Propulsion system for an aircraft
AssigneeGeneral Electric Company
InventorsRandy M. Vondrell, Anthony Austin Bouvette, Glenn David Crabtree
Life of this patent
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Abstract
A propulsion system for an aircraft includes an electric power source and an electric propulsion assembly having an electric motor and a propulsor, the propulsor powered by the electric motor. The propulsion system also includes an electric power bus electrically connecting the electric power source to the electric propulsion assembly. The electric power source is configured to provide electrical power to the electric power bus, and the electric power bus is configured to transfer the electric power to the electric propulsion assembly at a voltage exceeding 800 volts.
Claims19
A propulsion system for an aircraft comprising:
- an electric power source;
- an electric propulsion assembly comprising an electric motor and a propulsor, the propulsor powered by the electric motor;
- an electric power bus electrically connecting the electric power source to the electric propulsion assembly, the electric power source configured to provide electrical power to the electric power bus, and the electric power bus configured to transfer the electric power to the electric propulsion assembly at a voltage between 800 and 20,000 volts;
- and
- first and second inverter converter controllers positioned in series and electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly, the first inverter converter controller configured to increase a voltage of the electric power received from the power source and the second inverter converter controller configured to decrease the voltage of the electric power received from the first inverter controller.
A method for operating a propulsion system for an aircraft comprising:
- generating electric power with an electric power source;
- transferring the electric power generated with the electric power source to an electric propulsion assembly through an electric power bus through a cable including a conductor forming a central portion of the cable, a semi-conductive conductor screen enclosing the conductor, an insulation layer enclosing the conductor screen, and a semi-conductive insulator screen enclosing the insulation layer at a reduced voltage from an outputted voltage of the electric power source;
- and
- generating thrust for the aircraft with the electric propulsion assembly, the electric propulsion assembly being powered by the electric power transferred through the electric power bus.
A propulsion system for an aircraft comprising:
- an electric power source including a combustion engine and an electric generator;
- an electric propulsion assembly including an electric motor and a propulsor, the propulsor powered by the electric motor;
- and
- an electric power bus electrically connecting the electric power source to the electric propulsion assembly, the electric power source configured to provide electrical power to the electric power bus, and the electric power bus configured to transfer the electric power to the electric propulsion assembly, wherein the electric propulsion assembly operates at a voltage between 1,000 and 20,000 volts.
Dependencies are inferred from the claim text.