Abstract: Computations were performed to investigate the adiabatic effectiveness η distributions on the curvature turbine blade models under rotating conditions. In the present study, the Reynolds number Re based on mainstream velocity and film hole diameter varies from 3 198.4 to 6 716.6, the blowing ratio M ranges of 0.2 to 1.2, and the rotation number Rt alters from 0 to 0.015 9. Both κ-ω and the shear-stress transport(SST) models were chosen for turbulence closure. Results show that the increase of Rt leads to decreased η values in the centerline region downstream the film hole, but can improve the integrated effectiveness properly on the pressure surface. The augmentation of M also results in the decreased adiabatic effectiveness, while the variation of Re has little influence on the comprehensive cooling effect. In addition, the values of η on the suction surface are much greater than that on the pressure surface under the same operating conditions.