An experimental investigation was conducted to obtain the detailed film cooling efficiency distributions on both pressure side and suction side of turbine blade with a novel film hole injection.The blowing ratios of the coolant through the discrete holes are 0.5

1.0and 2.0

respectively.Detailed film cooling efficiency distributions and spatially averaged film cooling efficiency were obtained.The results show that the film cooling efficiency at the pressure side and the suction side was different.The suction side had the highest cooling efficiency at blowing ratio of 1.5.The increasing blowing ratio led to a much faster decrease in the spanwise averaged efficiency.The cooling efficiency distribution of the pressure side was complicated.The cooling efficiency at the hole exit reached the highest at blowing ratio of 1.0

while that at the down stream reached the highest at blowing ratio of 2.0and the lowest at 1.0.The efficiency distributions were different with the various blowing ratios.