This paper reports recent experimental and theoretical studies of transpiration-cooled turbine blades, and on the basis of this and earlier work in the total research program proposes a design method for such cooling systems. An integral boundary-layer method of analysis is shown to produce good agreement between observed and predicted heat transfer coefficients over most of the blade section where the effect of the coolant flow is significant, while a simple momentum-mixing theory appears adequate for assessing the effects of the coolant on the blade profile loss.

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