Numerical Study on Flim Cooling of Transonic Turbine Vane Endwall

The numerical study was conducted on the endwall film-cooling of transonic turbine vane.Several regions of high heat transfer rate were presented on turbine vane endwall.They are leading edge region where the horseshoe vortex occurs,suction side region where horseshoe vortex happens,channel region near the pressure side,and region near the trailing edge and downstream of trailing edge.According to the complex heat transfer distribution on the endwall,a new full film cooling holes on the endwall was designed.The endwall Nu number,film cooling effectiveness and thermal loads on the endwall were compared under different inlet blowing ratio,the result shows that there is the best inlet blowing ratio,the film-cooling effectiveness on the endwall is best at M■=1.0 on the leading edge and M■=4.0 on the trailing edge.