An engine assembly (24) includes a propulsor (22), a gearbox (32), an engine (28), a gas turbine engine (30), and an electric control assembly (34). The gearbox (32) includes a gear assembly (70) coupled with the propulsor (22). The engine (28) includes an air inlet (36), an exhaust outlet (38), and an engine output shaft (40). The engine output shaft (40) is coupled with the gear assembly (70) and configured to drive rotation of the propulsor (22) through the gear assembly (70). The gas turbine engine (30) includes a first rotational assembly (56), a compressor section (42), a turbine section (44), and a combustor (46). The compressor section (42) is connected to the air inlet (36). The combustor (46) is connected to the exhaust outlet (38). The combustor (46) is configured to direct a combustion gas (88) through the turbine section (44) to drive rotation of the first rotational assembly (56). The electric control assembly (34) includes a first electric motor (76). The first electric motor (76) is coupled with the gear assembly (70). The first electric motor (76) is configured to selectively apply a rotational force to the gear assembly (70) to further drive rotation of the propulsor (22).


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    Titel :

    ENGINE ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM


    Weitere Titelangaben:

    MOTORANORDNUNG FÜR EIN FLUGZEUGANTRIEBSSYSTEM
    ENSEMBLE MOTEUR POUR SYSTÈME DE PROPULSION D'AÉRONEF


    Beteiligte:
    WANG XI (Autor:in) / THOMASSIN JEAN (Autor:in) / GAGNON-MARTIN DAVID (Autor:in)

    Erscheinungsdatum :

    19.03.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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