An investigation was conducted in the NACA Lewis altitude wind tunnel to determine the effect of compressor-outlet bleedoff on the performance of an axial-flow turbojet engine equipped with a variable-area exhaust nozzle. Results presented indicate the effect of compressor-outlet bleedoff on performance at altitudes of 25,000 and 40,000 feet and a flight Mach number of 0.53. Variation of performance with bleedoff flow is indicated for operation with fixed- and variable-area exhaust nozzles. Temperature and pressure losses through the bleedoff ducting system are also discussed.


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    Title :

    Effect of Compressor-outlet Bleedoff on Turbojet-engine Performance


    Contributors:

    Publication date :

    1950-08-07


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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