Propulsion system for an aircraft

Patent metadata

Field	Value
Publication number	US-10703496-B2
Application number	US-201715493544-A
Country	US
Kind code	B2
Filing date	Apr 21, 2017
Priority date	Apr 21, 2017
Publication date	Jul 7, 2020
Grant date	Jul 7, 2020

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.

First claim

What is claimed is:

1. 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.

2. The propulsion system of claim 1 , wherein the second inverter controller is configured to transfer the electric power to the electric propulsion assembly to operate the electric propulsion assembly at a voltage between 1,000 and 20,000 volts.

3. The propulsion system of claim 1 , wherein the electric power bus is configured to transfer the electric power to the electric propulsion assembly to operate the electric propulsion assembly at an electrical current between about 30 amps and about 1,200 amps.

4. The propulsion system of claim 1 , wherein the electric power source comprises a combustion engine and an electric generator.

5. The propulsion system of claim 4 , wherein the combustion engine is at least one of a turboprop engine or a turbofan engine.

6. The propulsion system of claim 1 , wherein the electric propulsion assembly further comprises a plurality of electric motors and a plurality of propulsors, each propulsor powered by a respective one of the electric motors.

7. The propulsion system of claim 6 , wherein the electric power bus electrically connects the electric power source to each of the plurality of electric motors, and wherein the electric power bus is configured to transfer electrical power to each of the plurality of electric motors at a voltage between 800 and 20,000 volts.

8. The propulsion system of claim 1 , wherein the electric power bus comprises a high voltage cable configured to carry the electrical power having a voltage between 800 and 20,000 volts.

9. The propulsion system of claim 8 , wherein the high voltage cable comprises:
a conductor defining 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.

10. The propulsion system of claim 9 , wherein the high voltage cable further comprises:
a metallic shield enclosing the semi-conductive insulator screen.

11. The propulsion system of claim 10 , wherein the metallic shield is a grounded metallic shield.

12. The propulsion system of claim 8 , wherein the power bus further comprises a coolant system having a cooling line, wherein at least a portion of high voltage cable extends coaxially with the cooling line.

13. The propulsion system of claim 12 , wherein the cooling line comprises a coolant configured to flow therethrough to cool the high voltage cable.

14. 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.

15. The method of claim 14 , wherein transferring the electric power generated with the electric power source to the electric propulsion assembly through the electric power bus comprises transferring the electric power generated with the electric power source to the electric propulsion assembly through the electric power bus, the electric propulsion assembly configured to operate at a voltage between 1,000 volts and 20,000 volts.

16. The method of claim 14 , wherein transferring the electric power generated with the electric power source to the electric propulsion assembly through the electric power bus comprises transferring the electric power generated with the electric power source to the electric propulsion assembly through the electric power bus, the electric propulsion assembly configured to operate at an electrical current between about 30 amps and about 1,200 amps.

17. The method of claim 14 , wherein transferring the electric power generated with the electric power source to the electric propulsion assembly through the electric power bus comprises transferring the electric power generated with the electric power source to the electric propulsion assembly through the cable extending coaxially with a cooling line of a coolant system.

18. 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.

19. The propulsion system for an aircraft of claim 18 , wherein the transferred electric power is below 1,000 volts along a portion of the bus and outputted to the electric propulsion assembly at a voltage between 1,000 and 20,000 volts.

Assignees

• Gen Electric

Inventors

• Vondrell Randy M
• Bouvette Anthony Austin
• Crabtree Glenn David

Classifications

• B64D27/02

  Aircraft characterised by the type or position of power plants · CPC title

• B64D27/32

  within, or attached to, fuselages · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B60L50/10 Primary

  using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title