A heat shield for a gas turbine engine includes a radial heat shield flange that extends in a circumferential direction and forms a ring. A plurality of bosses extend from a first axial side of the radial heat shield flange. There is a plurality of guide pins. One of the plurality of guide pins extends from a corresponding one of the plurality of bosses.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Gas turbine engine exhaust component


    Beteiligte:
    EASTWOOD JONATHAN JEFFERY (Autor:in) / HART ADAM LEE (Autor:in) / CRAIG BRIAN (Autor:in) / AYALDE LUIS MIGUEL (Autor:in) / LEVY BRIAN (Autor:in)

    Erscheinungsdatum :

    15.09.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / 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



    Three-Component Velocity Measurements in a Turbine Engine Exhaust

    Jenkins, Tom P. / Hess, Cecil F. / Morgan, Regis et al. | AIAA | 2017


    GAS TURBINE ENGINE EXHAUST SYSTEM

    MENHEERE DAVID / TRUMPOUR ADAM | Europäisches Patentamt | 2018

    Freier Zugriff

    Turbine engine exhaust nozzle performance

    WEHOFER, S. / MATZ, R. | AIAA | 1973


    Three-Component Velocity Measurements in a Turbine Engine Exhaust (AIAA 2017-0022)

    Jenkins, Tom P. / Hess, Cecil F. / Morgan, Regis et al. | British Library Conference Proceedings | 2017


    EXHAUST NOZZLE FOR GAS TURBINE ENGINE

    HOLT GAVIN JOSEPH / IGLEWSKI TOMASZ / HOLLAND JOHN ROBERT | Europäisches Patentamt | 2017

    Freier Zugriff