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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    Title :

    ENGINE ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM


    Additional title:

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


    Contributors:

    Publication date :

    2025-03-19


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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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