An aircraft propulsion system is disclosed and includes a first gas turbine engine (20A) including a first input shaft (72) driving a first gear system (48A), a first fan (62A) driven by the first gear system (48A), a first generator (64A) supported on the first input shaft (72) and a fan drive electric motor (66A) providing a drive input to the first fan (22A), a second gas turbine engine (20B) including a second input shaft (72) driving a second gear system (48B), a second fan (62B) driven by the second gear system (48B), a second generator (64B) supported on the second input shaft (72) and a second fan drive electric motor (66B) providing a drive input to the second fan (62B) and a controller (68) controlling power output from each of the first and second generators (64A-B) and directing the power output between each of the first and second fan drive electric motors (66A-B).
AIRCRAFT HYBRID PROPULSION FAN DRIVE GEAR SYSTEM DC MOTORS AND GENERATORS
GLEICHSTROMMOTOREN UND -GENERATOREN FÜR FANGETRIEBESYSTEM FÜR FLUGZEUGHYBRIDANTRIEB
MOTEURS ET GÉNÉRATEURS À COURANT CONTINU DE SYSTÈME D'ENGRENAGE D'ENTRAÎNEMENT DE SOUFFLANTE POUR PROPULSION HYBRIDE D'AÉRONEF
2021-08-25
Patent
Electronic Resource
English
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02K JET-PROPULSION PLANTS , Strahltriebwerke |
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