Journal
JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME
Volume 134, Issue 3, Pages -Publisher
ASME-AMER SOC MECHANICAL ENG
DOI: 10.1115/1.4004261
Keywords
fatigue; cracks; crack growth; crack closure; plasticity; titanium alloy
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Funding
- Pratt Whitney
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Plasticity effects and crack-closure modeling of small fatigue cracks were used on a Ti-6Al-4V alloy to calculate fatigue lives under various constant-amplitude loading conditions (negative to positive stress ratios, R) on notched and un-notched specimens. Fatigue test data came from a high-cycle-fatigue study by the U. S. Air Force and a metallic materials properties handbook. A crack-closure model with a cyclic-plastic-zone-corrected effective stress-intensity factor range and equivalent-initial-flaw-sizes (EIFS) were used to calculate fatigue lives using only crack-growth-rate data. For un-notched specimens, EIFS values were 25-mu m; while for notched specimens, the EIFS values ranged from 6 to 12 mu m for positive stress ratios and 25-mu m for R = -1 loading. Calculated fatigue lives under a wide-range of constant-amplitude loading conditions agreed fairly well with the test data from low-to high-cycle fatigue conditions. [DOI: 10.1115/1.4004261]
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