Computations were performed to simulate the two rows of 90° staggered holes film cooling characteristics over a rotating turbine blade model both on leading and trailing surfaces. The influences of the Reynolds number ��Re��, rotation number ��Rt�� and the blowing ratio M on the film cooling effectiveness η and discharge coefficient ��C��d distributions were presented. Results show that the coolant is influenced by the centrifugal force and Coriolis force to deflect towards the high-radius locations, and this will lead to low values of η . The enhancement of ��Re�� can impair the film cooling effectiveness, and the high values of M are not suitable for the thermal protection near the exit of cooling holes. All the discharge coefficients increase with the augmentation of M , and decrease with the increase of Rt . Moreover, the C��d values beside trailing surface are much higher than that beside the leading surface under the same operating conditions.