A cooling system includes: a core casing (18) configured to house a compressor (12, 13), a combustion chamber (14), and a turbine (15, 16); a tail cone (28) configured to form at least part of an exhaust passage (23) of the turbine (15, 16) together with the core casing (18); struts (27) configured to connect the core casing (18) with a support body (26) of the tail cone (28); a housing (31) installed in the tail cone (28), configured to house an electrical apparatus; and at least one primary duct (40) configured to connect between an internal space of the housing (31) and an outlet passage (12a) of the compressor (12) or a discharge port of a blower (34) installed in a gas turbine engine via at least one of the struts (27) and a radial outside of the core casing (18).


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    Titel :

    COOLING SYSTEM FOR AIRCRAFT GAS TURBINE ENGINE


    Weitere Titelangaben:

    KÜHLSYSTEM FÜR EIN GASTURBINENTRIEBWERK EINES FLUGZEUGS
    SYSTÈME DE REFROIDISSEMENT D'UNE TURBINE À GAZ D'AVION


    Beteiligte:
    SUZUKI FUMINORI (Autor:in) / SEKI NAOKI (Autor:in) / KOBAYASHI TOSHIKAZU (Autor:in)

    Erscheinungsdatum :

    15.05.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES / 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



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