An experimental investigation of the effects of injecting a water-alcohol mixture of 2:1 at the compressor inlet of a centrifugal-flow type turbojet engine was conducted in an altitude test chamber at static sea-level conditions and at an altitude of 20,000 feet with a flight Mach number of 0.78 with an engine operating at rated speed. The net thrust was augmented by 0.16 for both flight conditions with a ratio of injected liquid to air flow of 0.05. Further increases in the liquid-air ratio did not give comparable increases in thrust.


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    Title :

    Performance of 4600-pound-thrust centrifugal-flow-type turbojet engine with water-alcohol injection at inlet


    Contributors:

    Publication date :

    1950-10-09


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English