The film cooling effectiveness on the blade surface under different coolant entrance pressures was numerically investigated using the shear-stress transport(SST) two-equation turbulent model

so as to understand the influences of film-cooling holes on cooling effectiveness.Three-dimensional turbulent flow in the turbine cascade and the cooling effectiveness on the blade surface with cylindrical film cooling hole were simulated in two cases: with/without heat transfer in the blade.The results show that the cooling effectiveness increases with the increment of the coolant entrance total pressure

and the cooling effectiveness with heat transfer in the blade is better than that without heat transfer in the blade

especially in the leading edge region.