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.
Summary of NASA Aerodynamic and Heat Transfer Studies in Turbine Vanes and Blades
Sae Technical Papers
Aerospace Engineering and Manufacturing Meeting ; 1976
1976-02-01
Aufsatz (Konferenz)
Englisch
Summary of NASA Aerodynamic and Heat Transfer Studies in Turbine Vanes and Blades
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