A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct.


    Access

    Download


    Export, share and cite



    Title :

    Gas turbine engine keel beam


    Contributors:

    Publication date :

    2020-12-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



    GAS TURBINE ENGINE KEEL BEAM

    PEACE RICHARD / INGLEY LUCIAN | European Patent Office | 2019

    Free access

    Aircraft keel beam assembly

    VUKOSAV DANILO / COX DANIEL JUSTIN / POTUPCHIK EVGENIY et al. | European Patent Office | 2023

    Free access

    AIRCRAFT KEEL BEAM ASSEMBLY

    VUKOSAV DANILO / COX DANIEL JUSTIN / POTUPCHIK EVGENIY et al. | European Patent Office | 2022

    Free access

    Keel beam of an aircraft

    DURAND YVES / SOULA DENIS / COLMAGRO JÉRÔME | European Patent Office | 2015

    Free access

    KEEL BEAM ASSEMBLY FOR AN AIRCRAFT

    VUKOSAV DANILO / COX DANIEL / POTUPCHIK EVGENY M et al. | European Patent Office | 2022

    Free access