摘要
The service load on high temperature rotating components of aero-engines generally exhibits flight mission characteristics. The general shape of the load spectrum is that Type III/IV cyclic loading and creep loading are superimposed on Type I cyclic loading. Meanwhile, the sequence of the Type III/IV cyclic and creep loading varies with mission. This work performed load spectrum test with this characteristic on the Ni-based alloy FGH96. Then a life prediction method was developed based on the Chaboche fatigue damage accumulation model and a modified time fraction model. Creep followed by Fatigue (C-F) test was carried out to reveal the creep-fatigue interaction and calibrate parameters. The results show that most test results fall within the 2-fold deviation band. The sequence of creep-fatigue loading within the load spectrum exhibited a limited effect on life. Finally, simplified methods were developed to improve analysis efficiency, and cases where simplified methods could replace the proposed method were discussed.
基金
supported by the National Science and Technology Major Project of China(No.J2019-IV-0017-0085)
the National Natural Science Foundation of China(Nos.12172021,52205177)
the Natural Science Foundation of Hunan Province,China(No.2021JJ40741).
