A computer model for gas turbine blade cooling analysis has been developed. The finite difference technique over the chord and span of the blade is employed. A flow balance and an energy balance program are included in the model. The model is capable of predicting cooling flow characteristics (mass flow rate and internal pressure distribution) and metal temperature profiles of multipass coolant passages in rotating blades with local film cooling. The paper first presents the analytical model of coolant flow and heat transfer, then the computer program is discussed. Finally, the computed results of a sample blade at engine conditions is presented and discussed.

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