A turboprop gas turbine engine mountable to an aircraft has an engine core and a gearbox driving a propeller, the engine core and the gearbox being enclosed within a nacelle. The propeller is located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft. An air intake is disposed within the nacelle and formed to direct ambient air into the engine core. The air intake includes an air inlet duct, having a forward-facing intake inlet receiving the ambient air, with an upstream section and a downstream section. The upstream section is in fluid communication with the intake inlet and extends downstream from the intake inlet. The downstream section fluidly connects to and directs air from the upstream section into the engine air inlet. A second air outlet duct is located within the nacelle and directs air into an air-cooled-oil-cooler (ACOC).


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    PUSHER TURBOPROP POWERPLANT INSTALLATION


    Beteiligte:
    LETOURNEAU LAURENT (Autor:in) / MORGAN KEITH (Autor:in) / WILSON JOHN (Autor:in) / WEAVER PAUL (Autor:in) / DUROCHER ERIC (Autor:in)

    Erscheinungsdatum :

    2021-02-18


    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



    PUSHER TURBOPROP POWERPLANT INSTALLATION

    LETOURNEAU LAURENT / MORGAN KEITH / WILSON JOHN et al. | Europäisches Patentamt | 2021

    Freier Zugriff

    Pusher turboprop powerplant installation

    LETOURNEAU LAURENT / MORGAN KEITH / WILSON JOHN et al. | Europäisches Patentamt | 2023

    Freier Zugriff



    Computational analysis of a wingtip-mounted pusher turboprop

    Janus, J. M. / Chatterjee, Animesh / Cave, Chris | AIAA | 1996