Numerical simulations were conducted to investigate the shaped-hole film cooling on the pressure side of a turbine rotor under engine operating conditions

including the effects of blowing ratio and rotational Reynolds number. Results showed that the film jet was deflected towards the blade tip subjecting to the combined influences of centrifugal force and Coriolis force under rotational conditions

due to the change of the film vortex structure. The film jet was deflected towards the blade tip more sharply with the increase of rotational Reynolds number. The laterally-average cooling effectiveness slightly improved owing to more uniform film coverage. In the same rotational speed

the fan-shaped hole and console hole enabled to effectively restrain the film separation with high blowing ratios compared with the cylindrical hole. The laterally-average cooling effectiveness monotonously decreased downstream and increased with the blowing ratio. Besides

the film jet bent to the tip more notably with a small blowing ratio. As a result

the fan-shaped hole and console hole still have a pronounced advantage over the cylindrical hole under rotational conditions.