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Summary of NASA Aerodynamic and Heat Transfer Studies in Turbine Vanes and Blades
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Abstract
Aerodynamic effects of trailing edge geometry, hole size, angle, spacing, and shape have been studied in two- and three-dimensional cascades and in a warm turbine test series. Heat transfer studies have been carried out in various two- and three-dimensional test facilities in order to provide corresponding heat transfer data. Results are shown in terms of cooling effectiveness and aerodynamic efficiency for various coolant fractions, coolant-primary temperature ratios, and cooling configurations.
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Citation
Moffitt, T., Stepka, F., and Rohlik, H., "Summary of NASA Aerodynamic and Heat Transfer Studies in Turbine Vanes and Blades," SAE Technical Paper 760917, 1976, https://doi.org/10.4271/760917.Also In
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