An aircraft engine (12) is mounted to an aircraft pylon (56) with a variable pitch mounting system which a includes variable length actuator (152) disposed between the engine and pylon for pitching the engine relative to the pylon. Spaced apart pylon front and rear mounts may pivotably mount (118,120) front and rear stationary engine components of the engine to front and rear mount positions on the pylon. Front and rear linkages (62,64) may vertically suspend the engine from the pylon with pivotable links disposed between pylon front and rear mounts and front and rear stationary engine components. One or more thrust links (126) may be pivotably joined at link rear ends to the pylon rear mount and at the link forward ends to a front support frame. An alternative mounting system may include a support structure cantilevered off the pylon for pivotably supporting the engine and the actuator substantially horizontally disposed between the engine and the pylon. The incidence angle between the engine centerline axis and air streamlines may be adjusted by changing the length of the actuator.


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    Titel :

    VARIABLE PITCH MOUNTING FOR AIRCRAFT GAS TURBINE ENGINE


    Weitere Titelangaben:

    MONTAGE MIT VARIABLER NEIGUNG FÜR EINEN GASTURBINENMOTOR EINES FLUGZEUGS
    MONTAGE À INCLINAISON VARIABLE POUR MOTEUR À TURBINE À GAZ D'AVION


    Beteiligte:

    Erscheinungsdatum :

    15.06.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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