A hybrid propulsion system including a turbine engine including a high-pressure spool and a low-pressure spool, the low-pressure spool including reduction gear, the reduction gear forming part of a transmission gearbox which is positioned axially at a front end of the propulsion system; —first and second electric machines mechanically and respectively connected to the high-pressure and low-pressure spools, the electric machines being configured to operate in modes referred to as motor and generator, the first and second electric machines being fixed to the transmission gearbox; —a control system which is configured to allow the transfer of power between the high-pressure and low-pressure spools via the first and second electric machines.


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    Titel :

    SYSTEME PROPULSIF HYBRIDE POUR UN AERONEF


    Weitere Titelangaben:

    HYBRID PROPULSION SYSTEM FOR AN AIRCRAFT
    HYBRIDANTRIEBSSYSTEM FÜR EIN FLUGZEUG


    Beteiligte:

    Erscheinungsdatum :

    28.05.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Französisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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