Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Mechanical Power Engineering

Cooling technologies for gas turbine applications play an increasingly more important role. This is due to the high firing temperatures to meet the demand for higher performance turbine power. Film cooling is a technique employed to protect the external surface of gas turbine blades from the hot mainstream gas by ejecting the internal coolant air through discrete holes or slots at several locations on the blade exterior surface. Passing the coolant through conventional cylindrical holes causes protection for gas turbine blades from high temperatures. Early studies have proved that the results obtained on simple flat surfaces models can be applied to real engine design with slight corrections

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