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.