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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    Title :

    Summary of NASA Aerodynamic and Heat Transfer Studies in Turbine Vanes and Blades


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Aerospace Engineering and Manufacturing Meeting ; 1976



    Publication date :

    1976-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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