A hybrid engine includes a gas turbine engine having at least one compressor rotor connected to be driven by at least one turbine rotor. A combustor is connected to receive compressed air from the at least one compressor rotor, and to receive fuel. At least one electric motor 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 includes processing circuitry and a memory storing instructions that, when executed cause the processing circuitry to control a flow of the fuel to the combustor, control the at least one electric motor. Feedback is received on an operating condition of the hybrid engine indicative of a failure of the at least one electric motor. The at least one compressor 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 based on the operating condition not indicating a potential failure of the at least one electric motor. The at least one compressor 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 determining that a failure of the at least one electric motor failure occurred. A method is also disclosed.


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    Title :

    HYBRID AIRCRAFT ENGINE WITH COMPRESSOR CONTROL FOR ELECTRIC MOTOR FAILURE


    Contributors:

    Publication date :

    2025-06-19


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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