A propulsion system for an aircraft includes at least two gas turbine engines and at least one auxiliary propulsion fan. The at least one auxiliary propulsion fan is configured to selectively receive a motive force from either or both of the at least two gas turbine engines through at least one shaft operatively coupled to the at least one auxiliary propulsion fan.
Aircraft system with distributed propulsion
2021-02-02
Patent
Electronic Resource
English
HYBRID ELECTRIC AIRCRAFT SYSTEM WITH DISTRIBUTED PROPULSION
European Patent Office | 2019
|Hybrid electric aircraft system with distributed propulsion
European Patent Office | 2020
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