A rear suspension for attaching an aeroengine (20) of longitudinal axis X to a carrier structure or mast (12) of an aircraft, the suspension including at least two clevis-forming vertical uprights (26A, 26B; 28A, 28B) supporting a respective horizontal slideway (30A, 30B) having a roller (32) freely mounted thereon that is suitable for moving in a slot (34A, 34B) in a lug (20A) arranged in a YZ plane of transverse axis Y and of vertical axis Z, in such a manner as to enable the aeroengine to move only in translation along the longitudinal axis X and in pivoting about said longitudinal axis X.


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    Titel :

    A suspension for a turbine engine


    Beteiligte:

    Erscheinungsdatum :

    15.03.2017


    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



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