A disclosed aircraft propulsion system includes a gas turbine engine supported within an aircraft fuselage, a main drive driven by the gas turbine engine and an open rotor propeller system supported outside of the aircraft fuselage separately from the gas turbine engine. A secondary drive that is driven by the main drive drives the open rotor propeller system.
Contra-rotating open rotor distributed propulsion system
11.07.2017
Patent
Elektronische Ressource
Englisch
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