Propulsion system for an aircraft

Patent metadata

Field	Value
Publication number	US-10538337-B2
Application number	US-201715493623-A
Country	US
Kind code	B2
Filing date	Apr 21, 2017
Priority date	Apr 21, 2017
Publication date	Jan 21, 2020
Grant date	Jan 21, 2020

Abstract

A propulsion system for an aircraft includes an electric power source, an electric propulsor assembly having an electric motor and a propulsor configured to generate thrust for the aircraft, and a power bus electrically connecting the electric power source to the electric propulsor assembly such that the electric power source powers the electric propulsor assembly. The power bus includes an electric line and a fluid cooling system, the fluid cooling system extending along at least a portion of a length of the electric line. The fluid cooling system is in thermal communication with the electric line for cooling the electric line during operation and is further in thermal communication with the electric motor of the electric propulsor assembly for cooling the electric motor of the electric propulsor assembly.

First claim

What is claimed is:

1. A propulsion system for an aircraft, the propulsion system comprising:
an electric power source;
an electric propulsor assembly comprising an electric motor and a propulsor configured to generate thrust for the aircraft; and
a power bus electrically connecting the electric power source to the electric propulsor assembly such that the electric power source powers the electric propulsor assembly, the power bus comprising an electric line and a fluid cooling system, wherein the fluid cooling system extends along at least a portion of a length of the electric line, the fluid cooling system in thermal communication with the electric line for cooling the electric line during operation and further in thermal communication with the electric motor of the electric propulsor assembly for cooling the electric motor of the electric propulsor assembly.

2. The propulsion system of claim 1 , wherein the fluid cooling system includes a fluid cooling conduit with a cooling fluid positioned therein, wherein at least a portion of the electric line extends in thermal communication with the fluid cooling conduit.

3. The propulsion system of claim 2 , wherein at least a portion of the electric line extends within the fluid cooling conduit.

4. The propulsion system of claim 2 , wherein the electric line comprises a conductor, and wherein the fluid cooling conduit extends within the conductor.

5. The propulsion system of claim 2 , wherein at least a portion of the electric line comprises a plurality of conductors, and wherein the fluid cooling conduit is braided together with the plurality of conductors.

6. The propulsion system of claim 2 , wherein the fluid cooling system further comprises a heat exchanger in fluid communication with the fluid cooling conduit.

7. The propulsion system of claim 2 , wherein the fluid cooling system further comprises a first fluid transfer box and a second fluid transfer box with the fluid cooling conduit extending therebetween.

8. The propulsion system of claim 2 , wherein the electric line electrically connects the electric power source to the electric propulsor assembly, and wherein the fluid cooling conduit extends along at least about fifty percent of a length of the electric line.

9. The propulsion system of claim 1 , wherein the electric line is a first electric line, wherein the power bus further comprises a second electric line, wherein the fluid cooling system includes a first fluid cooling conduit and a second fluid cooling conduit, wherein at least a portion of the first electric line extends in thermal communication with the first fluid cooling conduit, and wherein at least a portion of the second electric line extends in thermal communication with the second fluid cooling conduit.

10. The propulsion system of claim 9 , wherein the first fluid cooling conduit defines a coolant flow direction towards the electric propulsor assembly, and wherein the second fluid cooling conduit defines a coolant flow direction towards the electric power source.

11. The propulsion system of claim 1 , wherein the fluid cooling system further comprises a pump powered by the electric power source.

12. The propulsion system of claim 1 , wherein the fluid cooling system is an oil cooling system utilizing an oil as a coolant.

13. An aircraft extending between a forward end and an aft end comprising:
a fuselage;
an empennage at the aft end of the aircraft;
a wing assembly extending from the fuselage; and
a propulsion system comprising
an electric power source comprising a combustion motor and a generator, the combustion motor attached to at least one of the fuselage, the empennage, or the wing assembly;
an electric propulsor assembly attached to at least one of the fuselage, the empennage, or the wing assembly and configured to generate thrust for the aircraft; and
a power bus electrically connecting the electric power source to the electric propulsor assembly such that the electric power source powers the electric propulsor assembly, the power bus comprising an electric line and a fluid cooling system, wherein the fluid cooling system extends along a length of the electric line and in thermal communication with the electric line for cooling the electric line during operation.

14. The aircraft of claim 13 , wherein the wing assembly includes a first wing and a second wing, wherein the combustion engine is attached to the first wing, and wherein the electric propulsor assembly is attached to at least one of the second wing, the empennage, or the fuselage.

15. The aircraft of claim 14 , wherein the electric propulsor assembly is attached to at least one of the empennage or the fuselage at the aft end of the aircraft.

16. The aircraft of claim 14 , wherein the fluid cooling system includes a fluid cooling conduit with a cooling fluid positioned therein, wherein at least a portion of the electric line extends in thermal communication with the fluid cooling conduit.

17. The aircraft of claim 16 , wherein the fluid cooling conduit extends from the first wing to at least one of the second wing, the empennage, or the fuselage.

18. The aircraft of claim 16 , wherein the fluid cooling system further comprises a heat exchanger in fluid communication with the fluid cooling conduit.

19. The aircraft of claim 18 , wherein the heat exchanger is positioned in thermal communication with an outside surface of the fuselage of the aircraft or an outer surface of the wing of the aircraft.

20. A propulsion system for an aircraft, the propulsion system comprising:
an electric power source;
an electric propulsor assembly configured to generate thrust for the aircraft; and
a power bus electrically connecting the electric power source to the electric propulsor assembly such that the electric power source powers the electric propulsor assembly, the power bus comprising a first electric line and a second electric line, the power bus further comprising a fluid cooling system having a first fluid cooling conduit defining a coolant flow direction towards the electric propulsor assembly and a second fluid cooling conduit defining a coolant flow direction towards the electric power source, at least a portion of the first electric line extending in thermal communication with the first fluid cooling conduit and at least a portion of the second electric line extending in thermal communication with the second fluid cooling conduit.

Assignees

• Gen Electric

Inventors

• Vondrell Randy M
• Bouvette Anthony Austin
• Hon Robert Charles

Classifications

• B60L50/16

  with provision for separate direct mechanical propulsion · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• H02K9/19

  for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil · CPC title

• B64D33/10

  Radiator arrangement · CPC title

• B60L2200/10

  Air crafts · CPC title