Propulsion system for an aircraft
First Claim
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1. A propulsion system for an aircraft comprising a first wing and a second wing, the propulsion system comprising:
- an electric generator;
a turbomachine configured to be mounted to the first wing of the aircraft and comprising a turbine section and a shaft, the shaft rotatable with at least a portion of the turbine section, the turbomachine operable with the electric generator;
a first propulsor mechanically coupled to the shaft of the turbomachine; and
a second propulsor assembly configured to be mounted to the second wing at a location away from the turbomachine and the first propulsor, the electric generator in electrical communication with the second propulsor assembly for powering the second propulsor assembly, wherein the second propulsor assembly further includes an electric motor.
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Abstract
A propulsion system for an aircraft includes an electric generator and a turbomachine. The turbomachine is configured to be mounted to a first wing of the aircraft and is operable with the electric generator. The propulsion system additionally includes a first propulsor mechanically coupled to a shaft of the turbomachine and a second propulsor assembly configured to be mounted at a location away from the turbomachine and the first propulsor. The electric generator is in electrical communication with the second propulsor assembly for powering the second propulsor assembly.
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Citations
20 Claims
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1. A propulsion system for an aircraft comprising a first wing and a second wing, the propulsion system comprising:
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an electric generator; a turbomachine configured to be mounted to the first wing of the aircraft and comprising a turbine section and a shaft, the shaft rotatable with at least a portion of the turbine section, the turbomachine operable with the electric generator; a first propulsor mechanically coupled to the shaft of the turbomachine; and a second propulsor assembly configured to be mounted to the second wing at a location away from the turbomachine and the first propulsor, the electric generator in electrical communication with the second propulsor assembly for powering the second propulsor assembly, wherein the second propulsor assembly further includes an electric motor. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 19)
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9. An aircraft comprising:
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a fuselage, a first wing, and a second wing, the first wing and a portion of the fuselage defining a first side, and the second wing and another portion of the fuselage defining a second side; and an asymmetric propulsion system comprising an electric generator; a turbomachine mounted to the first side of the aircraft, the turbomachine comprising a turbine section and a shaft, the shaft rotatable with at east a portion of the turbine section, the turbomachine operable with the electric generator; a first propulsor mechanically coupled to the shaft of the turbomachine; and a second propulsor assembly, including an electric motor, mounted to the second side, the electric generator in electrical communication with the electric motor for powering the second propulsor assembly. - View Dependent Claims (10, 11, 12, 13, 14, 15, 16, 20)
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17. A method for operating a propulsion system of an aircraft comprising:
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powering, with a turbomachine mounted to a first side of the aircraft, a first propulsor in mechanical communication with the turbomachine; generating electrical power with an electric generator powered by the turbomachine; and powering an electric motor included in a second propulsor assembly mounted to a second side of the aircraft with the electrical power generated by the electric generator. - View Dependent Claims (18)
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Specification