An aircraft propulsion system includes: a gas turbine engine attached to an airframe of an aircraft; a generator connected to an engine shaft of the engine; a first electric motor driven using electric power including electric power generated by the generator; a rotor attached to the airframe of the aircraft and driven using a driving force output by the first electric motor; and a control device configured to control an operating state of the engine. The control device includes a flow rate controller which reduces the flow rate of fuel supplied to the engine so that the engine does not misfire when a decrease in output of the engine is promoted using a driving force output by a second electric motor included in the generator, and a drive controller which controls the magnitude of the driving force output by the second electric motor so that the temperature of the engine does not exceed an allowable temperature.


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    Titel :

    AIRCRAFT PROPULSION SYSTEM


    Beteiligte:
    OTA AKIRA (Autor:in)

    Erscheinungsdatum :

    15.09.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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