To study the influence of blade profiles and film cooling holes' parameter changes on the performance of the turbine blade

a blade stator with multi-row film cooling holes was optimized by multi-objective optimization algorithm to get the Pareto set; the overall performance of the blade was improved. The maximum aerodynamic efficiency increased by 0.35%; the maximum wall average temperature decrease was 0.74%; the maximum decrease of the high temperature function was 45.71%. The result shows that the increase of the backward curved angle can reduce the blade loss and second flow loss. The cooling effect improvement of the region near the leading edge is mainly due to the direction change of the film cooling holes near the leading edge stagnation point

as the direction change makes the cooling gas distribution reasonable.