Abstract: According to the thermeset coupling analysis and approach of turbine blade optimization based on genetic-finite element method,an optimization design method about the integration of thermeset of turbine cooling blade was persented.By modeling the rotor blade of gas engine turbine,the influence of the position,shape(circle and rectanglar),size and number of cooling holes on thermal stress and cooling effect of turbine blade were investigated.It is proved that the developed method can effectively reduce the stress of turbine blade,and rectangular cooling hole has more cooling effect and smaller stress,the higher temperature of blade is decreased with the increase of size and number,but the max stress is rised.