Wind-tunnel tests were conducted on thrust augmentation by injecting water at the inlet of the axial-flow compressor of a turbojet engine with a fixed-area tail-pipe nozzle 16.375 inches in diameter at an inlet-air temperature of 520 deg R. With a tail-pipe temperature of 1680 deg R and at a simulated flight Mach number of 0.265, the net thrust was increased 15% at a pressure altitude of 5000 feet and a water-air ratio of 0.0407 and 12% at a pressure altitude of 20000 feet and a water-air ratio of 0.0535. Specific fuel consumption was 22 and 28% greater, respectively, with water injection.


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    Titel :

    Altitude-Wind-Tunnel Investigation of Thrust Augmentation of a Turbojet Engine. 2 - Performance with Water Injection at Compressor Inlet


    Beteiligte:
    R. O. Dietz (Autor:in) / W. A. Fleming (Autor:in)

    Erscheinungsdatum :

    1947


    Format / Umfang :

    37 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch