A hybrid electric gas turbine propulsion system (100) may comprise: a first propulsion system (401), a second propulsion system (402), and a third propulsion system (403). The first propulsion system (401) may comprise a first fan (212), a first turbine (252), a first compressor (232), and a first electric motor (190), the first fan (212) operably coupled to the first turbine (252) and the first compressor (232) by a first shaft (126), the first shaft (126) coupled to the first electric motor (190), the first shaft (126) configured to be disposed radially inward of a fuselage (12) of an aircraft (10). The second propulsion system (402) and the third propulsion system (403) may be in accordance with the first propulsion system (401). The hybrid electric gas turbine propulsion system (100) may be symmetric about a vertical plane extending through a neutral aerodynamic axis (104).
SYSTEMS AND METHODS FOR HYBRID ELECTRIC GAS TURBINE ENGINES
SYSTEME UND VERFAHREN FÜR HYBRIDE ELEKTRISCHE GASTURBINENMOTOREN
SYSTÈMES ET PROCÉDÉS POUR MOTEURS À TURBINE ÉLECTRIQUES HYBRIDES
2022-01-26
Patent
Elektronische Ressource
Englisch
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