The flow exiting the combustor in a gas turbine engine is considerably hotter than the melting temperature of the turbine section components, of which the turbine nozzle guide vanes see the hottest gas temperatures. One method used to cool the vanes is to use rows of film-cooling holes to inject bleed air that is lower in temperature through an array of discrete holes onto the vane surface. The purpose of this study was to evaluate the row-by-row interaction of fan-shaped holes as compared to the performance of a single row of fan-shaped holes in the same locations. This study presents adiabatic film-cooling effectiveness measurements from a scaled-up, two-passage vane cascade. High-resolution film-cooling measurements were made with an infrared camera at a number of engine representative flow conditions. Computational fluid dynamics predictions were also made to evaluate the performance of some of the current turbulence models in predicting a complex flow such as turbine film-cooling. The renormalization group (RNG) turbulence model gave a closer prediction of the overall level of film effectiveness, while the turbulence model gave a more accurate representation of the flow physics seen in the experiments.
Experimental and Computational Comparisons of Fan-Shaped Film Cooling on a Turbine Vane Surface
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Colban, W., Thole, K. A., and Haendler, M. (January 29, 2006). "Experimental and Computational Comparisons of Fan-Shaped Film Cooling on a Turbine Vane Surface." ASME. J. Turbomach. January 2007; 129(1): 23–31. https://doi.org/10.1115/1.2370747
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