A gas turbine engine transition duct 34 is used to convey exhaust gas and bypass air away from the engine, towards an exhaust nozzle (not shown). The duct 34 defines the outer extremity of the path for gas and/or air through the duct. The duct comprises a plurality of flat panel members 36 which together define the outer extremity of the path.


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    Titel :

    Improvements in or relating to gas turbine engine transition ducts


    Weitere Titelangaben:

    Verbesserungen an oder in Zusammenhang mit Gasturbinenüberleitkanälen
    Améliorations de ou relatives à des conduits de transition sur un moteur à turbine à gaz


    Beteiligte:

    Erscheinungsdatum :

    2017-11-15


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    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



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