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.
HYBRID AIRCRAFT ENGINE WITH COMPRESSOR CONTROL FOR ELECTRIC MOTOR FAILURE
HYBRIDFLUGZEUGMOTOR MIT VERDICHTERSTEUERUNG FÜR ELEKTROMOTORAUSFALL
MOTEUR D'AÉRONEF HYBRIDE À COMMANDE DE COMPRESSEUR POUR PANNE DE MOTEUR ÉLECTRIQUE
18.06.2025
Patent
Elektronische Ressource
Englisch
ELECTRIC AIRCRAFT ENGINE AND COMPRESSOR FOR ENGINE RETROFIT
Europäisches Patentamt | 2024
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Europäisches Patentamt | 2024
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