A hybrid aircraft propulsion system. The sytem comprises a gas turbine engine (5) comprising a compressor (11), a combustor (12), one or more turbines (13), a shaft (14) coupled to one of the turbines (13), and a bypass fan (10) mechanically driven by the shaft (14). The system further comprises an electrical generator (15) mechanically coupled to the shaft (14), and an auxiliary propulsor (6) mechanically coupled to an electric motor (16) and electrically coupled to the electric generator (15). At maximum power, the gas turbine engine (5) is configured to produce a turbine entry temperature at maximum power between 1800 Kelvin and 2000 Kelvin, the engine comprises a fan bypass ratio of between 4:1 and 13:1, and the generator is configured to absorb between 10% and 60% of the mechanical power generated by the turbine.


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    Titel :

    HYBRID AIRCRAFT PROPULSION SYSTEM


    Weitere Titelangaben:

    HYBRIDES FLUGZEUGANTRIEBSSYSTEM
    SYSTÈME DE PROPULSION D'AÉRONEF HYBRIDE


    Beteiligte:
    SCOTHERN DAVID (Autor:in)

    Erscheinungsdatum :

    2023-08-16


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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