A hybrid engine (20) includes a gas turbine engine (21) having at least one compressor rotor connected to be driven by at least one turbine rotor. A combustor (40) is connected to receive compressed air from the at least one compressor rotor, and to receive fuel. At least one electric motor (42, 48) is connected to drive the at least one compressor rotor to supplement drive in combination with the at least one turbine rotor. A hybrid engine controller (50) includes processing circuitry (96) and a memory (98) storing instructions that, when executed cause the processing circuitry (96) to control a flow of the fuel to the combustor (40), control the at least one electric motor (42, 48). Feedback is received on an operating condition of the hybrid engine (20) indicative of a failure of the at least one electric motor (42, 48). The at least one compressor (30, 34) is controlled in a first mode to operate at a compressor pressure ratio spaced from a stall pressure ratio that could result in a stall of the at least one compressor (30, 34) based on the operating condition not indicating a potential failure of the at least one electric motor (42, 48). The at least one compressor (30, 34) is controlled to move to a second mode where the compressor pressure ratio is closer to the stall pressure ratio than in the first mode based on the hybrid engine controller (50) determining that a failure of the at least one electric motor failure occurred. A method is also disclosed.


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    Titel :

    HYBRID AIRCRAFT ENGINE WITH COMPRESSOR CONTROL FOR ELECTRIC MOTOR FAILURE


    Weitere Titelangaben:

    HYBRIDFLUGZEUGMOTOR MIT VERDICHTERSTEUERUNG FÜR ELEKTROMOTORAUSFALL
    MOTEUR D'AÉRONEF HYBRIDE À COMMANDE DE COMPRESSEUR POUR PANNE DE MOTEUR ÉLECTRIQUE


    Beteiligte:
    AMARI MARTIN (Autor:in) / VAN NOPPEN WILLIAM L (Autor:in) / ADAMS JOSHUA (Autor:in) / COLLOPY GARY (Autor:in)

    Erscheinungsdatum :

    18.06.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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