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Hot section components in high performance aircraft and rocket engines are increasingly being made of single crystal nickel superalloys such as PWA1480, PWA1484, CMSX-4 and Rene N-4 as these materials provide superior creep, stress rupture, melt resistance and thermomechanical fatigue capabilities over their polycrystalline counterparts. These alloys play an important role in commercial, military and space propulsion systems. A detailed analysis of the experimentally determined Low Cycle Fatigue (LCF) properties for PWA1493/1480 and SC 7-14-6 single crystal materials as a function of specimen crystallographic orientation is presented, over a wide temperature range of 75F to 1800 F. The data presented includes an extensive compilation of LCF data for single crystal nickel-base material at high temperature and in high-pressure hydrogen and air. Fatigue failure parameters are investigated for LCF data of single crystal material based on the shear and normal stress and strain amplitudes on the 30 possible slip systems for FCC single crystals. The max shear stress amplitude on the slip planes reduces the scatter in the LCF data and is found to be a good fatigue damage parameter, especially at elevated temperatures. Fatigue life equations are developed for various temperature ranges and environmental conditions based on power-law curve fits of the failure parameter with LCF test data.

Analysis of Low Cycle Fatigue Properties of Single Crystal Nickel-Base Turbine Blade Superalloys