A turboprop gas turbine engine (12) mountable to an aircraft (10) has an engine core (13) and a gearbox (38) driving a propeller (14), the engine core (13) and the gearbox (38) being enclosed within a nacelle (16). The propeller (14) is located rearward of the gearbox (38) and the engine core (13) relative to a direction of travel of the aircraft (10). An air intake (18) is disposed within the nacelle (16) and formed to direct ambient air into the engine core (13). The air intake (18) includes an air inlet duct (44), having a forward-facing intake inlet (20) receiving the ambient air, with an upstream section (43) and a downstream section (45). The upstream section (43) extends downstream from the intake inlet (20). The downstream section (45) fluidly directs air from the upstream section (43) into the engine air inlet (21). A second air outlet duct (47) is located within the nacelle (16) and directs air into an air-cooled-oil-cooler (ACOC) (50). A mounting structure (M) for securing such an engine is also provided.


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    Titel :

    PUSHER TURBOPROP POWERPLANT INSTALLATION


    Weitere Titelangaben:

    SCHUB-TURBOPROP-TRIEBWERKSINSTALLATION
    INSTALLATION MOTRICE DE TURBOPROPULSEUR POUSSEUR


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

    Erscheinungsdatum :

    25.09.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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