. The high-temperature anneal is followed by a full anneal or mill anneal. This heat treatment is very similar to RA, except the cooling rate from the first anneal temperature is faster, resulting in the transformed structure. The RA treatment uses a slower cooling rate, resulting in a predominantly equiaxed structure

Thermomechanical Processing. A recent patent (Patent No. 5,118,363, ALCOA, Pittsburgh, PA) has been issued for improving mechanical properties of forgings. The processing steps include heating slightly above the ~ transus temperature to form the ~ phase, followed by rapid cooling; reheating the billet (which now has a fine ~ transformed structure) to 855 to 925 °C (1570 to 1695 "F); forging to obtain a reduction ratio of about 3:1; cooling and solution treating to form primary a particles; and aging and cooling

Furnaces and Atmospheres. Heat treatment should be in atmospheres free of reducing gases and other contaminants that might produce excessive hydrogen pick up. Gas-fired furnaces should have oxidizing flames, and there should be no flame impingement on the part. Furnaces used above 650°C (1200 OF) that have contained endothermic or dissociated ammonia atmospheres should be equipped to prevent leakage, purged, and tested for hydrogen pickup prior to heat treating the first load of titanium parts. The use of inert gas or vacuum atmospheres minimizes contamination when properly controlled. Molten salt and fluidized beds should not be used. See MIL-H-81200 for further guidelines

Stress Relieving. The effect of time and temperature on stress relieving at elevated temperatures is shown in the nomograph for Ti-6AI-4V. At 595 °C (1100 OF), it takes 50 h to achieve a full stress relief; a 50% stress relief would take about 1 hat 595°C (1100 OF) or 5 h at 540°C (1000 "F). Such a diagram is extremely valuable in selection of thermal treatments to reduce residual stress levels. Stress relaxation data can often be fitted to a timetemperature parameter such as the Larson-Miller parameter.

SELECTED REFERENCES • C.R. Brooks, Heat Treatment, Structure and Properties of Nonferrous Alloys, American Society for Metals, 1982, p 361-376 • lA. Burger and D.K. Hanink, Heat Treating Titanium and Its Alloys, Met. Prog., Vol 91 (No.6), June 1957, p 70-75 • ASM Trans, 1956, p 657-676 • W. Herman et al., HeatTreating of Titanium and Titanium Alloys, Metals Handbook, Vol 4, 9th ed., Heat Treating, American Society for Metals, 1981, p 763-774 • R.A. Wood and R.I. Favor, Titanium Alloy Handbook, MCIC-HB-02, Battelle Memorial Institute, 1972 For further information see: • Table listing heat treatments and procedures • Table listing mechanical properties obtained with different heat treatments • Figure indicating stress relief obtained at different times • Nomograph for stress relief showing relationship of time, temperature, and percent of stress relief • Figure showing effect of temperature on tensile properties • Table showing variation in tensile properties of bar stock with solution treating temperature Beta Heat Treated Microstructures • Figure for heat treatment cycles of transformed beta Alpha + Beta Annealed Microstructures • Figures for typical microstructures, and for processing cycles used to obtain fme microstructures in alpha + beta alloys • See Figure for microstructure of equiaxed a and a"

Ti·6AI·4V: Wrought products Product

SizeIlIId weighl ranges

Pricecomparison(&)

Ingot Billet

3200to 13,600kg (7000to 30,000Ib) Nonnally100mrn(4 in.)diamto about355mrn (14in.)diam orsquare.Billetsupto 5000Ib havebeensold,butthisis nOI necessarily the upperlimit Cross-secrions up to0.4 x 0.4 m (16 x 16in.) Bar Dieforging From1300kg «lib to >3000Ib) Ti,$301lb; AI,$IOIlb; stainless steel,$8Ilb 'Iyplcaldimensions: Thickness: 5 to75 mrn Plale (0.1875to 3 in.); Width:915and 1220mrn (36and48 ln.); Length:1.8,2.4.and3 m (72, 96,and 120 in.) Typicaldimensions: Thickness: 0.4 to4.75mrn Ti,$16Ilb;stainless steel,$3I1b; AI, Sheet (0.016to 0.187 in.); Width:915 and 1220mrn $24I1b;Inco718,$IOllb (36and48 in.); Length:1.8,2.4,and3 m (72. 96,and 120in.) Tube Specialty item Ti, $8I1b; stainlesssteelandAI, Forgedblock Available in a widerangeof sizes,with $2.5Q.3I1b maximumsizerelatedto ingotsizeandthe amountof work thatcan be impartedtothe forgedblock Extrusion Fromcirclesizesofaboul25 to760 mrn(Ito 30 Ti,$13·15Ib; 300seriesstainless ln.) Warn. MInimumthicknessof about3 mrn steel,$3·4I1b; 15·5PH,$4-5I1b; (0.125in.)forsmallcirclesizes,andabout13 13·8PH,$9·1211b;AI, $2411b mrn(0.5 in.)forlargecirclesizes 'Iypicallymanufactured in sizesrangingfrom 0.25 in. wire: n, $261lb; A283, Wire $6IIb; stainlesssteel,$7.501lb; 0.281012.2mrn(O.01lto0.480in.)diam 8740,$llIb; AI7075,$2.301lb (a)Duetoitslowerdensity,Llbof'titanlurnisapproximately 1.7101.8moremeterialby volumethan lIb of steelor nickel-basealloy

Alpha-Beta Alloys I 525

Ti-6AI-4V andequivalents: Specifications andcompositions Spe ::>

~Q)

~ 600 Q) a. E ~ 500

a.

1000 E Q)

f-

800

Ti-6AI-4V: Variation of tensile properties of bar stock with solution treating temperature Room-temperature tensile propertlesta)

Sotution-treating

-c

temperature OF

845 870 900 925 940

1555 1600 1650 1695 1725


Yield streugth(b) MPa ksi

1025 1060 1095 1110 1140

980 985 995 1000 1055

149 154 159 161 165

142 143 144 145 153

Elongation in4D, %

18 17 16 16 16

(a)Propertiesdetennioed on 13mm(0.5in.)baraftersolutiontreating,quenchingand aging.Aging treatment: 8h at 480 °C(900 OF),aircool.(bj At 0.2% offset

Ti-6AI·4V: Microstructure (TEM). Equiaxed a (dark) and a" (light)

Alpha-Beta Alloys /531

Ti-6AI-4V: Thermal treatments with three different cooling rates

T 1050'C 850'C

®

800'C

c

p+u'

Low ~

-) High

Solulion lrealmenllemperalure

10

10

Time, min

600

2

~

Alpha-Beta Alloys I 539

Ti-662: Commercial compositions Specification France Ugine Ugine Germany DeutscheT Deutsche T

Designation

Description

AI

Cu

Fe

H

N

0

So

V

Other

Uf662 Uf662

ShPltFrgAnn ShPltFrgQA

5-6 5-6

0.35-1 0.35-1

0.35-1 0.35-1

0.Ql5 0.015

0.04 0.04

0.2 0.2

1.5-2.5 1.5-2.5

5-6 5-6

balTI balTI

ContimetA1VSn6-6-2 Contimet AIVSn6-6-2 LT33 LT33

PItBarFrgPipAnn PitBarFrgPipSTA FrgAged FrgAnn

5-6 5-6 5-6 5-6

0.35-1 0.35-1 0.35-1 0.35-1

0.35-1 0.35-1 0.35-1 0.35-1

0.015 0.Ql5 0.Ql5 0.Ql5

0.04 0.04 0.04 0.04

0.2 0.2 0.2 0.2

1.5-2.5 1.5-2.5 1.5-2.5 1.5-2.5

5-6 5-6 5-6 5-6

CO.05;balTI CO.05;balTI CO.05; balTI CO.05;balTI

KS6-6-2 KS6-6-2 Ti-6A1-6V-2Sn 662AT

PltShAnn PItShSTA

5-6 5-6

0.35-1 0.35-1

0.35-1 0.35-1

0.0125 0.0125

0.04 0.04

0.2 0.2

5-6 5-6

balTI balTi

STA

5-6

0.35-1

0.015

0.04

0.12-0.2

1.5-2.5

5-6

CO.05;balTi

CO.08;balTi C0.08;balTi CO.05max; balTi CO.05; balTi

DeutscheT DeutscheT Japan Kobe Kobe Sumitomo Toho USA OREMEf RMI RMI Timet

Ti6-6-2 RMI6AI-6V-2Sn RMI6A1-6V-2Sn T1METAL6-6-2

MultFonnsAnn MultFonnsSTA Ann

5-6 5-6 5-6

0.35-1 0.35-1

0.35-1 0.35-1 0.35-1

0.0125-0.015 0.0125-0.015 0.Ql5

0.04 0.04 0.05max

0.2 0.2 0.2 max

1.5-2.5 1.5-2.5 1.5-2.5

5-6 5-6 5-6

Timet

T1METAL6-6-2STA

BilBarPitShStrSTA

5-6

0.35-1

0.35-1

0.Ql5

0.04

0.2

1.5-2.5

5-6

Singlevaluesare maximums

Ti-662: Effect of thermomechanical processing on properties Microstructural observation of thermomechanical processing options for T1-662 suggest that a morphology is the key microstructural feature affected by this processing route. However, a grain size modification is least significant. Cost and product uniformity implications are similar to those for T1-6AI-4V.

Alloy

'lMPoplion

Ti-6AI-6V-2Sn Std

a+ ~ forgeJMA a + ~ forgeJRA

Ti-6AI-6V-2Sn Eli

a + ~ forgeJRA

Ti-6AI-6V-2Sn Std

~ prefonnIMA ~ prefonnlblockIMA

'Thnsileyield

UltimatetensJle

strength

strength

120

ksi

MPa

ksi

%

%

MPa'lm'

ksi'liii:"

L T L T L T .L T L T

1094 1049 1041 1028 1022 993 1032 1021 1024 973

158 152 151 149 148.2 144 150 148.0 148.5 141

1164 1128 1110 1095 1089 1068 1094 1090 1110 1076

169 163 161 159 158 155 158.6 158.1 161 156

18 15

31 24 33 29 37 29 22 23 19 22

39

35

50

45

74 68 58 59

67 62 52 53 64 63

Temperalure, OF 140 160 180 200

0

0


240

6

•

• o

J: a.

5 4

•

3

•

Crevice corrosion

BP

2'---_---I----L~_ ___'_

__'__..l-_

_1

25

100

125

50

75 Temperalure, °C

71

69

'Thmpemlure 'fteatment SoluIion treatments Typicalfor mostproducts Sheet3.2mm (0.125in.)thick Bar,forging, extrusions Aging 'tYPical Low agingtemperature Overage Flatrolledproducts Bar,forgings. extrusions

No crevice corrosion 7

17

16 19 15 11 12 9 10

Ti-662: Solution treatment and aging

9 8

Kk

MPa

LIVE GRAPH 100

of area,

Dire:

750

As quenched Aged 480°C (900 oF), 3 h Aged 620°C (1150 OF), 3 h

600

a' ----.. Q+P

Q.

..... U+P+l a+~

a+~

.,

E 550

ui

f-

III

Ql

500

c:

~42 J:

•

450 400

2

5 Seconds

Minutes Time ---.-.

o

6 12 18 24 30 Distance from quenched end of Jomlny bar,

\6 in.

36

3 Hours

4

5

,j

Previous Page Alpha-Beta Alloys /541

treatm~nt temperature (1 h exposure terminated by water quenching) on the aged tensile properties of die forgings aged 3 h, 585°C (1090 OF), air cooled

Ti-662: Effectof solutiontreatment on tensile properties. Effect of solution heat

LIVE GRAPH

LIVE GRAPH 1300 40

1300 1400 1500 1600 1700 1800 1900 2000 1500

1400

1500

1600

1700

(}

1400

'" :;

-

30

200

190~

~ 1300

~

0

til

0

13-25 >25-50 >50-100 >100(a) >100(b)

$.5 >0.5 >1-2 >2-4 >4(a) >4(b)

$13 >13-25 >25-50 >50-100 25 22

>100-150

>4-6

$25

$.5 >0.5-1 >1-2 >2-4 1 0.875 square ";1

U1Iin:uile tensile

strength

'Ienslle properties (guaranteed mloimum) Thnsile Yield Eloogalion in strength 4D,% (0.2% 011"0

MPa

ksi

MPa

ksi

L

1240 1170 1105 1035 1170 1170

180 170 160 150 170 170

1135 1105 1035 965 1105 1105

165 160 150 140 160 160

8 8 8 8

1105

160

1035

150

6

Nole: Specimenswereheattreared.(a) Upsetforged10 25 mm (l in.) maximumusing3 to 1ratio. (b) Reforgedto22 mm (0.875in.)square

T

6 6 8

Reduclionof

area, % L

20 20 20 20

T

12 10 15

20

8 4

15

12

Alpha-Beta Alloys I 543 Ti-7AI-4Mo: Equivalentspecifications Specification

Designation

UNS R56740 USA AMS4970E MILF-83142A Comp9 MILT-9047G TI-7A14Mo

Descriplion

AI

Fe

C

H

Mo

7 Frg Bar Wrr BilSTA

FrgHf BarBiiSTAAnn

845°C (1555 oF) I h. WQ. 480°C (900 oF) 16h.AC

870°C (1600 oF) I h, WQ. 480°C (900 oF) 16h.AC

0

OT

Other barn

0.05 0.05 0.05

0.2 0.2 0.2

0.4 0.4 0.4

Y 0.005; balTI Y 0.005; balTI Y 0.005; balTI

4

6.5-7.3 6.5-7.3 6.5-7.3

0.1 0.1 0.1

0.3 0.3 0.3

Ti-7AI-4Mo: Vickershardness Heat treatment

N

0.013 0.013 0.013

3.5-4.5 3.5-4.5 3.5-4.5

Ti-7AI-4Mo: Forgingprocess temperatures Ultimate tensile strength MPa ksI

1148 1147 1138 1135 1128 1139 1146 1168 1196 1165 1168 1148 1145 1150 1153 1174 1198 1248

166.5 166.4 165.1 164.7 163.3 165.2 166.3 169.5 173.5 169.0 169.5 166.6 166.1 166.8 167.2 170.3 173.8 181.0

Metallemperature

°C

Process Hardness, HV

400 360 388 376 373 365 349 366 386 348 347 355 348 348 356 360 367 364

Note: Measurements were made from consecutive 9.5 rnm (0.375 in.) locations on a standard Jominybar

Conventionalforging Supratransusforging

900-985

1650-1805

(a)

(a)

(a) Bela forgingcan be performed in earlyforging operationsifit is followedby substantialsubtransus working

Ti-7AI-4Mo: Heat treatment conditions Heat trealment

-c

Thmperalure OF

TIme,

Cooting

h

method

480-705 705-790 790

900-1300 1300-1455 1455

1-8 1-8 I

Air or slow cool Air cool Furnacecool to 565°C (1050 oF), then air cool

Solutiontreatmentrange 870-980 Recommendedsolutiontreatment 930-955 Aging range (min to max) 510-620 Typicalage 565

1600-1795 1700-1750 950-1150 1050

0.5 to 1.5 I Upl024 4-8

WQ WQ

Stressrelief Annealingrange Recommendedanneal

AC AC

TIMETAL® 625 Ti-6AI-1.7Fe-O.1 Si Common Name. 62S

Characteristics

UNS Number. Unassigned

Phases and Structures. The microstructural response of 62S to heat treatment is quite similar to that of Ti-6AI-4V. The transformed p microstructure is typically a colony structure after air cooling, but can be Widmanstiitten for more rapid cooling. Alpha-beta processing results in a structure consisting of primary ex with transformed 11 The transformed p structure varies with the cooling rate

Chemical Composition. In a study of the effect of iron and oxygen contents on the properties of this alloy, the following conclusions were made: • On average, an increase of about 0.07 wt% oxygen is equivalent to (or provides) about a 60 MPa increase in strength (i.e., about 8.5 MPa per 0.01 wt% oxygen) • On average, a 1 wt% change in iron content resulted in only about a 40 MPa increase in strength • For all heat treated conditions, the combination of high iron (2.4%) and high oxygen (0.25%) resulted in unacceptable post-creep ductility • Although annealing treatment had only a minor effect on creep properties (700°C anneal was worse than 790°C), the solution treated and aged condition provided substantially better properties than both an. nealed conditions • Post-creep ductility was maximized by the 790°C (1455 "F) anneal, low oxygen, and in general low iron. See Table for typical composition range

Product Forms. Ingot is available in 710,815, or 865 rom (28 to 34 in.) diameters in masses ranging from 3180 through 6365 kg (7000 through 14000 lb). Bloom is a semifmished form forged from above the p transus. Forging billet and bar are available as rounds, squares, or rectangles. Sheet and plate are also available. Plate is available in thickness from 4.8 to 102 rom (0.2 to 4 in.) in widths up to 3.05 m (10 ft) and lengths up to 10.67 m (35 ft). The distinction between plate and sheet is made at 4.8 rom (0.19 in.). The standard sheet thickness minimum is 0.41 rom (0.016 in.). Sheet widths are available up to 1220 mm (48 in.). Cut lengths beyond 4880 mm (192 in.) are not standard. Finish grinding on both sides is standard procedure. 62S is typically processed to plate or billet either in the p or ex-p temperature fields. Beta processing is used to improve yield and reduce the cost of processing in cases where the p structure is acceptable such as industrial

544/ Heat Treater's Guide: Nonferrous Alloys applications (in which the corrosion resistance and low density are the primary reasons for use) and automotive applications (in which improved creep strength may be used). Alpha-beta processing is used for applications such as armor for improved ballistic response Applications. Because iron is used as a stabilizer in lieu of more expensive elements, alloy 62S has a lower formulation cost than most titanium alloys, yet properties and processing characteristics are equivalent to or better than those of Ti-6AI-4V. The combination of reasonable cost and excellent mechanical properties makes 62S a practical substitute for other engineering materials in numerous industrial applications that require low weight and high corrosion resistance. The microstructural response of 62S to heat treatment is quite similar to that of Ti-6AI-4Y. The alloy has a relatively high modulus-to-density ratio.

625: General corrosion rates for

The alloy has industrial, automotive, and defense applications General Corrosion Properties. See Table listing general corrosion rates for alpha-beta processed sheet Mechanical Properties. In both the beta- and alpha-beta processed conditions, tensile properties are comparable to those of Ti-6AI-4V. Creep properties and Larson-Miller plots are also expected to be essentially the same as similarly processed Ti-6Al-4Y. See Table for minimum tensile properties of 62S vs. Ti-6AI-4V Fabrication Properties. Bulk working, forming, machining, and welding properties are similar to those of Ti-6AI-4V

Recommended Heat Treating Practice See Table for typical treatments: stress relief, mill anneal, recrystallization anneal, and aging

a-p processed sheet Conuslon rate, mm/year

Solutionfcondltlon

0.25%HCI,boiling 0.5%HCI,boiling 1.0%HCI,boiling 1.0%HCI,65°C (145oF) 3.0%HCI,65°C (145oF) 5.0%HCI,65°C (145oF) Seawater. pH 1.5,boiling Seawater. pH3.0,boiling Seawater. pH3.5.boiling 50 vol%acetic acid,50vol%formic acid.boiling 10vol%aceticacid,10vol%formic acid.boiling

1.19 2.3475 8.35 1.15 4.675 11.45 5.45 0.00375 0.000 1.775 3.625

625: Typical composition range

Minimum Maximum Nominal

AI

Fe

5.5 6.5 6.0

1.3 2.0 1.65

Composltlon, WI% Oz SI

0,07 0.13 0.10

0.15 O.W

0.18

625: Typical heat treatments 'Iemperature

625: Minimum tensile properties 'Thnsile yield

Alloy

Ultimate tensile st",ngth MPa ksi

MPa

ksI

Elongation, %

62S TI-6AI-4V

930 895

895 825

130 120

10 10

135 130

OF

Duratlon,h

CooHng method

Stressmlief(a) 480-650 700-790 Millanneal Recrystallization anneal 970

900-1200 1290-1455 1775

Ito 4 2 1

Solution treatment Age

Pr-llO°F 1000

1 8

Aircool Aircool furnace coolto 760°C (1400 oF), hold2 h, fanaircool Waterquench Aircool

'Ireatment strength

Note: Aonealed plateand forgings to 75 rom(3 in.) thick.62S and11-6AI-4V a-p processed plus annealedat700 to790 °C (1290to 1455oF) for2 h, air cooled

·C

Pr-60°C 540

(a)StressreliefsameasTI-6Al-4V

Ti-4.5AI-3V-2Mo-2Fe Common Name. SP-700 UNS Number. Unassigned Chemical Composition. See Table for composition requirements

Characteristics Beta Transus. 900 ± 5°C (1650 ± 9 OF) Product Forms. SP-700 is available in all mill product forms (plate, sheet, round bar, etc.), as well as in cast and powder metallurgy (P/M) forms Applications. SP-700 is a ~-rich a-~ titanium alloy designed to offer superplastic formability properties superior to those of Ti-6AI-4V. The low flow stress of the alloy, together with its fine microstructure, results in excellent superplastic formability at a temperature level of 700°C (1290 OF), which provides the origin of the name SP-700.

The fine microstructure results in an excellent combination of mechanical properties. The alloy exhibits excellent heat treatability, cold formability, and hot forgeability. SP-700 is specified in either the annealed or the solution-treated and aged condition. The alloy consists of a very fine microstructure in all heat treatment conditions-for example, the primary a grains are typically smaller than 3 11m in the recrystallization armealed condition. It can be hardened to 450 HV or higher by solution treatment in the a + ~ region followed by short-time aging. SP-700 is superplastically formed into such components as aerospace parts, metal wood golf club heads, and metal balloons. Other uses include working tools, automobile parts, wrist watch casings, and mountain-climbing equipment

Alpha-Beta Alloys I 545 Annealing. Mill annealing requires 0.5 to 2 h at 650 to 750°C (1200 to

Corrosion Properties General Corrosion. The corrosion resistance of SP-700 depends on the formation of a protective oxide layer, such as commercially pure titanium. SP-700 resists corrosion under a salt environment and has slightly higher corrosion resistance in hot or concentrated solutions of reducing acids such as hydrochloric and sulfuric acid than pure titanium and Ti-6AI-4V. Corrosion resistance in acid solutions depends on concentration and temperature

1380 "F) followed by furnace or air cooling. Recrystallization annealing (see Table) provides maximum cold working capability. The highest volume fraction of ~ phase, 40%, was retained for the annealing at 800°C (1470 OF)


Solution Heat Treating. Requires 0.5 to 2 h at temperature range of 800 to 850°C (1470 to 1560 "F), followed either by water quenching to obtain very high strength or by air cooling to obtain high strength with good ductility

Hardness. Mill-annealed SP-700 has a hardness of 300 to 330 HV

Aging. Requires 1 to 6 h at 450 to 600 °C (840 to 1110 "F), followed by

Recrystallization-annealed SP-700 has a hardness of 280 to 320 HV. Solution treated and aged SP-700 offers a wide range of hardness, from 350 to 510 HV, depending on solution treating and aging conditions.

air cooling (see Figures). A relatively short aging period is enough to achieve an excellent combination of strength and ductility (see Figure)

See Table for typical tensile properties of sheet

Fabrication Properties Forgeability. SP-7OO exhibits much higher resistance to hot deformation cracking than Ti-6AI-4V. See Figure for effect of temperature on flow stress; and Figure comparing forgeability with that of Ti-6AI-4V

Cold Formability. SP-700 has much better cold formability in comparison with Ti-6AI-4V

Superplastic Formability. SP-700 shows excellent formability at 775 °C (1425 oF), more than 100°C (180 "F) lower than the Ti-6AI-4V forming temperature See Table comparing cold formability vs. that ofTi-6AI-4V; and Figure (a) and (b) comparing superplastic fonnability with that of Ti-6AI-4V

Weldability. The alloy can be fusion and spot welded

Recommended Heat Treating Practice SP-700 is specified either in the annealed condition or in the fully heattreated condition

Hardenability. SP-700 has better hardenability than Ti-6AI-4v' SP-700 is also less sensitive to section size on quenching. The greater stability of the ~ phase of SP-700 compared to Ti-6AI-4V provides greater flexibility during heat treatment. SP-700 is relatively insensitive to quench delays of up to 30 s. It is also less sensitive than Ti-6AI-4V with regard to cooling rate down to about 1 °C/s (2 °F/s) and relatively insensitive to cooling rate in the range of about 7 to 150 °C/s (13 to 270 °F/s). See Tables for: • • • •

Minimums of annealed sheet Comparison of annealed tensile properties Properties of heat treated plate Recommended heat treatments

See Figures for: • • • • • •

Effect of aging temperature on hardness and tensile properties (a), (b), (c) Effect of aging time on tensile properties (a), (b) Aging response Effect of delay time of quenching on strength Effect of cooling rate on strength Effect of quenched section size on strength

SP-700: Cold formability versus Ti-6AI-4V Alloy

SP-700: Comparison of annealed tensile properties among product forms 0.2 ~ Yield strength

'Thn5IIe streogth

Elongollon,

Product ronn

MPa

IIsI

MPa

ksI

~

Plate Sheet Bar

990 949 936

144 138 136

1028 1025 1007

149 148 146

16.8 22.8 18.4

Mill-annealed material.Tensiletestingwasperformed on 6.25 nun(0.25in.) diamroundspecimens with a 25 nun (1 in.) gagelengthfor a 15 nun (0.6in.) thickplateand a 22 nun (0.9in.)bar,and on rectangularspecimenswitha 6 nun (0.24in.) widthand a 25 nun (l in.) gagelengthfor a 3.8 nun (0.15in.)thicksheet

SP-7oo Ti-6Al-4V

Element Aluminum Vanadium Molybdenum Iron

Oxygen Carbon

Nitrogen Hydrogen yttrium

4.0-5.0 2.5-3.5 1.8-2.2 1.7-2.3 0.15max 0.08max 0.05max 0,0\ max 0.005max

Other Each Total

Titanium

0.10max 0.40max bal

Coldrolling reduction limit, ~

L T L,T

2.1 2.1 4

69 58 20

SP-700: Properties of heat-treated 15 mm (0.6 in.) plate 0.2~ YIeld

SP-7OO Wt~

Bend factor(RIl)

(a) L, longitudinal; T, transverse. SP-7oowas recrystallization annealed; Ti-6AI-4V was mill annealed.Bendfactorsweredetermined bybendingtestson specimens 20 nun (0.8in.)wide, 140nun (5.5 in.) long,and 4 nun (0.16in.) thick.Maximumreductionlimitswereobtainedby cold rolling tests

Alloy

SP-700: Composition requirements

Dire

s:

c:

0,

Ql

1300 ~ tl

~ 1300 0.2%YS 'C

Qi

>

TS

~

~ 1100

0-..

--

0.2%YS - " -, 900 1

-- --

5.0 4.0

10

3.0

1500

TS

a.

'"

a.

s: 1300

1300 ::::;

i

0, c:

e

c:

l!!

tl

Ql

> 1100

1100 I
c

~

~

~

1ii .9! 1300 '0; c

......................... 190 .9! '0; cQ) 180 -;

s

j 1200·····

(;j

E 1705

5"" 110°L.450

---'

.....;,.

500 550 Aging temperature, °C

....160 600

730-785 690-730 815-870

1350-1450 1275-1350 1500-1600

Cooling

methOO(.)

ACor WQ ACorWQ ACorWQ

5

5 5(b)

Click here to view

1500

; 1400 0> c

OF

Beta III: Effect of pre-aging and cold work. Effect of pre-aging heat treatments with and without prior cold work on tensile strength of aged (450 °C, 840 OF) specimens. Solution heat treated 5 min at 730 °C (1345 OF) and water quenched priorto cold working or pre-aging LIVE GRAPH 1600

~

0C

Note:The bestcombination of properties is obtained by solutiontreatmentnearthe beta transus. (a) Eitheraircool(AC)or waterquench(WQ) mightalloythesameagingresponsedepending onsectionthickness. (b)Exposureis usuallyshort,but may be longerfor thickersections

1100 210._

TIme, min

'Iemperature

TypicalST LowSTforrod, wire,etc. HighSTforthickersection

:r:

Click here to view

.g450 -'.

0 ~

'1

III

81400 c: 'E

0"c

/

os

"-

/

.c: {'! ~

(6000min) 850 -c (1560oF)(2 h)+ WQ + 250°C (480°F) (10 min) 720°C (1330oF)(100min)+ WQ + 370°C (700°F) (1000min) 850°C (1560 "P) (100min)+ WQ + 370°C (700oF)(1000min) 730°C (1345oF)+ WQ + 500°C (930oF)(60 min) 850°C (1560oF)(100 min) + WQ+ 500 °C (930oF)(240min)

Thnsile yield strength MPa ksi

UltJmate tenslle strength MPa k.d

741 107 262 38 1218 176 Brittle,no yield 1240 180 Brittle.no yield 1063 154 1225 177

862 878 1266

125 127 183

1430

207

1106 1243

160 180

Unlfonn elongation,

Elongation

...

toratlure,

Reduction ofarea,

9.7 l5.7 0.26 0 2.7 0 4.6 2.3

18.6 21.8 0.58 0 8.9 0 17.5 8.7

35 32 2.25 0 16 0 58 14

...

...

Note: Tensiletestingwas performedon an Instron machineusing a clip-onextensometer. The strainrate was 0.00055Is. and the tensilespecimengage sectionswere0.640em (0.25 in.) in diarnand3.2 cm (1.3In.)in length.Specimenswerepulledwith the rollingdirectionparallelto the tensileaxis

Beta and Near-Beta Alloys I 569

Ti-l0V-2Fe-3AI: Heat treatingschedules for forgings Solutiontreat andage

Ti-10V-2Fe-3AI: Effect of solution temperature on primary a content LIVE GRAPH

75010765°C(l385 to 1410°F),lh, WQ 48010495 -c(90010950oF),8 h,AC 730°C (1350oF),1h,AC 580 to595°C (1075to 1l00°F), 8h,AC 765°C (1400oF),1h, Fe to565°C (1050oF) 565°C (1050oF),8 h,AC 480°C (900 oF),48 h, AC(optional) 815°C(1500°F), 1h,AC 620°C (1150oF),8 h,AC

Solutiontreatand overage Stabilize

Beta anneal and overage

Click here to view Solution treatmenttemperature, OF

E

51 30

'S

S-

II

E

Ti-l0V-2Fe-3AI: Heat treatmentper AMS specifications

20

O.3%) RT Ti-2.5Al-IMo-11Sn-5Zr-O.2Si (lM1-679), TI-5Al-2.5Sn, TI-SMn,Ti-6Al4V, Ti-6AI6V-2Sn.TI-6Al-2Nb-1Ta,Ti4Al-3MoIV, Ti-SAI-IMo-IV, Ti-6AI-2Sn4Zr-6Mo

Metal embrittlement Cooling method

Cadmium(solid +liquid) Mercury(liquid)

25·600 370

75-1110 TI-SMn.grade2, TI-6Al4V 700 GrATI,TI-6Al4V. TI-8Al-IMo-IV

AC 15 5-15

AC AC ACorWQ

(a) Stressrelief if aging is not planned; stress reliefcartbe accomplishedduring4S0 °C (900 "P) aging. (b) Stress relieffor materialother than weldments

Ti-13-11-3: Solution treatment and aging Thmperalure OC

OF

Time, h

Cooling method

>760 775-S00

>1400 1425-1475

0.25-1 0.25-1

ACorWQ ACorWC

700-1040 425-540 425-510

1300-1900

0.25-1

SOO-950

20-100

ACorWQ AC AC

Heat

'Ireatmenr

Typicalsolutiontreatment Narrowsolutiontreating range BroadST range Agingrange Typicalage

aoo-iooo


Ti-13V-ll Cr-3AI: RTtensile properties of forged and heat treated bars

Harsize nun In.

150

480 0C (900 OF) aging treatDirection menf.h

6

L

48

T 100

4

48

L

T 75

3

L

48

T 30

L

T 50

2

30

L

30

1.2

20

L

T

Ultimate lensUe strength MPa ksl

'Iensileyield strength (0,2 % offset) MPa ksl

1264 1297 1474 13% 1478 1462 1438 1407 1368 1340 1424

1153 1169 1388 1307 1369 1364 1341 1288 1241 1232 1290

183.3 188.1 213.9 202.5 214.4 212.1 208.6 204.1 198.5 194.4 206.6

Ti-13V-ll Cr-3AI: Vickers hardness of weldments Post-weld b..tt ....tment

BasemetaJ

Hardnessla), HV HAZ

Weldzone

280 257 287 265

278 287 291 281

253 315 368 383

Reduction Elongation, ofarea,

167.2 169.6 201.3 189.6 198.6 197.9 194.6 186.9 180.0 178.7 187.2

%

%

8.0 8.0 4.0 4.0 6.0 3.0 6.5 5.0 7.0 5.0 10.0

13.7 8.5 11.6 12.4 9.3 6.2 8.5 12.0 10.0 12.0 15.8

As welded Weld + 2h 315°C (600°F) Weld+4h 315°C (600°F) Weld + 8 h 315°C (600 oF)

(a) Spot weldingcharacteristics were investigated by hardnesstestinga cross sectionof the weld nugget.The hardnesssurveyindicatedthatdecomposition takesplaceaftershort-termthermal exposureat 315°C (600 "F), Increasein hardnessis confinedto theweldmetal.(a 15Q.g load)

Ti-13V-11Cr-3AI: Phase diagram with variable aluminum content LIVE GRAPH

Centerofbar samples.Barsageddirectlyfromforgingoperation

Click here to view 800 Nominal aluminumcontent

fBeta transus with high oxygeniontent I _

750

Ti-13V-11Cr-3AI: Phase diagram with variable chromium content LIVE GRAPH Click here to view 800

I

P 700

t IBeta transus with highe

1300

o

i! Q)

c. E Q)

a+(3+TiCr2

0.05wt%02 500L-_-'-_ _L-_-'-_ _' - - _ - ' - _ - l 8

5

6

9

10 11 12 Chromium content, wt%

13

1000

Ti-13V-11Cr-3AI: Rockwell hardness vs. aging time. The rapid increase in hardness that follows the initial stages of aging occurs at times corresponding to the appearance of the ex phase. Strips from sheet were vacuum annealed at 850°C (1560 OF) for about 4 h and cold rolled to a thickness of0.4 mm (0.015 in.). Coupons were prepared from rolled material and solution treated at 800°C (1470 OF) for 90 min in purified helium, then quenched in water, oil or air. Several coupons were solution treated at 900 °C (1650 OF) and water quenched. Aging was done in salt baths held at 250 to 500°C (480 to 930 OF) to 1000 h

14

Ti-13V-11Cr-3AI: TTl diagram


60 1400 Beta transus te'!!R-erature ~ -

I

~

1300 U

so

II:

1100 @ :J

~ 500 \ As solution trea

~"

55

1200 ~

(3/ ---

I

400

2 3 4 Aluminum content, w1%

1100 f-

550

Q)

1000

500L.-_-'-_---I._ _...L-_---''--_-'-_---'

2F

Q)

e

1100 f-

0.05w10/0°2

!I:::>

1200

c. E ~ 600

~600

1200 f! Q) c. E Q)

a+ (3 + TICr2

oxygen content

:::>

U

i

a

~ 650

1400

i! 650

700

1300 !l-

~ 600

---- - -l _//

2F

--+~

P 700 i:::>

aE

Nominal chromium content

750

1400

-,

1000 d 900

--... ...;::: As solulion treated "....Linoo C,

~

540 ~C aging

1300

III

~

s01

!

~

180

.~ 1200

160

0 \

5 1000j--,l"Y-"c---+~--+-425 ~ a Ino----I 25

50 Aging time, h

~

75

140

Cold

U1limaletensile

Thll'lileyield

sIre'Wh

%

MPa

ksi

s1rength (0.2 %l MPa lis!

0 10 20 30 40 50

924 1013 1117 1206 1289 1372 1434 1489 1537

134 147 162 175 187 199 208 216 223

903 951 1013 1103 1193 1268 1337 1399 1482

60 70 80

131 138 147 160 173 184 194 203 215

o'-o

100

-'--25

_

Elongation in50mm(2ln.l,

Reduction ofarea,

%

%

25 17 12 8 6 6 5 4 2

50 42 36 32 28 25 22 22 16

_

........

0

........

50 Aging time, h

LIVE GRAPH

Ti-13V-ll Cr-3AI: Effectof cold work on tensile properties of STA sheet reduction,

o _

i

Click here to view

(a)

540 DC

~ ~

595°C aging 1100

ic

100

75


(b)

Ti~13-11-3:

Effect of solution temperature on hardness. Effect of solution temperature on the annealed and annealed plus 480 °C (900 OF) aged Vickers hardness. Hardnesses shown are averages of five impressions, using a 5-kg load

LIVE GRAPH

1000

Solution temperature, OF 1400 1600 1800 2000

1200

II

I"

II •

>

J: 400 ui III

01

C

~ 350

J:

, .-- I II

Beta transus 720°C

,

./

0

250 500

rl

~

Solution,treated plus aged 100 h at 480°C

I 300

2200

I

500

450

Click here to view

I

-/

t

/

.

Solution treated only, 30 min 700 900 1100 Solution temperature, °c

1300

Previous Page Beta and Near-Beta Alloys I 577

Ti-13-11-3: Effect of working on aging. Effect of warm and cold rolling on longitudinal aged tensile properties

~J

1600 Aging at 480 DC

os 1500 ll.

--- ---

;'

::E £ 1400 0, c ~ 1300

/

•

s

Ql

~ 1100

/

.1.

.I

30 Aging at

220 I

-.-'

"'"

..-- ..---.

V

y

- 5000min

~ 15

c:o :;

Cl

c:

/~

A

5

300

/.

" ",~

o\ -

" "-,

/. /" '/

,

V

'

/

~ ~~ -

~~k'iV-

--------

V

~

'"

/-

£-. p. /

r-,

" ""~~

~~y

2;-

350

LIVE GRAPH (b)

y /' /

iB 10 ['\

1100

1000

I

25

Click here to view

400

450 Temperature,

500

°c

550

600

Beta and Near-Beta Alloys I 591 Ti-15Mo-5Zr: Mechanical properties of hot rolled bar at room temperature Alloy

Uhimate tensile strength ksi MPa

TI-I5Mo-5:lI(a) Ti-15Mo-O.2Pd(a) CPTi(b) TI-6AI-4V(b) Ti-5AI-2Cr-1Fe(b)

961 1118 412 961 1000

Reduction

CJuupy impact

Elongation,

oCarea,

Iougbnea,

%

%

J/em'

Hardn .... HV

25 20 41 13 19

65 55 70 35 40

59 39 176 39 49

283 278 140 330 320

Thmiley\eld

strength (0.2%) MPa ksi

139 162 59 139 145

922 1069 323 892 951

133 155 47 129 138

(a)Solutiontreated.(b)Annealed.Source:Kobe Steel

Ti-15Mo-5Zr: Aging transformation diagram. 9.5 mm (0.35 in.) diameter bar hot rolled at 880°C (1615 OF), 98% reduction. Xray diffraction analysis 1100

600

• !;' 500

i:::l

~

Ol

a.

E

~ 400

• •

J3+a

Ti-15Mo-5Zr: Chemical composition of bar, wire, and sheet Chemical composition, % Fe(a) Zr

H(a)

O(a)

N(a)

0.020

0.20

0.05

0.35

4.5-5.5

Mo

1'1

14.0-16.0

rem

(a)Maximum

1000 u.

... .... ..

J3+ro+a

tJ.

900

tJ. tJ.

800

°

i

~

Ol

a.

E

Ol

I-

J3+ro

..

600

300 10

700

100

1000

10000


Time, min

Ti-15Mo-5Zr-3AI Chemical Composition. See Table for chemical composition. Molybdenum enhances corrosion resistance to reducing atmospheres. Zirconium is added to: (I) further enhance corrosion resistance above that achieved by a single molybdenum addition, (2) suppress 0) transformation to prevent 0) embrittlement, and (3) to improve thermal stability of ~ phase. Zirconium additions of 5% minimum are required to enhance thermal stability. An aluminum addition of 3% is needed to suppress 0) transformation effectively at lower temperatures and longer times. Moreover, aluminum enhances post-aging strength and resistance to oxidation as well

Characteristics Crystal Structure. Body-centered cubic ~ phase is obtained after solution treating in the ~ temperature region and quenching. Close-packed hexagonal ~ phase and 0) phase precipitate during aging above and below 425°C (795 "F), respectively. Compared with Ti-15Mo-5Zr, embrittlement caused by 0) phase does not occur as predominantly because the amount of 0) phase is reduced by the 3% aluminum additions Grain Structure. The grain structure and distribution of phases depend on the thermomechanical history of the material. The grain size obtained by solution treating above the ~ transus generally ranges from approximately 20 to 100 11m Beta Transus. 785°C (1445 OF) Product Forms. Forging billet and bar, hot rolled plate and bar, cold rolled sheet, and cold drawn wire are available: Cold roIled sheet is

available in thicknesses up to O. I mm. The standard cold drawn wire diameter minimum is 1.0 mm

Applications. Ti-15Mo-5Zr-3AI is characterized by high strength, good cold formability, and in particular, high corrosion resistance to reducing atmospheres. Its corrosion resistance is superior to that of Ti-0.2Pd. Ti-15Mo-5Zr-3AI can be used in various applications where many other titanium aIIoys cannot be used. For example, it is a candidate material for sour gas weII plants because of its high strength-to-density ratio and resistance to atmospheric stress-corrosion cracking. It is currently used as an erosion shield material for 1015 mm (40 in.) titanium turbine blades in power plants

Corrosion Properties. Ti-15Mo-5Zr-3AI has high corrosion resistance to reducing atmospheres. Its erosion resistance is somewhat inferior to that of Ti-15Mo-5Zr. However, the strength, ductility, and toughness of Ti15Mo-5Zr-3AI are superior to Ti-15Mo-5Zr, and it is used as an erosion shield as well as Ti-15Mo-5Zr. Stress-corrosion cracking properties in a H2S-saturated solution with 5% NaCI and 0.5% CH3COOH for solution treated and aged samples are shown

Mechanical Properties Tensile Properties. With optimum heat treatment this aIloy can reach a tensile strength of 1470 MPa (213 ksi) with an elongation of 15%. A higher tensile strength of over 1570 MPa (227 ksi) can be obtained by duplex aging.

592/ Heat Treater's Guide: Nonferrous Alloys See Tables for mechanical properties of aged specimens, and for mechanical properties of duplex aged specimens

Fabrication Properties Forming. Ti-15Mo-5Zr-3AI is hot worked or cold worked. Prior to cold working, the material is solution treated to obtain low flow stress and high ductility. Products usually are supplied in the solution treated condition. Solution treatment is carried out alternatively either in the I} temperature field (at 800 to 850°C, or 1470 to 1560 "F) for cold formability, or in the a-I} field at 735 °C (1355 "F) for a good combination of strength and ductility after aging. In the former case, the microstructure consists of a small amount of a phase and recovered I} phase. See Table for effect of solution treatment temperatures on n-value

tion of strength and ductility after aging, the material should be solution treated at735 °C (1355 "F) for 0.5 to 1 h. Water quenching is preferable for cooling after solution treating

Aging. Treatment should be carried out at temperatures of 425

to 500 °C (795 to 930 "F), Maximum strength can be obtained after aging at temperatures of 425 to 450°C (795 to 840 OF), but long times are required. However, age hardening occurs relatively rapidly at temperatures of475 to 500 °C (890 to 930 oF).

To obtain a higher strength, duplex aging is sometimes used. The first aging is carried out at 425°C (795 "F) for a phase to precipitate finely; and the second aging at 475 to 500 °C (890 to 930 "F) is used to accelerate the growth of the a precipitates. See Figures for:

Recommended Heat Treating Practice Solution treatment conditions depend on subsequent product application. When cold formability is required, the material should be solution treated just above the I} transus (785°C, or 1455 OF). To obtain a better combina-

• • • •

Effect of solution treating temperature on tensile properties Effect of solution temperature on STA tensile properties Aging transformation diagrams Amount of alpha phase during aging

Ti-15Mo-5Zr-3AI: Effectof solutiontemperature on tensileproperties. 9.5 mm (0.35 in.) diameter bar hot rolled at 880°C (1615 OF); 98% reduction. Specimens were solution treated for one hour and aged at 500 °C (930 OF) for indicated times

LIVE GRAPH

Solution temperature, OF 1500 1600

Click here to view

1700

1565 1460f· ..·························,·······..······ ..~,,;dele and

depth

oontwnlnation

mils

JlID

mils

JlID

mils

2 8 9 10 14 15

1.0 2.1 2.2 2.3 2.4 3.3

25 53 56 58 62 83

1.1 2.4 2.6 2.7 3.0 3.8

27 61

Transage 129: Composition limits of wrought alloy Compooltloo, wt iii

Element

yttrium

1.7-2.7 0.08 max 0.20 max 0.05 max 0.I5max 1.5-2.5 10.5-12.5 10.0-12.0 0.03 max 0.015 max 0.005 max

Residualelements Each Total TItanium

0.10 max 0.40 max bal

Iron

Duration,

Cooling

h

method

0.3 1 24 24

Fan air cool Waterquench(a) Air cool Air cool

1 24

Fan air cool Air cool Air cool

(a) Waterquenching for heavy sectionfor maximumformability, If aging follows solutionanneal, any convenient cooling rate may be used. (b) Solution treatment and isothermal transformation (STlT)produceshighertoughnessthanSTA.(c) For superiorfatigue resistance

66

68 76 98

Note: From730 to 815°C (1345 to 1500 "F) intergranulardiffusionof oxygen is faster than intragranular.At 870°C (1600 "F), the two rates areabout equal,and oxide dissolutionat the interfaceis fasterthanoxide formation.(a)Interpolatedvalues

Aluminum Carbon

Transage 129: Recommended heat treatments Thmpernlure

'Iemperature

Nitrogen Oxygen TIn Vanadium(a) Zirconium Boron Hydrogen

(a)The vanadium-aluminummasteralloy (nominally 15to 17 W!%aluminum)additionis to be calculated toobtain the nominalvanadiumcontent of 11.5 W!%

Transage 129: Effect of ex case on tensile properties Queocbing

Fan air cool Fan air cool Water Water

Milled!o)

No Yes No Yes

Ultimate tenslle strength MPo ksi

781±6 834±0 788±4 824±2

113.3±0.9 121.0±0.0 14.3±0.6 1l9.5±0.3

ThIL'Jile yield strength MPo ksI

593±16 520±8 365±27 295±14

86.0±2.3 75.4± 1.2 52.9±3.8 42.8±2.0

Elongation,

Reduction

iii

or area, iii

9.0 ± 0.0 18.7± 1.2 13.3±0.6 19.0±0.0

11.6±0.9 33.7±2.7 27.1 ±3.0 39.7

Note: 6.6 mm (0.26in.) plate producedfrom 820 kg (1800 Ib) ingot.Beta solutionannealedat815 °C (l5oo "F), I h. Sand blasted 10 remove oxide scale. Tensiletest valuesgiven are average and standard deviationfor three tests.(a)Milled 0.25 mm (0.010 in.) from surfaces


195

45

LIVE GRAPH

LIVE GRAPH


Click here to view

~40

UTS

/

,.- - _- --0

~

gf 35 Q)

c:

-E,

:::J

a 30

•

~

:::J

o

~ 25

TYS

175

170,1-._ _--'-_ _---L-_ _----'--_ _- - - '_ _----' 1300

1400

1500

1600

Temperature,

:J

20,L._ _-'-_ _--'-_ _-'-_ _-'-_ _--'

1800

1700

1300

OF

1400

1500

1600

Temperature,

1700

1800

OF

(b)

(8)

20

\


\

;;!! 15

§

RA

\

~

01

s 10 Gi

V

----,

Elongation,

of area,

ksi

MPa

ksl

%

%

MPa'liii"

ksl'JiiL

174 184 -10

1138 1213 -76

165 176 -11

7.0 4.0 +3.0

17 7 +10

53.1 55.4 -2.3

48.3 50.4 -2.1

181 174 +7

1200 1138 +62

174 165 +9

7.5 7.0 +0.5

12 17 -5

55.3 52.7 +2.6

50.4 48.0 +2.4

175 164 +11

1131 1069 +62

164 155 +9

9.0 10.0 -1.0

33 33 0

51.1 50.3 +0.8

46.5 45.8 +0.7

Note: Conclusionsfrom thislimitedstudyare thatfor higherstrengthand slightlyhigherfracturetougbness: (1)solutionannealat 815°C (1500 "F) rather thanat 870 °C (1600 "F), (2) firsttemperature age at 565°C (1050 oF) ratherthanat 595°C (1100 "P), and (3)followwithwaterquenchingratherthan air cooling.(a)L,longitudinal;T, transverse


Ti-13V-2.7AI-7Sn-2Zr Commercial Names. Common name. Transage 175; Trade names. Transage 175 and T175 UNS Number. Unassigned Chemical Composition. Transage 175 is an experimental alloy. See Table for chemical compositions of wrought and cast Transage 175

Characteristics Product Forms. The alloy can be produced to all mill product forms Applications. Transage 175 can improve the structural efficiency of and reduce cost-of all applications for titanium alloys. Compared to the most commonly used titanium alloys, it can extend service temperature ranges. Transage 175 exhibits particularly good fatigue resistance in wrought and cast forms. It has demonstrated good endurance limits under various types of fatigue loading and at various temperatures Mechanical Properties. See Tables for typical mechanical properties and for typical tensile properties

Fabrication Properties This age-hardenable, high strength alloy is castable, weldable, forgeable, and extrudable. Castability is rated good.

air cooling for thin sections to be cold formed, or followed by any convenient cooling rate in preparation for age hardening; and (2) solution anneal followed by aging at 425 to 565°C (795 to 1050 "F) depending on strength level desired. For a given aging temperature, the slower the cooling rate from the solution anneal, the lower the yield strength obtained. This type of heat treatment produces yield strength up to 1450 MPa (210 ksi). The annealing temperature required to obtain the lowest strength state is 815°C (1500 OF) for 15 min to 1 h followed by rapid air cool or water quench depending on section size. However, from the standpoint of stress relief, age hardening, per se, eliminates residual stress due to the unique age-hardening mechanism of Transage titanium alloys. Consequently, partial or total age hardening facilitates machining because the workpiece is more stable geometrically as metal is removed. Yield strength can vary from 895 to 1450 MPa (130 to 210 ksi) in inverse relation to age hardening temperature. For a given component, it may be necessary to determine the aging temperature by trial to get a desired combination of strength and ductility and/or toughness. Transage 175 has exceptional hardenability. The alloy readily age hardens to strength levels of 1170 MPa (170 ksi) or higher, following the slow cooling rates imposed by hot isostatic processing facilities and by superplastic forming operations. In steel terms, the ideal round size exceeds 200 mm (8.0 in.). See Tables for typical heat treatments, and for effect of solution temperature. See also Table for tensile properties vs. treatment temperature of cast impeller .

Weld repair capability, by titanium alloy standards, is excellent. Net shape parts can be isothermally forged. Extrusion properties are excellent. In forming sheet, all cold and hot forming methods generally used for titanium alloys are applied. See Table for recommendations for the production of near-net shape and net-shape forgings. See Figure for effect of forging temperatures on mechanical properties. See Table for tensile properties of electron beam welded specimens

Recommended Heat Treating Practice 1\vo types of heat treatments may be applied to Transage 175: (1) solution anneal, preferably at 815°C (1500 OF) for 15 min to 1 h followed by fan

Transage 175: Typical heat treatments STAwrought bar 815°C (1500oF) for I h,coolingrateoptional fromair cool10 waterquenchdepending onsection size,ageal455 °C (850"P) or highertemperature, depending onstrength desired andapplication temperature, for21024 h Castings STA:900°C(1650"P) for2 h, air cool,fanair cool,or forced gascool,age at 540°C(1000oF) for2 h.air cool HIP:900°C (1650oF), 103MPa(15 ksi) for2 h,forcedgascool,ageat540°C (1000"F) for2 h, air cool

Transage 175: Effect offorging temperature on mechanical properties. Tension test properties versus isothermal forging temperature ofa+ ~ preforms upsetto 62% reduction. Specimens were 818 kg (1800 Ib) ingots processed to 160 mm (6.3 in.) round, then cogged to 100 mm (4.0 in.) round at 730°C (1345 OF) for 58% reduction to make a-~ preform stock. Preforms were upset isothermally at various temperatures and 0.42 mm/s (1.0 in.lmin) platen speed. Heat treated at 720°C (1325 OF), 2 h, WO, 480°C (900 OF), 24 h, AC

LIVE GRAPH

LIVE GRAPH

Temperature, OF

Click here to view

1300 1500

140OI-

'" :2

1350

. 0

l:.

o.

1400

1450

1500

I I UTS, radial UTS, tangential TYS, radial TYS, tangential

1300 60 210

~

c

~

....... o. 1:.-"'"

til 1200

.........

190 ~

r---

--

c

UTS

0

..

---

TYS

1100 700

725

750

775

Temperature, DC

e

0

•

800

1350

180 til

'if.

40

0_

RA(

~30

U :::l

o

./ 20

--

10

160 825

o

I:.

o.

'"

-

725

1500

RA, radial RA, tangential Elongation, radial Elongation, tangential

-............

~ -1:.-

~ E\Ongation

o.

700

•

1450

~I'-o-.....

1:.--

170

1400 0

50

200

II.

~ 1300

Click here to view

Temperature, OF

750

-775

Temperature, DC

-

-

•

............ 0

800

825

598/ Heat Treater's Guide: Nonferrous Alloys Transage 175: Effectof solution temperature

Transage 175: Recommendations for the production of near-net-shape and net-shape forgings

RTtensile properties of cast impeller after aging at 540°C (1000 OF), 2 h, AC Ultimatetensile

Thnsileyield

Slnmgth

strength (0.2%) MPa ksi

MPa

ksi

No homogenization(a) 1193 173 1261 183 1193 173 1165 169 1268 184 845°C (1555 oF), 2 h(b) 1152 167.1 1133 164.3 1215 176.3 870 ~C (1600 oF), 2 h(b) 1110 161.0 1211 175.7 1262 183.1 900 °C (1650 oF), 2 h(b) 1202 174.4 1196 173.5 1204 174.7 930°C (1700 oF), 2 h(b) 164.7 1135 1147 166.4 1226 177.9

Reduclion Elongation,

erarea,

%

%

1186 1261 1172 1165 1255

172 183 170 169 182

0.3 0.2 3.9 0.4 0.9

0.8 0.8 9.4 0.0 0.0

1137 1096 1194

164.9 159.0 173.2

3.9 3.5 3.0

5.2 4.8 3.2

Equipment Thmperature of diesand workpiece Platenspeed Solutionheattreatment Temperature Time Coolingrate Heavy sections Light sections Agingtreatment Temperature Time Coolingrate

1195 1235

173.4 179.1

3.1 2.9 3.3

2.4 2.4 3.2

1161 1163 1155

168.5 168.7 167.5

4.1 4.6 4.3

3.2 7.8 5.6

1089 1107 1192

158.0 160.6 172.9

3.1 3.6 3.7

4.0 3.2 3.2

Isolhermalpress 815°C ± 15(1500± 25 oF) 0.21mm1s (0.5 inJmin) 815 °C±15°C (l500±25 oF) 0.5tolh

Fan aircool,or waterquench Aircool 455t054O±5 °C (850to lOoo± 10 oF), dependingon strenglhdesired. Strenglhrange from 1520to 1170MPa (220to 170ksi) 4 h forshort-timestrenglh;24 h for long-timestrenglhat elevated temperatures and agingtemperatures below480°C (900 "F) Aircool

Note: At 815°C (1500"F), Transage175 has a flowstressof 43 MPa (6200psi).The alloywillflow at constantload as long as the load per unit plan areaexceeds the flow stress.If shape is to be net, chemicalmill to removesurfacecontaminationand to meet drawingdimensions

Transage 175: Chemical composition Composillon,

Speclllcatlonrequirements

wt%

(a)Baseline;no homogenization; 815°C (1500"P), 2h, gasfan cool. (b) Plusfurnacecooledto 540 °C (1000 "F), thenremovedfromfurnaceandair cooled.Solutionheat treatedat 815°C (1500"F), 2h, gasfancooledandaged540 °C (1000 "F), 2h,AC

Aluminum Carbon Iron Nitrogen Oxygen Tm

Transage 175: Tensile properties vs. solution treatment temperature of cast impeller. Tensile properties with standard deviation bars for specimens taken from the base of 267 mm (10.5 in.) diameter cast impeller vs. temperature of 2-h solution heat treatments; 900°C (1650 OF) appears to be optimum for solution heat treatment or HIP temperature. Processing: HIP 815 °C (1500 OF), 2 h, 103 MPa (15 ksi), heat treated at 900 °C (1650 OF), 2 h, furnace cooled to 540 °C (1000 OF), then AC, 540°C (1000 OF), 2 h,AC LIVE GRAPH

Vanadium(a) Zirconium Boron Hydrogen yttrium

Residualelements, each Residualelements, total TItanium

'Irsnsage175,wrought

'ftansage175C,caotiugo

2.2-3.2 0.08 max 0.20 max 0.05 max 0.15 max 6.5-7.5 12.0-14.0 1.5-2.5 0.03 max 0.D15max 0.005 max 0.10 max 0.4 bal

2.0-3.0 0.08 max 0.20 max 0.05 max 0.15 max 6.5-7.5 11.0-13.0 1.5-2.5 0.03 max 0.015 max 0.005 max 0.10 max 0.40 max bal

(a)The vanadium-aluminum (nominally15to 17 wt% aluminum)masteralloyadditionis to becalculatedtoobtainthenominalvanadiumcontentof 13.0 wt% for wroughtproductsand 12.0wt% for electrodestockforcastings


Solution treat temperature, OF 1550 1600 1650 1700

Transage 175: Tensile properties of electron-beam welded specimens

1300

~

/ ~

1200

'~ V.

~

£ C, c

~

en

.L

180

0

1380 30

230 ';;; sc

s::

220

g.

~ 1ij

210

-g Cl «

~ 20

~

g

"0 "0 CD

~10

200

• ~

r---

.

r---

°

Reduction of area

.~

n

° ~

\ Elongation (25 mm)

0

o

190 760 780 800 Solution temperature, °c


240

Yield strength

c/

Solution temperature, OF 1400 1420 1440 1460 1480

820

740

(b)

i

I_

!~ 0


820


Ti-8V-5Fe-1 AI: Effect of solution treatment and aging on tensile properties. 14 mm (0.625 in.) diam bar. solution treated 0.5 h, water quenched, aged 2 h, air cooled; room-temperature tests

LIVE GRAPH


Aging temperature, of 940 950 960 970 980

990 1000

930

1650

Click here to view

Aging temperature, of 940 950 960 970 980

990 1000

1700 240

230 III

15501t-----=.......± : - - - - - t - - - - - - - - t

~

220

~

~

~

~

~ 1450

210 ~

o

00

~

~

200 ~

m

>= 1350 - - 775 °c ----t---_=___~ 760°C 745°C 1250L..-

230

~

---l..

~

'lij

~

5E 1400

~

220 ~

c: ~ 1500

190

----I

495

~ 16001t------""k----t--------t

210

s

~ =

5

--775°C 7600C 745°C

"

200

...J

510 525 Aging temperature, °c

510 525 Aging temperature, °c

540

(8)

(b) 930

Aging temperature, of 950 960 970 980

940

990

1000

930

20

60 --7750C 760°C - . 745 °c E

'" l!!

120 'lii

800

E :::> E

100

'iii

::;

'iii

::;

600 80 60

400 10 3

10 4

10 5

106

10 7

108

Cycles to failure, N, (a) 1200

LIVE GRAPH

3 - - - Ti-3AI-8V-6Cr-4Zr-4Mo(Bela-C) 10 - - Ti-10V-2Fe-3AI

Click here to view «l CL

1000

-----------

'\

::;

ui

'" ~

800

160

- - - - - 3,3

140 ]I

gj

-----3,2 -----3.1

l!! 120 'lii

E :::> E

100

'iii

::;

'iii

::;

600 80 400 10 3

60 10 4

10 5

106

Cycles to failure, M (b)

E :::> E

107

108

Cast and PIM Titanium 1605

Compositions andcomparisons of cast titanium alloys Alloy

TI-6Al-4V TI-6Al-4V EU(b)(cO Commercially puretitanium (grade2) TI-6Al-2Sn-4Zr-2Mo TI-6Al-2Sn-4Zr-6Mo TI-5Al-2.5Sn TI-3Al-8V-6Cr-4Zr-4Mo (Beta-C) TI-15V-3Al-3Cr-3Sn (11-15-3) TI-11oo IMl-834 Thtal

Eotimated relatlwwe orcastings

85% 1% 6% 7%

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