The invention relates to the field of aero-engine design, particularly relates to a main mounting joint mechanism for a clamping type aero-engine, and solves the problem of lower installation efficiency of the existing aero-engine. The main mounting joint mechanism for the clamping type aero-engine comprises two thrust pins and two clamping mechanisms, wherein the two thrust pins are respectively arranged on main supporting cases at two horizontal sides of the engine; the two clamping mechanisms are respectively arranged on main supporting rings at two horizontal sides of a plane; the clamping mechanism at each side is used for fixedly clamping the thrust pin at the corresponding side; the clamped engine is in a predetermined installation position; moreover, the engine in the predetermined installation position comprises a predetermined quantity of omnidirectional rotation compensation. According to the main mounting joint mechanism for the engine provided by the invention, the thrust pins protrude out of the contour of the engine, so that the difficulty of inserting the thrust pins into mounting holes with small clearances is avoided, therefore the aero-engine can be precisely aligned to the mounting holes of the plane, and the labor intensity for assembly is lowered.


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    Titel :

    Main mounting joint mechanism for clamping type aero-engine


    Beteiligte:
    LIU XUYANG (Autor:in) / XU XUE (Autor:in) / TIAN DAKE (Autor:in) / ZHANG DEZHI (Autor:in) / HUAI SHIWEI (Autor:in)

    Erscheinungsdatum :

    30.12.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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