Propulsion system for an aircraft

Patent metadata

Field	Value
Publication number	US-10696416-B2
Application number	US-201715639200-A
Country	US
Kind code	B2
Filing date	Jun 30, 2017
Priority date	Jun 30, 2017
Publication date	Jun 30, 2020
Grant date	Jun 30, 2020

Abstract

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine such that the turbomachine rotates the propulsor; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.

First claim

What is claimed is:

1. A method for operating a hybrid-electric propulsion system of an aircraft, the hybrid-electric propulsion system comprising a propulsor, a turbomachine, and an electrical system, the electrical system comprising an electric machine coupled to the turbomachine, the method comprising:
operating, by one or more computing devices, the turbomachine such that the turbomachine rotates the propulsor;
receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine;
maintaining a rotational speed of a high pressure system of the turbomachine substantially constant for an initial time period in response to the received command to accelerate the turbomachine, maintaining a temperature within the turbomachine substantially constant for the initial time period, or both; and
providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.

2. The method of claim 1 , wherein the hybrid electric propulsion system further comprises an electric energy storage unit, wherein providing, by the one or more computing devices, electrical power to the electric machine comprises providing, by the one or more computing devices, electrical power to the electric machine from the electric energy storage unit.

3. The method of claim 2 , wherein providing, by the one or more computing devices, electrical power to the electric machine from the electric energy storage unit comprises providing, by the one or more computing devices, at least about fifteen horsepower of mechanical power to the turbomachine, the propulsor, or both with the electric machine.

4. The method of claim 1 , wherein operating, by the one or more computing devices, the turbomachine comprises operating, by the one or more computing devices, the turbomachine in a steady-state flight operating condition.

5. The method of claim 4 , further comprising:
maintaining, by the one or more computing devices, a fuel flow to a combustion section of the turbomachine substantially constant for an initial time period in response to the received command to accelerate the turbomachine.

6. The method of claim 4 , further comprising:
increasing, by the one or more computing devices, one or more clearances within the turbomachine using an active clearance control system of the turbomachine in response to the received command to accelerate the turbomachine.

7. The method of claim 4 , further comprising:
maintaining, by the one or more computing devices, a fuel flow to a combustion section of the turbomachine substantially constant for an initial time period in response to the received command to accelerate the turbomachine, and wherein increasing, by the one or more computing devices, the one or more clearances within the turbomachine using the active clearance control system comprises increasing, by the one or more computing devices, the one or more clearances within the turbomachine using the active clearance control system substantially simultaneously with maintaining, by the one or more computing devices, the fuel flow to the combustion section of the turbomachine substantially constant for the initial time period.

8. The method of claim 7 , wherein increasing, by the one or more computing devices, the one or more clearances within the turbomachine using the active clearance control system comprises increasing, by the one or more computing devices, the one or more clearances within the turbomachine using the active clearance control system substantially simultaneously with providing, by the one or more computing devices, electrical power to the electric machine.

9. The method of claim 4 , wherein operating, by one or more computing devices, the turbomachine in the steady-state flight operating condition comprises extracting, by the one or more computing devices, electrical power from the electric machine.

10. The method of claim 1 , wherein operating, by the one or more computing devices, the turbomachine comprises operating, by the one or more computing devices, the turbomachine in an idle operating condition.

11. The method of claim 10 , wherein receiving, by the one or more computing devices, the command to accelerate the turbomachine while operating the turbomachine in the idle operating condition comprises receiving, by the one or more computing devices, a command to accelerate the turbomachine to a takeoff power level while operating the turbomachine in the idle operating condition.

12. The method of claim 10 , receiving, by the one or more computing devices, the command to accelerate the turbomachine while operating the turbomachine in the idle operating condition comprises receiving, by the one or more computing devices, a thrust increase command.

13. The method of claim 12 , wherein receiving, by the one or more computing devices, the command to accelerate the turbomachine further comprises determining, by the one or more computing devices, a rate of change of commanded thrust increase, and wherein providing, by the one or more computing devices, electrical power to the electric machine comprises modulating, by the one or more computing devices, an amount of electrical power provided to the electric machine based at least in part on the determined rate of change of commanded thrust increase.

14. The method of claim 1 , further comprising:
receiving, by the one or more computing devices, data indicative of an operational parameter of the turbomachine, and wherein providing, by the one or more computing devices, electrical power to the electric machine comprises modulating, by the one or more computing devices, an amount of electrical power provided to the electric machine based at least in part on the received data indicative of the operational parameter of the turbomachine.

15. The method of claim 1 , further comprising:
receiving, by the one or more computing devices, data indicative of an operational parameter of the turbomachine; and
terminating, by the one or more computing devices, the provision of electrical power to the electric machine based at least in part on the received data indicative of the operational parameter of the turbomachine.

16. The method of claim 1 , wherein the hybrid electric propulsion system further comprises an electric energy storage unit, and wherein the method further comprises:
receiving, by the one or more computing devices, data indicative of a state of charge of the electric energy storage unit, and wherein providing, by the one or more computing devices, electrical power to the electric machine comprises modulating, by the one or more computing devices, an amount of electrical power provided to the electric machine based at least in part on the received data indicative of the state of charge of the electric energy storage unit.

17. The method of claim 1 , wherein the hybrid electric propulsion system further comprises an electric energy storage unit, and wherein the method further comprises:
receiving, by the one or more computing devices, data indicative of a state of charge of the electric energy storage unit; and
terminating, by the one or more computing devices, the provision of electrical power to the electric machine based at least in part on the received data indicative of the state of charge of the electric energy storage unit.

18. A hybrid-electric propulsion system for an aircraft comprising:
a propulsor;
a turbomachine coupled to the propulsor for

Assignees

• Gen Electric

Inventors

• Gansler Michael Thomas
• Hon Robert Charles

Classifications

• Y02T50/60

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

• B64D27/35

  Arrangements for on-board electric energy production, distribution, recovery or storage · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• F01D11/20 Primary

  Actively adjusting tip-clearance · CPC title