An aircraft system is provided that includes a propulsor rotor, an electric machine and a gas turbine engine. The electric machine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine includes a compressor section, a combustor section, a turbine section, an exhaust duct and a flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust duct. The exhaust duct extends longitudinally along the electric machine. The exhaust duct extends partially circumferentially about the electric machine between opposing circumferential sides of the exhaust duct.


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    Titel :

    EXHAUST DUCT FOR HYBRID AIRCRAFT POWERPLANT


    Weitere Titelangaben:

    CONDUIT D'EVACUATION POUR UN GROUPE MOTOPROPULSEUR D~AERONEF HYBRIDE


    Beteiligte:
    MENHEERE DAVID (Autor:in)

    Erscheinungsdatum :

    2024-06-23


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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