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抄録
This experimental work is to investigate film cooling for slot injection into a separated region of very thin turbine blade. The purpose of this research is to clarify the feasibility of the turbine blade which has been thinned the thickness. With such a thin turbine blade, as flow separation occur on the pressure-side, so film cooling practice in that kind of flow filed has not been well established. The experimental results showed: followings a reattachment length is about five times step height. Characteristic of adiabatic effectiveness in the pressure-side wall depends not only blowing ratio but also situation of a separated shear layer and shape of turbine blade.
