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.