Abstract
The cooling characteristics are theoretically investigated in the case of a return-flow type of gaseous-cooled gas turbine rotor blade. The blade model is intended for the application of a closed-circuit gaseous coolant system. An analytical method based on one-dimensional fluid flow and heat transfer is proposed for calculating temperatures of the blade metal, incoming coolant, and outgoing coolant at various spanwise positions, and also pressure losses of the coolant at each cooling passage. The numerical analysis is carried out for a steam-cooled rotating blade under reasonably selected gas turbine operating conditions. In comparing both cooling characteristics of the blade with and without rotation, it is shown that the pumping effect on the cooling performance and pressure loss is relativery small in this study.
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