An apparatus and method for mounting a turbine engine 20 to an aircraft 10 can include an engine core 40 for the turbine engine 20 including a compressor section 42, a combustor section 48, and a turbine section 52 in flow arrangement. At least one strut 110 couples to the engine core 40 about a single mount plane 120. A structural wall 116 at least partially defining a mainstream flow path 118 couples to the at least one strut 110 and passes through the compressor section 42 and the turbine section 52.


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    Titel :

    TURBINE ENGINE WITH SINGLE WALL CANTILEVERED ARCHITECTURE


    Weitere Titelangaben:

    TURBINENMOTOR MIT EINWANDIGER FREITRAGENDER ARCHITEKTUR
    MOTEUR DE TURBINE À ARCHITECTURE EN PORTE-À-FAUX À PAROI UNIQUE


    Beteiligte:

    Erscheinungsdatum :

    2019-02-27


    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 / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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