الفهرس 
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Abstract
The present work is concerned with an investigation of heat transfer around the leading edge of a film cooled gas turbine blade. Of special interest is the influence of the injection of cold air from holes located in the neighborhood of the stagnate point, and therefore attention is focused on the determination of the variation of local heat transfer coefficient in this region.
However the injected air was heated and the mainstream was at the atmospheric temperature as in de-icing process, and this will give the same effect of coolant injection.
This thesis reports the progress made to date. So far , preliminary theoretical and experimental investigations has been conducted to determine the flow and heat transfer parameters for the case of ” Un blown ” blade. The results of these investigations will serve as a bases of comparison, with these results of the ” blown ” blade to check the procedures adopted.
Experiments have been carried out to determine the local values of the heat transfer with various values of blowing parameter (Ub/U) and at different values of Reynolds number. Also the effect of blowing angle and hole centerline angle on the heat transfer coefficient have been studied.