A mounting arrangement for mounting an aircraft gas turbine engine to an aircraft. The mounting arrangement comprises an engine nacelle. The engine nacelle comprises a distal assembly comprising a part annular engine cowl, a gas turbine engine core housing surrounded by the engine cowl and a distal bifurcation extending between the engine core housing and engine cowl, the distal bifurcation extending in a first direction to define a first axis. The mounting arrangement further comprises a proximal assembly having a mount configured to mount the proximal assembly to the engine core housing. The proximal assembly further comprises a pylon configured to mount the proximal assembly to mounting location such as a wing of the aircraft at an engine mounting location. The pylon extends in a line between the wing and the engine core housing to define a second axis, wherein the second axis is normal to a distal surface of the wing at the engine mounting location and is non-parallel to the vertical axis.


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    Titel :

    GAS TURBINE ENGINE MOUNT ARRANGEMENT


    Weitere Titelangaben:

    MONTAGEANORDNUNG FÜR EINEN GASTURBINENMOTOR
    AGENCEMENT DE MONTAGE D'UN MOTEUR À TURBINE À GAZ


    Beteiligte:
    LIM CHIA HUI (Autor:in) / STRETTON RICHARD (Autor:in) / SHEAF CHRISTOPHER (Autor:in)

    Erscheinungsdatum :

    22.01.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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