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In the development of 1700 degree gas turbines, the innovation of turbine cooling technology is important. Film cooling is widely used in order to reduce the metal temperature and thermal stress. In this paper, the novel film hole configurations are proposed. The adiabatic effectiveness of those configurations is measured using PSP (pressure sensitive paint). The adiabatic effectiveness of those configurations is higher than cylindrical film hole. The shaped hole was applied to the vane/blade of low speed rotating test facility. It is found that the rotating blade platform is difficult to cool by film cooling technique compared to stationary vane shroud.

Development of High Performance Film Cooling of 1700 Degree C Class Gas Turbines