Turbine-outlet radial temperature distributions of an XJ34-WE-32 turbojet engine were investigated in the altitude wind tunnel at the NACA Lewis laboratory over a range of pressure altitudes, engine-inlet air temperatures and flight Mach numbers at or near rated engine conditions. From blade stress considerations, the turbine-outlet temperature distribution was considered satisfactory at altitudes up to 25,000 feet at corrected engine speeds corresponding to rated speed (12,500 rpm); however, operation at either higher corrected engine speeds or higher altitudes resulted in an inversion of the turbine temperature distribution that was detrimental to turbine life. Installation of a compressor-outlet mixer greatly improved the turbine radial temperature distribution.


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    Title :

    Investigation of Turbine-outlet Temperature Distribution of XJ34-WE-32 Turbojet Engine


    Contributors:
    Prince, W R (author) / Wintler, J T (author)

    Publication date :

    1951-11-07


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English



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