The improvements in performance in turbojet and turboprop engines by increasing the maximum cycle temperature through the use of transpiration air cooled turbine blades for operation at 2500°F cycle temperature are presented. The fabrication aspects of a transpiration air cooled blade are discussed. Initial test results are presented demonstrating the feasibility of the transpiration air cooled blade concept for advanced aircraft turbine engines.


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    Title :

    DESIGN AND FABRICATION ASPECTS OF TRANSPIRATION AIR COOLED BLADES FOR 2500°F TURBINE OPERATION


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    SAE World Congress & Exhibition ; 1964



    Publication date :

    1964-01-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English





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