An aircraft gas turbine engine includes a main engine shaft, a main engine shaft bearing arrangement for rotatably supporting the main engine shaft, and an electric machine including a rotor and a stator. The rotor is mounted to the main engine shaft and is rotatably supported by a further electric machine bearing arrangement extending between the rotor and the stator, and the stator is mounted to static structure of the gas turbine engine.
Gas turbine engine electrical generator
2022-02-01
Patent
Elektronische Ressource
Englisch
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