An aircraft propulsion system (10) comprises first and second co-axial propulsors (13a, 13b), one of the first and second propulsor (13a, 13b) being positioned forward of the other propulsor (13a, 13b). A first electric motor (30a) is configured to drive the first propulsor (13a), and a second electric motor (30b) is configured to drive the second propulsor (13b). The first electric motor (30a) comprising a rotor (32a) radially inwardly of the stator (42a), and the second electric motor (30b) comprises a rotor (32b) radially outwardly of the stator (42b). The stator (42a) of the first electric motor (30a) is mounted to the stator (42b) of the second electric motor (30b).
Aircraft Propulsion System
31.10.2018
Patent
Elektronische Ressource
Englisch