航空发动机涡轮叶片的热机械疲劳寿命的快速准确预测，是提高发动机安全性和可靠性的关键问题之一。以IC10合金涡轮叶片为研究对象，基于晶体塑性理论，建立了弹塑性本构关系和三参数幂函数能量法寿命预测模型。根据真实涡轮叶片载荷条件，确定叶片热机械疲劳寿命薄弱位置为叶根处气膜孔，并设计了薄壁模拟件开展数值模拟和试验研究，获取了4种热机械疲劳载荷条件下的应力-应变关系和寿命。结果表明：以晶体塑性理论为基础的各向异性本构？？能够很好地表征IC10 合金的弹塑性应力-应变关系，计算得到的薄壁圆管试验件的热机械疲劳寿命与试验结果基本一致，在2倍误差带以内，所构建的三参数幂函数能量法模型具有参数少、易获取的优势，可为复杂结构涡轮叶片热机疲劳寿命设计提供一定的参考。

The rapid perdition of thermo-mechanical fatigue life of aeroengine turbine blades is one of the most important issue concerning the engine safety and reliability. In this scenario, the thermo-mechanical fatigue life of a IC10 alloy turbine blades was studied. Based on the crystal plasticity theory, an elastic-plastic constitutive relationship and a three-parameter power law energy-based fatigue life prediction model were established. By considering the actual loading conditions of the turbine blades, the weak spot for thermo-mechanical fatigue life was identified as the film-cooling hole at the blade root. A thin-walled simulated specimen was designed for numerical simulation and experimental research to obtain the stress-strain relationship and fatigue life under four different loading conditions. The results demonstrate that the anisotropic constitutive model based on the crystal plasticity theory could well characterize the elastic-plastic stress-strain relationship of IC10 alloy. The calculated thermo-mechanical fatigue life of the thin-walled circular tube test specimen was in good agreement with the experimental results within a 2-fold error range. The three-parameter power law energy-based model constructed in this study has the advantages of requiring fewer parameters and being easily obtained. It would provide valuable insights for the design of thermo-mechanical fatigue life in complex turbine blades.

航空动力基金；基础性稳定支持项目