A system (10) for an aircraft includes a propulsor rotor (12) and a powerplant (14) configured to drive rotation of the propulsor rotor (12). The powerplant (14) includes a turbo-compounded intermittent internal combustion engine (16) and a dual rotor electric machine (22, 62). The turbo-compounded intermittent internal combustion engine (16) includes a turbine rotor (42) operatively coupled to the propulsor rotor (12) through the dual rotor electric machine (22, 62). The dual rotor electric machine (22, 62) includes a first rotor (64, 66), a second rotor (64, 66), a first stator (67, 68) and a second stator (67, 68). The first stator (67, 68) and the second stator (67, 68) are arranged radially between and axially aligned with the first rotor (64, 66) and the second rotor (64, 66).
AIRCRAFT POWERPLANT WITH ELECTRIC TRANSMISSION(S)
FLUGZEUGTRIEBWERK MIT ELEKTRISCHEM GETRIEBE
GROUPE MOTOPROPULSEUR D'AÉRONEF À TRANSMISSION(S) ÉLECTRIQUE(S)
2025-01-22
Patent
Electronic Resource
English
AIRCRAFT PROPULSION SYSTEM HAVING HYBRID-ELECTRIC POWERPLANT AND COMBUSTION POWERPLANT
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