The disclosure relates to an aircraft propulsion assembly comprising a bypass turbojet engine equipped with a nacelle, the bypass turbojet engine including a structure defining a first part of a secondary flow path for channeling secondary flow, and the nacelle having a structure defining a second part of the secondary flow path. The structure of the nacelle defining the second part of the secondary flow path is arranged such that the first part and the second part of the secondary flow path are angularly offset around a longitudinal axis of the engine when the engine is shut down/stopped.


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    Titel :

    ENSEMBLE PROPULSIF D'AERONEF


    Beteiligte:
    BELLET FRANCOIS (Autor:in) / RENAULT CEDRIC (Autor:in) / RABINEAU JEREMIE (Autor:in)

    Erscheinungsdatum :

    15.07.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Französisch


    Klassifikation :

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



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