A control system (34) for an aircraft hybrid propulsion system (5). The hybrid propulsion system (5) comprises a gas turbine engine (10) coupled to an electric generator (28, 32), a propulsor (12) coupled to an electric motor (28), and an electrical storage device (30) coupled to the motor (28) and the generator (32). The control system (34) is configured to operate the propulsion system (5) in one of a first descent mode and a second descent mode. In the first descent mode, for a given thrust, the gas turbine engine (10) is operated at a first engine power level and the generator (28, 32) is operated at a first generator power level. In the second descent mode, for a given thrust, the gas turbine engine (10) is operated at a second engine power level which is higher than the first engine power level, and the generator (28, 32) is operated at a second generator power level which is higher than the first generator power level. Electric power generated by the electric generator (28, 32) during operation in the second descent mode is stored in the electrical storage device (30).


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    Titel :

    AIRCRAFT PARALLEL HYBRID PROPULSION SYSTEM


    Weitere Titelangaben:

    PARALLEL-HYBRID-ANTRIEBSSYSTEM FÜR EIN FLUGZEUG
    SYSTÈME DE PROPULSION HYBRIDE-PARALLÈLE D'AÉRONEF


    Beteiligte:
    SWANN PETER (Autor:in)

    Erscheinungsdatum :

    31.05.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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