Aerodynamic effect of trailing edge coolant ejection on transonic turbine cascade

A two-dimensional compressible computer program was developed to predict the influence of the coolant ejection on the aerodynamic performance in transonic turbine cascade. The code was applied to the computation of energy loss coefficient for two different trailing edge ejection configurations. The results show that: (1) The energy loss coefficient for the ejection through the trailing edge holes would be higher than that for the ejection on the pressure side near the trailing edge. (2) The trailing edge ejection has no significant influence on the exit flow angle. (3) The energy loss decreases a little and then increases with increasing coolant mass ratio after a definite point.