The flow field and film cooling characteristics on the blade surface were 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.The flow and cooling effectiveness for four configurations of film cooling holes were compared.Results show that the cooling effectiveness for each film cooling hole increases with the increment of the coolant entrance total pressure.Under the same coolant entrance total pressure
the cooling effectiveness of the dustpan and slot film cooling holes are the best