Summary of NASA Aerodynamic and Heat Transfer Studies in Turbine Vanes and Blades 760917
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.
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. Download Citation
Author(s):
Thomas P. Moffitt, Francis S. Stepka, Harold E. Rohlik
Affiliated:
National Aeronautics and Space Administration
Pages: 22
Event:
Aerospace Engineering and Manufacturing Meeting
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Heat transfer
Test facilities
Coolants
Aerodynamics
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