Abstract: The film cooling characteristics on blade surface were numerically investigated using the two-equation turbulence model of the shear-stress transport.Three-dimensional turbulent flow in turbine cascade and the cooling effectiveness on blade surface were carried out under the same coolant total pressure.The influence of the cooling effectiveness of cylindrical film cooling holes on the blade suction surface with varying film hole inclination angles was investigated.Results show that the front inclination of the film cooling hole may improve the film cooling effectiveness for every row of film cooling holes,and the improvement is more obviously for the first row of film cooling holes.