2. (15 points) The stress pattern shown in the figure is repeatedly applied to an unnotched member of titanium alloy Ti-

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2 15 Points The Stress Pattern Shown In The Figure Is Repeatedly Applied To An Unnotched Member Of Titanium Alloy Ti 1 (28.33 KiB) Viewed 59 times

2 15 Points The Stress Pattern Shown In The Figure Is Repeatedly Applied To An Unnotched Member Of Titanium Alloy Ti 2 (40.35 KiB) Viewed 59 times

2 15 Points The Stress Pattern Shown In The Figure Is Repeatedly Applied To An Unnotched Member Of Titanium Alloy Ti 3 (23.52 KiB) Viewed 59 times

2. (15 points) The stress pattern shown in the figure is repeatedly applied to an unnotched member of titanium alloy Ti-6Al-4V (solution treated and aged) of Table 9.1. Calculate the number of repetitions required to cause fatigue failure, Bs. Use the SWT equation, Eq. 9.18, to determine the equivalent completely reversed stress amplitudes, Oar. Stress, MPa One repetition 600 400 200 0 1 2 3 1199 1200 time -200
do 228 Table 9.1 Constants for Stress-Life Curves for Various Ductile Engineering Metals, from Tests at Zero Mean Stress on Unnotched Axial Specimens Yield Ultimate True Fracture 0.=/(2N)' = AN Strength Strength Strength Material OB o А b=B (a) Steels SAE 1015 415 726 1020 927 -0.138 (normalized) (33) (60.2) (105) (148) (134) Man-Ten 322 557 990 1089 1006 -0.115 (hot rolled) (46.7) (80.8) (144) (158) (146) RQC-100 683 758 1186 938 897 -0.0648 (roller Q&T) (99.0) (110) (172) (136) (131) SAE 4142 1584 1757 1998 1937 1837 -0.0762 (Q & T, 450 HB) (230) (255) (290) (281) (266) AISI 4340 1103 1172 1634 1758 1643 -0,0977 (aircraft quality) (160) (170) (237) (255) (238) (b) Other Metals 2024-T4 AI 303 631 900 839 -0.102 (44.0) (69.0) (91.5) (131) (122) Ti-6A1-4V 1185 1233 1717 2030 1889 -0.104 (solution treated (172) (179) (249) (295) (274) and aged) 476
An additional relationship that is frequently employed is the Smith, Watson, and Topper (SWT) equation. Two equivalent forms are Our Omaxo (max > 0) (a) (9.18) R Caromax (max) b 2