An airborne type thrust measuring instrument was developed and subsequently tested on both a J79-GE-8 turbojet engine mounted on a thrust stand in a laboratory altitude cell and a JT3C-7 turbojet engine aboard a Boeing 720 aircraft. The thrustmeter system using measurements of internal engine pressures, ambient altitude pressure and total air temperature, computed engine gross thrust, net thrust and percent of maximum continuous rated thrust at the operating flight condition. Laboratory tests indicated that the thrustmeter gross thrust values were within + or -3.0% of the thrust stand measured values, and the thrustmeter net thrust values were within + or -4.2% of the thrust stand measured net thrust. Flight test results indicated that the system functioned properly aboard the aircraft and was responsive to small changes in engine power setting. The thrustmeter gross thrust and net thrust values agreed with the computed gross and net thrust of the engine within + or -2.2% and + or -2.8% respectively. In measuring net thrust during the flight tests, some difficulty was encountered in obtaining consistent static pressure readings at the compressor inlet station thus causing errors in the computation of ram drag. (Author)


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    Titel :

    Evaluation of a Thrustmeter for Measuring In-Flight Thrust of Turbojet Engines


    Beteiligte:
    R. F. Salmon (Autor:in)

    Erscheinungsdatum :

    1966


    Format / Umfang :

    54 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch