Abstract    An experimental study of hydrodynamics of film cooling is performed by using a single longitudinal slot on a cylindrical model simulated to the leading edge of the gas turbine blade. The model is set up into the test section of an open-circuit induced flow wind tunnel which provides the main flow. The injected air, as a secondary film flow, produced from a high pressure compressor is considered so that, the cooling factor always remained between 0.1 and 3.9. The first separation region of the boundary layer over the cylinder caused by the presence of injected flow was determined. The separation region extends up to 20 degrees after injection point with different conditions used in this experiment.

Keywords    Gas Turbine Blade, Leading Edge, Film Cooling, Slot Film Cooling, Cooling Factor, Effectiveness of Film Cooling

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