Study on influence of coolant mass flux on the thermal stress around the hole provided a reference for the design of the reliability of the film cooling vane. Combining the finite element method and boundary element method

the pore size was changed

and the finite element model was established to obtain the maximum temperature

temperature imbalance degree and maximum thermal stress of the vane after thermal shock with transient thermal/flow/structure coupling technology. Research showed that increasing the coolant mass flux was beneficial to improve the cooling efficiency and reduce the vane temperature

but also increase the imbalance temperature of the vane

which may lead to more serious thermal stress concentration at the trailing edge. Increasing the pore diameter at the leading edge can increase the average cooling efficiency by 66%

helping to slow down the thermal stress in the pores. However

increasing the trailing air hole diameter had moderate effect on average cooling efficiency and thermal stress. Above all

numerical results were consistent with experiment and theory

showing the results were valuable reference for aero-engine turbine vane cooling designers.