Studies On Cooling Performance Of Round Cooling Holes With Various Configurations On A High-Pressure Turbine Vane
PROCEEDINGS OF THE ASME TURBO EXPO: TURBOMACHINERY TECHNICAL CONFERENCE AND EXPOSITION, 2018, VOL 5C(2018)
摘要
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.
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关键词
Film Cooling,Thermal Performance
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