Hybrid electric propulsion system for an aircraft

Patent metadata

Field	Value
Publication number	US-10822100-B2
Application number	US-201715632846-A
Country	US
Kind code	B2
Filing date	Jun 26, 2017
Priority date	Jun 26, 2017
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

A propulsion system for an aircraft includes a propulsor; a turbomachine mechanically coupled to the propulsor for driving the propulsor during a combustion operating mode of the propulsion system and mechanically decoupled from the propulsor during an electric operating mode of the propulsion system; and an electrical power source. The propulsion system further includes an electric machine, the electric machine being electrically coupled to the electrical power source and mechanically coupled to the propulsor during the electric operating mode of the propulsion system such that the electric machine drives the propulsor during the electric operating mode of the propulsion system.

First claim

What is claimed is:

1. A propulsion system for an aircraft, the propulsion system comprising:
a propulsor;
a turbomachine mechanically coupled to the propulsor for driving the propulsor during a combustion operating mode of the propulsion system and mechanically decoupled from the propulsor during an electric operating mode of the propulsion system;
an electrical power source; and
an electric machine, the electric machine being electrically coupled to the electrical power source and mechanically coupled to the propulsor during the electric operating mode of the propulsion system such that the electric machine drives the propulsor during the electric operating mode of the propulsion system;
wherein the turbomachine defines an exhaust, and wherein the turbomachine comprises an aft variable geometry component for at least partially closing off the exhaust when the propulsion system is operating in the electric operating mode.

2. The propulsion system of claim 1 , wherein the turbomachine defines an inlet, and wherein the turbomachine further comprises a forward variable geometry component for at least partially closing off the inlet when the propulsion system is operating in the electric operating mode.

3. The propulsion system of claim 1 , wherein the aft variable geometry component is movable between an open position and a closed position along a radial direction.

4. The propulsion system of claim 1 , wherein the propulsor is configured as an aft fan.

5. The propulsion system of claim 4 , wherein the aft fan is a boundary layer ingestion fan configured to ingest a boundary layer airflow over at least a portion of the aircraft during operation.

6. The propulsion system of claim 1 , wherein the electric machine is an electric motor configured to be positioned within a fuselage of the aircraft when installed.

7. The propulsion system of claim 1 , wherein the electrical power source is an electric energy storage unit.

8. The propulsion system of claim 7 , further comprising:
an electric generator mechanically coupled to the turbomachine, wherein the electric generator is electrically coupled to the electric energy storage unit.

9. The propulsion system of claim 8 , wherein the electric generator is positioned within an aft end of the turbomachine.

10. The propulsion system of claim 1 , further comprising:
a clutch configured to mechanically couple the turbomachine and the propulsor when the propulsion system is operable in the combustion operating mode, and is further configured to mechanically decouple the turbomachine from the propulsor when the propulsion system is operable in the electric operating mode.

11. The propulsion system of claim 1 , wherein the electric machine is an electric motor/generator configured to generate electrical power when the propulsion system is in the combustion operating mode and further configured to drive the propulsor when the propulsion system is in the electrical operating mode.

12. A method for operating a propulsion system for an aircraft, the propulsion system comprising a propulsor, a turbomachine, an electrical power source, and an electric machine, the method comprising:
operating the propulsion system in a combustion operating mode, wherein operating the propulsion system in the combustion operating mode comprises driving the propulsor with the turbomachine to provide a propulsive benefit for the aircraft; and
operating the propulsion system in an electric operating mode, wherein operating the propulsion system in the electric operating mode comprises providing electrical power from the electrical power source to the electric machine and driving the propulsor with the electric machine;
wherein the turbomachine defines an exhaust, and wherein the turbomachine comprises an aft variable geometry component for at least partially closing off the exhaust when the propulsion system is operating in the electric operating mode.

13. The method of claim 12 , wherein operating the propulsion system in the electric operating mode further comprises decoupling the turbomachine from the propulsor.

14. The method of claim 12 , wherein operating the propulsion system in the electric operating mode further comprises operating the aircraft in a cruise operating mode.

15. The method of claim 12 , wherein operating the propulsion system in the combustion operating mode comprises operating the aircraft in a high power operating mode.

16. The method of claim 12 , wherein the propulsion system further comprises an electrical generator, and wherein operating the propulsion system in the combustion operating mode comprises rotating the electric generator of the propulsion system with the turbomachine to generate electrical power.

17. The method of claim 16 , wherein the electrical power source is an electric energy storage unit, and wherein rotating the electric generator with the turbomachine to generate electrical power comprises transferring electrical power from the electric generator to the electric energy storage unit.

18. The method of claim 12 , wherein the electric machine is an electric motor/generator, wherein operating the propulsion system in the combustion operating mode further comprises extracting electrical power from the turbomachine using the electric motor/generator.

19. The method of claim 12 , further comprising:
operating the propulsion system in a wind-milling operating mode, wherein operating the propulsion system in the windmilling operating mode comprises driving the electric machine with the propulsor to generate electrical power and transferring electrical power from the electric machine to the electrical power source.

20. The method of claim 12 , wherein operating the propulsion system in the electric operating mode further comprises closing off an inlet to the turbomachine using a variable geometry component of the turbomachine.

Assignees

• Gen Electric

Inventors

• Dindar Mustafa
• Blodgett Keith E J

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D27/32

  within, or attached to, fuselages · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D27/20 Primary

  within, or attached to, fuselages · CPC title