A hybrid aircraft propulsion system (14). The system (14) comprises a gas turbine engine (16) having a turbine system (30a, 30b, 34) comprising first and second turbine sections (30a, 30b). The gas turbine engine (16) further comprises a first combustor (26) provided upstream in core flow from the turbine system (30a, 30b, 34), and a second combustor (32) provided between the first and second turbine sections (30a, 30b). The hybrid aircraft propulsion system further comprises an energy storage system (74) and an electric propulsion system (72) electrically coupled to the energy storage system (74).
Hybrid electric aircraft propulsion system
2019-06-26
Patent
Elektronische Ressource
Englisch