Method for discharge coefficients computation of film cooling holes on blade surface of turbine cascade

The empirical means for prediction of discharge coefficients of film cooling holes on the turbine blade suggested by Rowbury D.A. et al was improved to adapt the computations in the cases of low pressure ratios and the holes in leading edge region especially. The effects of external cross flow, hole geometry and Reynolds number in the hole were taken into account. An additive loss coefficient method is subsequently applied to the test data in order to show the effect of the external crossflow. To compare with a great deal of experimental data, the result shows that the improved method may be used as a generalized design methodology of film cooling for turbine blade.