A compressor optimization study defined a 10-stage configuration with a 22.6:1 pressure ratio, and adiabatic efficiency goal of 86.1%, and a polytropic efficiency of 90.6%; the corrected airflow is 53.5 kg/sec. Subsequent component testing included three full-scale tests: a six-stage rig test, and another 10-stage rig test completed in the second quarter of 1982. Information from these tests is being used to select the configuration for a core engine test scheduled for July 1982 and an integrated core/low spool test slated for early 1983. The test results will also provide data base for the flight propulsion system.


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    Titel :

    Energy efficient engine. High pressure compressor detail design report


    Beteiligte:
    Holloway, P. R. (Autor:in) / Koch, C. C. (Autor:in) / Knight, G. L. (Autor:in) / Shaffer, S. L. (Autor:in)

    Erscheinungsdatum :

    01.05.1982


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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