A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon portion and extends in the aft direction from the stationary portion. A second annular portion is positioned aft of the first portion and coupled to the rail, the second portion being movable along an engine core centerline between a closed position and an open position, wherein the second annular portion is configured to engage with the first annular portion in the closed position to provide access to an engine core. The second annular portion includes a nozzle plug.


    Access

    Download


    Export, share and cite



    Title :

    Integrated nozzle and plug


    Contributors:

    Publication date :

    2017-02-21


    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



    CHARGER PLUG NOZZLE

    HEMRLE JAROSLAV / GARCIA-FERRE FRANCISCO / BORTOLATO MATTEO et al. | European Patent Office | 2021

    Free access

    Charger plug nozzle

    HERMELE JAROSLAV / GARCIA-FERRE FRANCISCO / BORTOLATO MATTEO et al. | European Patent Office | 2023

    Free access

    Charger Plug Nozzle

    HEMRLE JAROSLAV / GARCIA-FERRE FRANCISCO / BORTOLATO MATTEO et al. | European Patent Office | 2023

    Free access

    CHARGER PLUG NOZZLE

    HEMRLE JAROSLAV / GARCIA-FERRE FRANCISCO / BORTOLATO MATTEO et al. | European Patent Office | 2021

    Free access

    Integrated Thrust Control System Using a Moveable Plug Nozzle

    Smith, Richard / Nyberg, Don / Groudle, Thomas et al. | AIAA | 2008