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Damage Tolerance Behavior of a Nickel-Based Super-alloy GTM718 Under Cold-TURBISTAN Variable Amplitude Loads
Transactions of the Indian Institute of Metals ( IF 1.6 ) Pub Date : 2021-02-17 , DOI: 10.1007/s12666-021-02212-x
Sharanagouda G. Malipatil , Anuradha N. Majila , D. Chandru Fernando , M. Manjuprasad , C. M. Manjunatha

In this study, the damage tolerance behavior in terms of fatigue crack propagation behavior of an aero-engine material under a standard variable amplitude load sequence was predicted and compared with experimental results. The constant amplitude (CA) fatigue crack growth rate (FCGR) behavior of GTM718, a nickel-based super-alloy, was determined at various stress ratios R = σmin/σmax ranging from R = 0.1 to 0.7. The empirical fatigue crack growth law was derived from this data in terms of two-parameter crack driving force, ΔK*. Then, the fatigue crack propagation behavior of GTM718 under a standard cold-TURBISTAN variable amplitude load sequence was predicted using cycle-by-cycle approach and using the CA fatigue crack growth law. Also, experimental fatigue crack growth behavior under the same cold-TURBISTAN variable amplitude load sequence was determined and compared with predicted results. A fairly good correlation was observed with predicted and experimental results.



中文翻译:

镍基超合金GTM718在冷突波变幅载荷下的耐损伤性能

在这项研究中,预测了航空发动机材料在标准变幅载荷序列下的疲劳裂纹扩展行为所产生的损伤耐受行为,并将其与实验结果进行了比较。在各种应力比测定GTM718,基于镍的超合金,所述的恒定振幅(CA)疲劳裂纹扩展速率(FCGR)行为- [R  =  σ分钟/ σ最大范围从- [R  = 0.1〜0.7。经验疲劳裂纹扩展定律是根据两参数裂纹驱动力ΔK得出的。*。然后,使用逐周期方法和CA疲劳裂纹扩展定律,预测了GTM718在标准冷TURBISTAN可变振幅载荷序列下的疲劳裂纹扩展行为。此外,确定了在相同的冷TURBISTAN变幅载荷序列下的实验疲劳裂纹扩展行为,并将其与预测结果进行了比较。观察到的预测结果和实验结果具有相当好的相关性。

更新日期:2021-02-17
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