An aircraft engine, has: a low-pressure compressor and a high-pressure compressor located downstream of the low-pressure compressor; a gaspath valve upstream of the high-pressure compressor, the gaspath valve movable between an open configuration and a closed configuration; and a bypass flow path having in flow series a bypass inlet, a bypass valve, and a bypass outlet, the bypass inlet fluidly communicating with the gaspath upstream of at least one stage of the low-pressure compressor, the bypass valve having an open configuration in which the bypass valve allows a bypass flow and a closed configuration in which the bypass valve blocks the bypass flow, the bypass outlet fluidly communicating with the bypass inlet via the bypass valve and with the gaspath at a location in the gaspath fluidly downstream of the gaspath valve, downstream of the low-pressure compressor, and upstream of the high-pressure compressor.


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    Titel :

    GAS TURBINE ENGINE WITH LOW-PRESSURE COMPRESSOR BYPASS


    Weitere Titelangaben:

    TURBINE A GAZ A DERIVATION DE COMPRESSEUR BASSE PRESSION


    Beteiligte:
    COUTU DANIEL (Autor:in)

    Erscheinungsdatum :

    2023-01-21


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT




    Supersonic STOVL aircraft with turbine bypass/turbo-compressor engines

    Franciscus, L. C. / Luidens, R. W. | NTRS | 1984


    Supersonic STOVL aircraft with turbine bypass/turbo-compressor engines

    Franciscus, L. C. / Luidens, R. W. | NTRS | 1984



    TURBOFAN GAS TURBINE ENGINE WITH BYPASS DUCT

    STRETTON RICHARD / WILLMOT MICHAEL | Europäisches Patentamt | 2020

    Freier Zugriff