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.


    Access

    Download


    Export, share and cite



    Title :

    Aircraft propulsion assembly


    Contributors:

    Publication date :

    2018-05-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



    Aircraft propulsion assembly and aircraft comprising such aircraft propulsion assembly

    SOULIERE AURELIEN | European Patent Office | 2023

    Free access

    Aircraft propulsion assembly and aircraft comprising such propulsion assembly

    PONS FRANCOIS / FLEMING CHRISTIAN | European Patent Office | 2024

    Free access

    Aircraft propulsion assembly

    COMBES STÉPHANE / SOULIE ADELINE / PAUTIS OLIVIER | European Patent Office | 2023

    Free access

    AIRCRAFT PROPULSION ASSEMBLY

    BELLET FRANCOIS / RENAULT CÉDRIC / RABINEAU JÉRÉMIE | European Patent Office | 2017

    Free access

    AIRCRAFT PROPULSION ASSEMBLY

    COMBES STÉPHANE / SOULIE ADELINE / PAUTIS OLIVIER | European Patent Office | 2020

    Free access