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


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    Titel :

    TURBINE ENGINE WITH SINGLE WALL CANTILEVERED ARCHITECTURE


    Weitere Titelangaben:

    MOTEUR DE TURBINE A ARCHITECTURE EN PORTE-A-FAUX A PAROI SIMPLE


    Beteiligte:

    Erscheinungsdatum :

    2019-02-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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