A gas turbine engine for an aircraft is provided. 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 a core casings surrounding the engine core. The engine further includes one or more engine accessories mounted adjacent to and vertically beneath the core casings. The engine further includes a heatshield positioned between the one or more engine accessories and the core casings. The heatshield contains one or more ventilation holes for channelling convectively driven flows of ventilation air around the one or more engine accessories on engine shutdown.


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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) / RAYA EMILE (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 / SAVINGS DAVID / DITHERIDGE WILLIAM | Europäisches Patentamt | 2019

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