A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Convergent divergent exit nozzle for a gas turbine engine


    Beteiligte:

    Erscheinungsdatum :

    2022-02-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



    Convergent divergent exit nozzle for a gas turbine engine

    SIDELKOVSKIY DMITRIY B / PETRENKO OLEG / MALECKI ROBERT E et al. | Europäisches Patentamt | 2019

    Freier Zugriff

    Convergent-divergent nozzle

    ZAHID HUSSAIN | Europäisches Patentamt | 2016

    Freier Zugriff

    Convergent-divergent nozzle flows.

    KLIEGEL, J. R. / QUAN, V. | AIAA | 1968


    Convergent-Divergent Nozzle Flows

    J. R. Kliegel / V. Quan | NTIS | 1966


    The Jet Noise of a Convergent-Divergent Nozzle

    Harper-Bourne, Marcus | British Library Conference Proceedings | 2022