A gas turbine engine is provided for an aircraft. The engine includes an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The engine further includes core casings surrounding the engine core. The engine further includes one or more engine accessories mounted adjacent to the core casings. The engine further includes a self-supporting heatshield positioned between the one or more engine accessories and the core casings. The heatshield is formed of ceramic matrix composite material.


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    Titel :

    GAS TURBINE ENGINE HEATSHIELD


    Weitere Titelangaben:

    GASTURBINENTRIEBWERKHITZESCHILD
    ÉCRAN THERMIQUE DE MOTEUR À TURBINE À GAZ


    Beteiligte:
    INGLEY LUCIAN (Autor:in) / SAVINGS DAVID (Autor:in) / DITHERIDGE WILLIAM (Autor:in)

    Erscheinungsdatum :

    2019-09-25


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



    GAS TURBINE ENGINE HEATSHIELD

    INGLEY LUCIAN / RAYA EMILE | Europäisches Patentamt | 2019

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