Studies on Cooling Performance of Round Cooling Holes With Various Configurations on a High-Pressure Turbine Vane

This study deals with detailed experimental investigations on cooling performance of round cooling holes with three hole configurations on the pressure surface of a large-scale test model of a high-pressure turbine vane for gas turbines, where one configuration is a conventional one and the other two are newly designed through a GA (Generic Algorithm) optimization. The purpose of this study is to see how those new hole configurations perform under realistic flow conditions. A blow-down type wind tunnel is used in this study, where IR camera-based transient method is applied to the measurement of film effectiveness and heat transfer distributions on the test model. Numerical simulations using a commercial software are also carried out to enhance the understanding of the cooling performance of each of the hole configurations.