An aircraft propulsion system (fig.2,5) has an internal combustion engine (fig.2,10) such as a gas turbine engine; an electric motor (fig.2,28); and a propulsor (fig.2,12) driven by at least the motor. The motor has an engine fuel cooled cooling system 40 having a heat exchanger 46 which transfers heat from the motor to engines fuel. The system also has an overboard fuel dump system with a drain valve 54 provided downstream of the heat exchanger, preferably also a number of fuel injectors 17 downstream of the valve. The system may be a series hybrid propulsion system, in which the engine is coupled to an electric generator 32 providing power to the motor, and the engine is not mechanically coupled to a propulsor. Alternatively, the system may be a parallel hybrid propulsion system where the engine is coupled to a propulsor. An electrical energy storage device (fig.2,30) for the motor may be provided. Preferably, the engine has an oil cooling with a fuel-oil heat exchanger 50 downstream of the motor heat exchanger, rejecting heat from engine oil to engine fuel. The motor cooling system preferably has an intermediate cooling loop with a second heat exchanger 48 using an intermediate cooling fluid.


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    Titel :

    Hybrid aircraft propulsion system


    Beteiligte:

    Erscheinungsdatum :

    2021-10-20


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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