In accordance to analysis of interaction mechanism between the ejection and the main flow

a 2-D compressible model of the turbine blade trailing edge ejection has been improved

which uses energy loss coefficient for representing the effect of the ejection on the aerodynamics of the main flow.The aerodynamical loss after the ejection has been analyzed through correlation of the model with the numerical calculation of the cascade main flow field and boundary layer parameters.The comparison between calculation results and experimental data shows that the improved model can exactly describe the mixing process between the main flow and the ejection

and predict the energy loss coefficient for the ejection on the pressure side near the trailing edge and through the trailing edge holes.