Click to View Calculation Example
Example 2.1: Liquid Discharge through a Hole in a Tank Input Data: Tank pressure abov...
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Click to View Calculation Example
Example 2.1: Liquid Discharge through a Hole in a Tank Input Data: Tank pressure above liquid: Pressure outside hole: Liquid density: Liquid level above hole: Hole diameter: Excess Head Loss Factors: Entrance: Exit: Others: TOTAL:
0.1 barg O barg 490 kg/m**3 2m 10 mm 0.5 1 O 1.5
Calculated Results: Hole area:
7.9E-05 m**2
Equation terms: Pressure term: Height term: Velocity coefficient: Exit velocity: Mass flow:
I
-20.4082 m**2/s**2 -19.6 m**2/s**2 1.25 5.7 m/s 0.22 kg/s
Figure 2.8. Spreadsheet output for Example 2.1: Liquid discharge through a hole in the tank.
Example 2.2: Liquid Trajectory from a Hole. Consider again Example 2.1. A stream of liquid discharging from a hole in a tank will stream out of the tank and impact the ground at some distance away from the tank. In some cases the liquid stream could shoot over any diking designed to contain the liquid. (a) If the hole is 3 m above the ground, how far will the stream of liquid shoot away from the tank? (b) At what point on the tank will the maximum discharge distance occur? What is this distance? Solution: (a) The geometry of the tank and the stream is shown in Figure 2.9. The distance away from the tank the liquid stream will impact the ground is given by s = v2t
FIGURE 2.9. Tank geometry for Example 2.2.
(2.1.32)
Click to View Calculation Example
Example 2.2a: Liquid Trajectory from a Hole Input Data: Liquid velocity at hole: Height of hole above ground:
5.7 m/s 3m
Calculated Results: Time to reach ground: Horizontal distance from hole:
I
0.78 s 4.46 m
I |
FIGURE 2.10. Spreadsheet output for Example 2.2a: Liquid trajectory from a hole. where s is the distance (length), V2 is the discharge velocity (distance/time), and t is the time (time). The time, £, for the liquid to fall the distance h, is given by simple acceleration due to gravity, t=fikTg
(2.1.33)
These two equations are implemented in the spreadsheet shown in Figure 2.10. The velocity is obtained from Example 2.1. The horizontal distance the stream will impact the ground is 4.46 m away from the base of the tank. Solution (b) The solution to this problem is found by solving Eq. (2.1.10) for V2. The algebraic result is substituted into Eq. (2.1.32), along with Eq. (2.1.33). The resulting equation for s is differentiated with respect to h. The expression is set to zero to determine the maximum, and solved for h. The result is
*.l(w+«i] A SP )
0.025 in. thickness, 10 percent. b Applicable, providing ST dimension is > 3.000 inches. c Average, values may vary with test direction.
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MIL-HDBK-5H 1 December 1998
I n t er act i ve T ab l e - D e s ig n P rop er t i es
Interacti ve T ab le - T yp i c a l P r op ert i es
Table 5.3.2.0(b2). Design Mechanical and Physical Properties of Ti-8Al-1Mo-1V Sheet and Plate Specification . . . . . . . .
AMS 4916, MIL-T-9046, and Comp. A-4
Form . . . . . . . . . . . . . . Condition . . . . . . . . . .
Sheet
Plate Duplex Annealed
Thickness, in. . . . . . . . 0.015-0.024 0.025-0.1875 0.1875-0.500 0.501-1.000 1.001-2.000 2.001-4.000 Basis . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ............... LT . . . . . . . . . . . . . . Fty, ksi: L ............... LT . . . . . . . . . . . . . . Fcy, ksi: L ............... LT . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . . . (e/D = 2.0) . . . . . . . Fbry, ksi: (e/D = 1.5) . . . . . . . (e/D = 2.0) . . . . . . . e, percent: L ............... LT . . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . Ec, 103 ksi . . . . . . . . . G, 103 ksi . . . . . . . . . µ ................ Physical Properties: , lb/in.3 . . . . . . . . . . C, Btu/(lb)(F) . . . . . K and . . . . . . . . . . . a
S
S
S
S
S
S
135 135
135 135
130 130
130 130
125 125
120 120
120 120
120 120
120 120
120 120
115 115
110 110
126 126 84
126 126 84
... ... ...
... ... ...
... ... ...
... ... ...
223 269
223 269
... ...
... ...
... ...
... ...
174 191
174 191
... ...
... ...
... ...
... ...
8 8
10 10
10 10
10 10
10 10
8 8
17.5a 18.0a 6.7 0.32 0.158 0.12 See Figure 5.3.2.0
Average, L and LT; values may vary with test direction.
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MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es
Interacti ve T ab le - T yp i c a l P r op ert i es
Table 5.3.2.0(c). Design Mechanical and Physical Properties of Ti-5Al-2.5Sn Bar and Forging
Specification . . . . . . . . . . . . Form . . . . . . . . . . . . . . . . . . Condition . . . . . . . . . . . . . . Thickness or diameter, in. . . Basis . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ................... LT . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . . Fty, ksi: L ................... LT . . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . . Fcy, ksi: L ................... LT . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . Fbry, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . e, percent: L ................... LT . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . E, 103, ksi . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . µ .................... Physical Properties: , lb/in.3 . . . . . . . . . . . . . . C, Btu/(lb)(F) . . . . . . . . . K and . . . . . . . . . . . . . . . a b c d
MIL-T-9047 Bar Duplex annealed 2.501-4.000a < 2.500a S S
AMS 4973 Forging Solution treated and stabilized < 2.499 2.500-4.000 S S
130 130b ...
120 120b 120b
130 130c ...
120 120 120
120 120b ...
110 110b 110b
120 120c ...
110 110 110
... ... ... ...
... ... ... ...
... ... ... ...
... ... ... ...
... ...
... ...
... ...
... ...
... ...
... ...
... ...
... ...
10 10b ...
10 10b 8b
10 10c ...
10 10 10
17.5d 18.0d 6.7 0.32 0.158 0.12 See Figure 5.3.2.0
Maximum of 16 square-inch cross-sectional area. Applicable, providing LT or ST dimension is > 3.000 inches. Applicable, providing LT dimension is > 2.500 inches. Average, values may vary with test direction.
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.2.1.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of single-annealed Ti-8Al-1Mo-1V alloy sheet.
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.2.1.4. Effect of temperature on the tensile and compressive moduli (E and Ec) of Ti-8Al-1Mo-1V alloy sheet.
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse
.5 -hr exposure
160 RT
120
Stress, ksi
400 F 550 F
80
Ramberg - Osgood n (RT) = 33 n (400 F) = 50 n (500 F) = 50 TYPICAL
40
0 0
4
8
12
16
20
24
Strain, 0.001 in./in.
Figure 5.3.2.1.6(a). Typical tensile stress-strain curves for single-annealed Ti-8Al-1Mo-1V alloy sheet at room and elevated temperatures.
VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse
1/2 -hr exposure
RT
160
120
RT
550 F
Stress, ksi
550 F
80
Ramberg - Osgood n (RT) = 50 n (550 F) = 50
40
TYPICAL
0 0
4
8
12
16
20
24
Strain, 0.001 in./in. 3 Compressive Tangent Modulus, 10 ksi
Figure 5.3.2.1.6(b). Typical compressive stress-strain and compressive tangentmodulus curves for single-annealed Ti-8Al-1Mo-1V alloy sheet at room and elevated temperatures.
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.2.2.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of duplex-annealed Ti-8Al-1Mo-1V alloy sheet.
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse .5 -hr exposure
160
RT
Stress, ksi
120 400 F
550 F
80
Ramberg - Osgood n (RT) = 16 n (400 F) = 32 n (550 F) = 24 40
TYPICAL
0 0
4
8
12
16
20
24
Strain, 0.001 in./in.
Figure 5.3.2.2.6(a). Typical tensile stress-strain curves for duplex-annealed Ti-8Al-1Mo-1V alloy sheet at room and elevated temperatures.
VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse .5 -hr exposure
160
RT
RT
Stress, ksi
120 550 F
550 F
80
Ramberg - Osgood n (RT) = 50 n (500 F) = 22
40
TYPICAL
0 0
4
8
12 16 Strain, 0.001 in./in. 3 Compressive Tangent Modulus, 10 ksi
20
24
Figure 5.3.2.1.6(b). Typical compressive stress-strain and compressive tangentmodulus curves for duplex-annealed Ti-8Al-1Mo-1V alloy sheet at room and elevated temperatures.
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.2.2.8(a). Best-fit S/N curves for unnotched, duplex annealed T1-8Al-1Mo-1V sheet at room temperature, long transverse direction.
Correlative Information for Figure 5.3.2.2.8(a) Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - RT Environment - Air
Product Form: Sheet, 0.050-inch thick Properties:
TUS, ksi
TYS, ksi
147.2
135.6
Temp.,F RT
No. of Heats/Lots: 1
Specimen Details: Unnotched 0.750-inch net width
Equivalent Stress Equation: Surface Condition: HNO3/HF pickled References:
Log Nf = 10.57-3.46 log (Seq-66.7) Seq = Smax (1-R)0.61 Standard Error of Estimate = 0.47 Standard Deviation in Life = 0.81 R2 = 66.7%
5.3.2.2.8(a) and (b)
Sample Size = 24 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.2.2.8(b). Best-fit S/N curves for notched, Kt = 2.6, duplex annealed Ti-8Al-1Mo-1V sheet at room temperature, long transverse direction.
Correlative Information for Figure 5.3.2.2.8(b) Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - RT Environment - Air
Product Form: Sheet, 0.050-inch thick Properties:
TUS, ksi
TYS, ksi
147.2
135.6
Temp.,F RT Unnotched
No. of Heats/Lots: 1 Specimen Details: Notched, hole type, Kt = 2.6 1.500-inch, gross width 1.250-inch, net width 0.250-inch, diameter hole
Equivalent Stress Equation: Log Nf = 14.49-5.90 log (Seq-12.7) Seq = Smax (1-R)0.55 Standard Error of Estimate = 0.33 Standard Deviation in Life = 1.10 R2 = 90.9%
Surface Condition: HNO3/HF pickled References:
5.3.2.2.8(a) and (b)
Sample Size = 26 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.2.2.8(c). Best-fit S/N curves for unnotched duplex annealed T1-8Al-1Mo-1V sheet at 400°F, long transverse direction.
Correlative Information for Figure 5.3.2.2.8(c) Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - 400F Environment - Air
Product Form: Sheet, 0.050-inch thick Properties:
TUS, ksi
TYS, ksi
119.5
100.8
Temp.,F 400
No. of Heats/Lots: 1
Specimen Details: Unnotched 0.750-inch net width
Equivalent Stress Equation: Surface Condition: HNO3/HF pickled References:
Log Nf = 8.30-2.53 log (Seq-73.9) Seq = Smax (1-R)0.74 Standard Error of Estimate = 0.38 Standard Deviation in Life = 0.87 R2 = 80.9%
5.3.2.2.8(a) and (b)
Sample Size = 23 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.2.2.8(d). Best-fit S/N curves for notched, Kt = 2.6, duplex annealed Ti-8Al-1Mo-1V sheet at 400°F, long transverse direction.
Correlative Information for Figure 5.3.2.2.8(d) Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - 400F Environment - Air
Product Form: Sheet, 0.050-inch thick Properties:
TUS, ksi
TYS, ksi
119.5
100.8
Temp.,F 400 Unnotched
No. of Heats/Lots: 1 Specimen Details: Notched, hole type, Kt = 2.6 1.500-inch, gross width 1.250-inch, net width 0.250-inch, diameter hole
Equivalent Stress Equation: Log Nf = 13.39-5.68 log (Seq-18.7) Seq = Smax (1-R)0.46 Standard Error of Estimate = 0.41 Standard Deviation in Life = 1.16 R2 = 87.2%
Surface Condition: HNO3/HF pickled References:
5.3.2.2.8(a) and (b)
Sample Size = 20 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.2.2.8(e). Best-fit S/N curves for unnotched duplex anneled Ti-8Al-1Mo-1V sheet at 650°F, long transverse direction.
Correlative Information for Figure 5.3.2.2.8(e) Product Form: Sheet, 0.050-inch thick Properties:
TUS, ksi
TYS, ksi
110.2
86.8
Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - 650F Environment - Air
Temp.,F 650
No. of Heats/Lots: 1
Specimen Details: Unnotched 0.750-inch, net width
Equivalent Stress Equation: Surface Condition: HNO3/HF pickled References:
Log Nf = 9.83-3.66 log (Seq-73) Seq = Smax (1-R)0.78 Standard Error of Estimate = 0.88 Standard Deviation in Life = 1.18 R2 = 44.3%
5.3.2.2.8(a) and (b)
Sample Size = 20 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.2.2.8(f). Best-fit S/N curves for notched, Kt = 2.6, duplex annealed Ti-8Al-1Mo-1V sheet at 650°F, long transverse direction.
Correlative Information for Figure 5.3.2.2.8(f) Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - 650F Environment - Air
Product Form: Sheet, 0.050-inch thick Properties:
TUS, ksi
TYS, ksi
110.2
86.8
Temp.,F 650 Unnotched
No. of Heats/Lots: 1 Specimen Details: Notched, hole type, Kt = 2.6 1.500-inch, gross width 1.250-inch, net width 0.250-inch, diameter hole
Equivalent Stress Equation: Log Nf = 10.16-3.88 log (Seq-23) Seq = Smax (1-R)0.69 Standard Error of Estimate = 0.38 Standard Deviation in Life = 0.65 R2 = 66.0%
Surface Condition: HNO3/HF pickled References:
5.3.2.2.8(a) and (b)
Sample Size = 22 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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MIL-HDBK-5H 1 December 1998 5.3.3 Ti-6Al-2Sn-4Zr-2Mo 5.3.3.0 Comments and Properties — Ti-6Al-2Sn-4Zr-2Mo is a near-alpha titanium composition developed for improved elevated-temperature performance. The alloy has a titanium-aluminum base that is solid solution strengthened by additions of tin and zirconium. Molybdenum improves both room and elevated temperature strength, creep and thermal stability. Introduction of this alloy initially met the requirements for certain advanced performance gas turbine engine applications. Some of the more recent applications, however, require better creep strength than the alloy initially provided. Development work showed that a small addition of silicon, approximately 0.08 percent, substantially improved the creep strength of the alloy without significantly affecting the thermal stability. The alloy is creep resistant and relatively stable to about 1050F. Creep and thermal stability of the alloy are further enhanced by solution treating high in the alpha-beta phase field. The alloy is available in bar, billet, plate, sheet, strip, and extrusions. Manufacturing Conditions — Forging of Ti-6Al-2Sn-4Zr-2Mo at temperatures below the beta transus temperature is recommended. For optimum creep properties beta forging or a modification of it is recommended with some loss in ductility to be expected. Elevated temperatures may be used for severe sheet forming operations while room-temperature forming may be used for mild contouring. Stress relief annealing may be combined with a final hot-sizing operation. The material can be welded using TIG or MIG fusion processes to achieve 100 percent joint efficiencies but with limited weld zone ductility. As in welding any titanium alloy, shielding from atmospheric contamination is required except for spot or seam welding. Environmental Considerations — Ti-6Al-2Sn-4Zr-2Mo is somewhat more resistant to hot-salt cracking than either Ti-8Al-1Mo-1V or Ti-6Al-4V alloys. The material is marginally susceptible to aqueous chloride solution stress-corrosion cracking. Surface oxides formed during exposure to service temperature (~950F) do not adversely affect properties. Under certain conditions, titanium, when in contact with cadmium, silver, mercury, or certain of their compounds, may become embrittled. Refer to MIL-S-5002 and MIL-STD-1568 for restrictions concerning applications with titanium in contact with these metals or their compounds. Heat Treatment — Several different annealing treatments, which are described below, are available for Ti-6Al-2Sn-4Zr-2Mo. For sheet and strip: Duplex Anneal:
1650F for ½ hour, air cool, followed by 1450F for ¼ hour, and air cool.
Triplex Anneal: 1650F for ½ hour, air cool, followed by 1450F for ¼ hour, air cool, followed by 1100F for 2 hours and air cool. For plate: Duplex Anneal: 1650F for 1 hour, air cool, followed by 1100F for 8 hours and air cool. Triplex Anneal: 1650F for ½ hour, air cool, followed by 1450F for ¼ hour, air cool, followed by 1100F for 2 hours and air cool. For bars and forgings: Duplex Anneal: Solution anneal 25 to 50F below beta transus temperature for 1 hour, air cool or faster, followed by 1100F for 8 hours and air cool.
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MIL-HDBK-5H 1 December 1998
Table 5.3.3.0(a). Material Specifications for Ti-6Al-2Sn-4Zr-2Mo
Specification MIL-T-9046 AMS 4975 AMS 4976 AMS 4919
Form Sheet and strip Bar Forging Sheet, strip, and plate
Specifications and Properties — Material specifications for Ti-6Al-2Sn-4Zr-2Mo are given in Table 5.3.3.0(a). Room-temperature mechanical and physical properties for Ti-6Al-2Sn-4Zr-2Mo are presented in Table 5.3.3.0(b) and (c). The effect of temperature on physical properties is shown in Figure 5.3.3.0. 5.3.3.1 Single, Duplex,and Triplex Annealed — Room and elevated temperature property curves are shown in Figures 5.3.3.1.1, 5.3.3.1.2, and 5.3.3.1.4. Typical stress-strain curves at room and elevated temperatures are shown in Figures 5.3.3.1.6(a) and (b). Full range stress-strain curves at room and elevated temperatures are shown in Figure 5.3.3.1.6(c).
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I n t er act i ve T ab l e - D e s ig n P rop er t i es
Interacti ve T ab le - T yp i c a l P r op ert i es
Table 5.3.3.0(b). Design Mechanical and Physical Properties of Ti-6Al-2Sn-4Zr-2Mo Supercedes page 5-45 of MIL-HDBK-5H
Specification . . . . . . . . . . .
AMS 4919
AMS-T-9046, Comp. AB-4
Form . . . . . . . . . . . . . . . . .
Sheet
Condition . . . . . . . . . . . . . .
Duplex annealed #0.046
Thickness or diameter, in. . Basis . . . . . . . . . . . . . . . . .
a b c d e
0.094-0.140
0.141-0.187
#0.187
A
B
A
B
A
B
A
B
Sa
135b 135b
143 143
135b 135b
143 143
135b 135b
143 143
135b 135b
143 143
145 145
125c 125c
136 134
125c 125c
136 134
125c 125c
136 134
125c 125c
136 134
135 135
132 132 ...
142 142 ...
132 132 ...
142 142 ...
132 132 ...
142 142 ...
132 132 ...
142 142 ...
... ... ...
195 217
206 230
205 243
217 258
214 266
227 282
219 279
232 295
... ...
171 202
183 217
171 202
183 217
171 202
183 217
171 202
183 217
... ...
8e 8e
... ...
e e
... ...
10 10
... ...
10 10
... ...
e e
E, 103 ksi . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . F ..................
16.5 18.0 6.2 0.32
Physical Properties: ω, lb/in.3 . . . . . . . . . . . . . . C, K and α . . . . . . . . . . . .
0.164 See Figure 5.3.3.0
S-basis values are representative of test specimens excised from duplex annealed material and thermally treated to triplex annealed condition in a laboratory furnace. S-basis. The rounded T99 values are as follows: Ftu(L<) = 139 ksi. S-basis. The rounded T99 values are as follows: Fty(L) = 131 ksi and Fty(LT) = 129 ksi. Bearing values are “dry pin” values per Section 1.4.7.1. 8% for 0.025 through 0.062 inch and 10% for >0.062 inch.
MIL-HDBK-5H, Change Notice 1 1 October 2001
5-45
Mechanical Properties: Ftu, ksi: L .................. LT . . . . . . . . . . . . . . . . . . Fty, ksi: L .................. LT . . . . . . . . . . . . . . . . . . Fcy, ksi: L .................. LT . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . Fbrud, ksi: (e/D=1.5) . . . . . . . . . . . . (e/D=2.0) . . . . . . . . . . . . Fbryd, ksi: (e/D=1.5) . . . . . . . . . . . . (e/D=2.0) . . . . . . . . . . . . e, percent (S-basis): L .................. LT . . . . . . . . . . . . . . . . . .
0.047-0.093
Triplex annealed
MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es
Interacti ve T ab le - T yp i c a l P r op ert i es
Table 5.3.3.0(c). Design Mechanical and Physical Properties of Ti-6Al-2Sn-4Zr-2Mo
Specification...............................
AMS 4975
AMS 4976
Form...........................................
Bar
Forging
Condition....................................
STA (Duplex annealed)
STA (Duplex annealed)
Cross-Sectional area, in.2...........
16
9
Thickness, or diameter, in..........
3.000
3.000
Basis........................................... Mechanical Properties: Ftu, ksi: L............................................ LT.......................................... ST.......................................... Fty, ksi: L............................................ LT.......................................... ST.......................................... Fcy, ksi: L............................................ LT.......................................... ST.......................................... Fsu, ksi...................................... Fbru, ksi: (e/D=1.5)............................... (e/D=2.0)............................... Fbry, ksi: (e/D=1.5)............................... (e/D=2.0)............................... e, percent(S basis): L............................................ LT.......................................... ST.......................................... RA, percent (S basis): L............................................ LT.......................................... ST..........................................
A
B
S
130a 130b 130b
144 ... ...
130 130b 130b
120a 120b 120b
131 ... ...
120 120b 120b
... ... ... ...
... ... ... ...
... ... ... ...
... ...
... ...
... ...
... ...
... ...
... ...
10 10b 10b
... ... ...
10 10b 10b
25 25b 25b
... ... ...
25 25b 25b
E, 103 ksi................................. Ec, 103 ksi................................ G, 103 ksi................................. ...............................................
16.5 18.0 6.2 0.32
Physical Properties: , lb/in.3................................... C, K, and ..............................
0.164 See Figure 5.3.3.0
a S basis. The rounded T99 values are as follows: Ftu(L) = 138 ksi and Fty(L) = 125 ksi. b S basis. Applicable providing transverse dimension is 2.500 in.
REPRINTED WITHOUT CHANGE.
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.3.0. Effect of temperature on the physical properties of Ti-6Al-2Sn-4Zr-2Mo alloy.
VIEW INTERACTIVE GRAPH
Figure 5.3.3.1.1. Effect of temperature on the tensile ultimate strength (Ftu) and tensile yield strength (Fty) of duplex- and triplex-annealed Ti-6Al-2Sn-4Zr-2Mo (all products).
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.3.1.2. Effect of temperature on the compressive yield strength (Fcy) of duplex annealed Ti-6Al-2Sn-4Zr-2Mo alloy sheet.
VIEW INTERACTIVE GRAPH
Figure 5.3.3.1.4. Effect of temperature on the tensile and compressive moduli (E and Ec) of duplex-annealed Ti-6Al-2Sn-4Zr-2Mo alloy.
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH 200 Longitudinal .5 -hr exposure 160 RT
Stress, ksi
120
900 F
80 Ramberg - Osgood n (RT) = 34 n (900 F) = 10 TYPICAL
40
Thickness = 1.125 - 1.250 in.
0 0
4
8
12
16
20
24
Strain, 0.001 in./in.
Figure 5.3.3.1.6(a). Typical tensile stress-strain curves for duplex-annealed Ti-6Al-2Sn-4Zr-2Mo alloy bar at various temperatures.
VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse .5 -hr exposure
160
RT
Stress, ksi
120 900 F
80 Ramberg - Osgood n (RT) = 35 n (900 F) = 12 40
TYPICAL Thickness = 0.048 - 0.085 in.
0 0
4
8
12
16
20
24
Strain, 0.001 in./in.
Figure 5.3.3.1.6(b). Typical tensile stress-strain curves for duplex- and triplexannealed Ti-6Al-2Sn-4Zr-2Mo alloy sheet at various temperatures.
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MIL-HDBK-5H 1 December 1998
VIEW INTERACTIVE GRAPH
Figure 5.3.3.1.6(c). Typical tensile stress-strain curves (full-range) for duplexannealed Ti-6Al-2Sn-4Zr-2Mo alloy sheet at room and elevated temperatures.
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5.4 ALPHA-BETA TITANIUM ALLOYS The alpha-beta titanium alloys contain both alpha and beta phases at room temperature. The alpha phase is similar to that of unalloyed titanium but is strengthened by alpha stabilizing additions (e.g., aluminum). The beta phase is the high-temperature phase of titanium but is stabilized to room temperature by sufficient quantities of beta stabilizing elements as vanadium, molybdenum, iron, or chromium. In addition to strengthening of titanium by the alloying additions, alpha-beta alloys may be further strengthened by heat treatment. The alpha-beta alloys have good strength at room temperature and for short times at elevated temperature. They are not noted for long-time creep strength. With the exception of annealed Ti-6Al-4V, these alloys are not recommended for cryogenic applications. The weldability of many of these alloys is poor because of the two-phase microstructure. However, some of them can be welded successfully with special precautions. 5.4.1 TI-6AL-4V 5.4.1.0 Comments and Properties — Ti-6Al-4V is available in all mill product forms as well as castings and powder metallurgy forms. It can be used in either the annealed or solution treated plus aged (STA) conditions and is weldable. Useful temperature range is from -320 to 750F. For maximum toughness, Ti-6Al-4V should be used in the annealed or duplex-annealed conditions whereas for maximum strength, the STA condition is used. The full strength potential for this alloy is not available in sections greater than 1 inch. Manufacturing Considerations — Ti-6Al-4V alloy may be forged above the beta transus temperature using procedures to promote a high toughness material. The material is routinely finished below beta transus temperature for good combinations of fabricability, strength, ductility, and toughness. Elevated temperatures are usually used for form flat-rolled products although extensive forming may be accomplished at room temperature. Flat-rolled products are usually formed and used in the annealed condition although some forming in the STA condition is possible. This alloy can be spot welded and is being fusion welded extensively in certain applications. Established titanium-welding techniques must be employed and special design considerations may be involved in fusion weldments. Stress-relief annealing after welding is recommended. Environmental Considerations — Ti-6Al-4V can withstand prolonged exposure to temperatures up to 750F without loss of ductility. Its toughness in the annealed condition is adequate at temperatures down to -320F. (A special low interstitial grade may be used down to -423F.) Ti-6Al-4V is resistant to hot-salt stress corrosion to about its maximum use temperature depending on exposure time and exposure stress. The material is marginally susceptible to aqueous chloride solution stress corrosion, but is considered to have good resistance to this reaction compared with other commonly used alloys. Under certain conditions, titanium, when in contact with cadmium, silver, mercury, or certain of their compounds, may become embrittled. Refer to MIL-S-5002 and MIL-STD-1568 for restrictions concerning applications with titanium in contact with these metals or their compounds. Heat Treatment — This alloy is commonly specified in either the annealed condition or in the fully heat-treated condition. Annealing requires 1 hour at 1300F followed by furnace cooling if maximum ductility is required. The specified fully heat-treated, or solution-treated and aged condition for sheet is as follows: Solution treat at 1700F for 5 to 25 minutes, quench in water.
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MIL-HDBK-5H 1 December 1998 Age at 975F for 4 to 6 hours, air cool. For bars and forgings: Solution treat at 1700F for 1 hour, quench in water. Age at 1000F for 3 hours, air cool. Specifications and Properties — Some material specifications for Ti-6Al-4V are shown in Table 5.4.1.0(a). Room-temperature mechanical properties for Ti-6Al-4V are shown in Tables 5.4.1.0(b) through (g). The effect of temperature on physical properties is shown in Figure 5.4.1.0. Table 5.4.1.0(a) Material Specifications for Ti-6Al-4V Specification MIL-T-9046 MIL-T-9047 AMS 4934 AMS 4935 AMS 4967 AMS 4928 AMS 4911 AMS 4920 AMS 4962
Form Sheet, strip, and plate Bar Extrusion Extrusion Bar Bar and die forging Sheet, strip, and plate Die forging Investment casting
5.4.1.1 Annealed Condition — Elevated temperature curves for annealed Ti-6Al-4V are shown in Figures 5.4.1.1.1 through 5.4.1.1.5. Typical stress-strain curves at several temperatures are shown in Figures 5.4.1.1.6(a) through (c). Typical full-range stress-strain curves at room temperature are shown in Figure 5.4.1.1.6(d). Unnotched and notched fatigue data are shown in Figures 5.4.1.1.8(a) through (g). Fatigue crack-propagation data for plate are shown in Figure 5.4.1.1.9. 5.4.1.2 Solution-Treated and Aged Condition — Elevated temperature curves for solutiontreated and aged alloy are shown in Figures 5.4.1.2.1 through 5.4.1.2.4. Typical tensile and compressive stress-strain and tangent-modulus curves are shown in Figures 5.4.1.2.6(a) through (g). Typical full-range stress-strain curves at several temperatures up to 1000F are shown in Figure 5.4.1.2.6(h). A nomograph of typical creep properties of solution-treated and aged sheet for the temperature range 600F through 800F is shown in Figure 5.4.1.2.7. Fatigue data at room and elevated temperatures are shown in Figures 5.4.1.2.8(a) through (i).
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MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es
Interacti ve T ab le - T yp i c a l P r op ert i es
Table 5.4.1.0(b). Design Mechanical and Physical Properties of Ti-6Al-4V Sheet, Strip, and Plate
Specification . . . . . . . .
AMS 4911 and MIL-T-9046, Comp. AB-1
Form . . . . . . . . . . . . . .
Sheet
Condition . . . . . . . . . .
Plate
Sheet, strip, and plate
Annealed
Solution treated and aged 2.0014.000
0.1875
0.18750.750
0.7511.000
1.0012.000
B
S
S
S
S
S
130a 130a
135 138
130 130
160 160
160 160
150 150
145 145
131 131
120 120a
125 131
120 120
145 145
145 145
140 140
135 135
138 141 90
124 130 79
129 142 84
124 130 79
154 162 100
150 ... 93
145 ... 87
... ... ...
213b 221b 272b 283b
206b 260b
214b 276b
206b 260b
236 286
248 308
233 289
... ...
171b 178b 208b 217b
164b 194b
179b 212b
164b 194b
210 232
210 243
203 235
... ...
10 10
... ...
10 10
5d 5d
8 8
6 6
6 6
Thickness, in. . . . . . . .
0.1875
Basis . . . . . . . . . . . . . .
A
B
A
134 134
139 139
126 126 133 135 87
Mechanical Properties: Ftu, ksi: L ............. LT . . . . . . . . . . . . Fty, ksi: L ............. LT . . . . . . . . . . . . Fcy, ksi: L ............. LT . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . (e/D = 2.0) . . . . . Fbry, ksi: (e/D = 1.5) . . . . . . (e/D = 2.0) . . . . . . e, percent (S-basis): L ............. LT . . . . . . . . . . . .
MIL-T-9046, Comp. AB-1
8c 8c
... ...
0.1875-2.000
E, 103 ksi . . . . . . . . . Ec, 103 ksi . . . . . . . . G, 103 ksi . . . . . . . . . µ ................
16.0 16.4 6.2 0.31
Physical Properties: , lb/in.3 . . . . . . . . . C, K, and . . . . . . .
0.160 See Figure 5.4.1.0
a The rounded T99 values are higher than specification values as follows: Ftu(L) = 131 ksi, Ftu(LT) = 132 ksi, and Fty(LT) = 123 ksi. b Bearing values are “dry pin” values per Section 1.4.7.1. c 8%—0.025 to 0.062 in. and 10%—0.063 in. and above. d 5%—0.050 in. and above; 4%—0.033 to 0.049 in. and 3%—0.032 in. and below.
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I n t er act i ve T ab l e - D e s ig n P rop er t i es
Interacti ve T ab le - T yp i c a l P r op ert i es
Table 5.4.1.0(c1). Design Mechanical and Physical Properties of Ti-6Al-4V Bar Specification . . . . . . . . . . . . .
AMS 4928
Form . . . . . . . . . . . . . . . . . . . .
Bar
Condition . . . . . . . . . . . . . . . .
Annealed
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