Abstract
In order to study the fatigue properties and fatigue life prediction model of aeroengine compressor components made of Ni-based superalloy GH4169 under simplified service condition, creep–fatigue test and fatigue test under different stresses at 650 °C were performed. The morphology of fatigue damage was analyzed. A modified Bannantine life prediction model which considers fatigue damage as the foundation and creep–fatigue damage factor as the correction was suggested and explained the different failure contributions between fatigue damage and creep damage, which leads to less logarithmic relative error compared with common method. The finite element analyses of compressor’s mechanical properties were conducted by the software ABAQUS to find failure position, and mechanical parameters of failure location were obtained by statistical analysis. The results indicated that the fatigue life of compressor components was predicted by optimized model, which exhibited a good agreement with the experiment data, which has important reference value for the engineering application of aeroengine compressors.
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The authors gratefully acknowledge the financial support of Tianjin Science and Technology Support Project (Grant No. 18JCTPJC66800).
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Chen, Y., Zhang, X., Wang, F. et al. Fatigue Failure Analysis and Life Prediction of Aeroengine Compressor Components. J. of Materi Eng and Perform 28, 6418–6427 (2019). https://doi.org/10.1007/s11665-019-04370-y
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DOI: https://doi.org/10.1007/s11665-019-04370-y