抄録
The distribution of film cooling effectiveness on both suction and pressure surfaces of a gas turbine blade was measured for several density ratios of injectant and main stream. The coolant was injected from a rectangular hole located near the leading edge of the blade. As a result, it was clarified that the film cooling effectiveness is mainly governed by the momentum flux ratio of injectant and main stream on both suction and pressure surfaces independent of density ratio, and the optimum momentum flux ratio is about 1.0 on the suction surface and about 0.01 or less than 0.01 on the pressure surface.
