An aircraft power plant (10), comprising: a fan (11) for providing power to an aircraft; a gas turbine engine (21) located on a first axial side of the fan (11), the gas turbine engine (21) having a compressor (22) and a turbine (24) that drives an engine shaft (25); an electric motor (31) powered by a power source (33), the electric motor (31) driving a motor shaft (32); and a gearbox (40) located on a second axial side of the fan (11) opposite the first axial side, the gearbox (40) in driving engagement with the engine shaft (25), the motor shaft (32), and the fan (11), the gearbox (40) defining a first load path between the gas turbine engine (21) and the fan (11) and a second load path between the electric motor (31) to the fan (11), the fan (11) in continuous driving engagement with both of the gas turbine engine (21) and the electric motor (31) along the first load path and the second load path.


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    Title :

    HYBRID AIRCRAFT POWER PLANT


    Additional title:

    HYBRIDFLUGZEUGKRAFTWERK
    CENTRALE ÉLECTRIQUE HYBRIDE POUR AÉRONEF


    Contributors:

    Publication date :

    2025-08-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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