Volume 36 Issue 11
Nov.  2021
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Article Navigation >  Journal of Aerospace Power  > 2021  >  36(11): 2372-2378
QIAN Zhengming, LI Gaiqi, MI Dong, AI Xing. Creep-fatigue life prediction method of tail edge holes in turbine blade for a turboshaft engine[J]. Journal of Aerospace Power, 2021, 36(11): 2372-2378. doi: 10.13224/j.cnki.jasp.20210130
Citation: QIAN Zhengming, LI Gaiqi, MI Dong, AI Xing. Creep-fatigue life prediction method of tail edge holes in turbine blade for a turboshaft engine[J]. Journal of Aerospace Power, 2021, 36(11): 2372-2378. doi: 10.13224/j.cnki.jasp.20210130
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Creep-fatigue life prediction method of tail edge holes in turbine blade for a turboshaft engine

doi: 10.13224/j.cnki.jasp.20210130

  • Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

  • Received Date: 2021-03-24
  • Publish Date: 2021-11-28
    Abstract
  • A creep-fatigue life analysis method considering stress relaxation was established for turbine blade in a turboshaft engine.The nonlinear creep deformation of a superalloy was predicted by coupling creep damage in the framework of viscoplastic theory.The results revealed that based on the elastic-plastic creep analysis of a turbine blade，the creep damage and its evolution law of the leading edge and trailing edge of the blade were clarified，and a method was provided for determining the local dangerous points on the blade.The calculation error of the model for the elastic-plastic stress-strain curve was less than 5%，while the simulation accuracy for the creep curve was within the dispersion range of the inherent properties of material creep deformation.With the help of the linear damage cumulative life theory，the creep-fatigue life of the trailing edge hole of a turbine blade considering the stress relaxation was obtained，providing a more reasonable and better engineering application method for the blade life evaluation.

     

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