An engine assembly includes a propulsor, a gearbox, an engine, a gas turbine engine, and an electric control assembly. The gearbox includes a gear assembly coupled with the propulsor. The engine includes an air inlet, an exhaust outlet, and an engine output shaft. The engine output shaft is coupled with the gear assembly and configured to drive rotation of the propulsor through the gear assembly. The gas turbine engine includes a first rotational assembly, a compressor section, a turbine section, and a combustor. The compressor section is connected to the air inlet. The combustor is connected to the exhaust outlet. The combustor is configured to direct a combustion gas through the turbine section to drive rotation of the first rotational assembly. The electric control assembly includes a first electric motor. The first electric motor is coupled with the gear assembly. The first electric motor is configured to selectively apply a rotational force to the gear assembly to further drive rotation of the propulsor.


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    Titel :

    Engine assembly for an aircraft propulsion system


    Beteiligte:
    WANG XI (Autor:in) / THOMASSIN JEAN (Autor:in)

    Erscheinungsdatum :

    10.12.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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