The evolution of increasing turbine inlet temperature has led to the necessity of full-coverage film cooling for the first turbine vane and blade. This paper deals with the investigation of the aerodynamic behaviour of the transonic wall film on a leading edge with and without leading edge pressure waves. Here these films are used for turbine blade cooling. The pressure waves are produced with a rotating „Pressure Wave Generator“. The numerical simulations have been realised with a commercial CFD-Program. The experimental data were obtained in a linear cascade.

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