System and method for purging a fuel manifold of a gas turbine engine through a flow divider valve

Patent metadata

Field	Value
Publication number	US-11536201-B2
Application number	US-202016871130-A
Country	US
Kind code	B2
Filing date	May 11, 2020
Priority date	May 15, 2019
Publication date	Dec 27, 2022
Grant date	Dec 27, 2022

Abstract

Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and supplying pressurized air to the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.

First claim

What is claimed is:

1. A method of operating a gas turbine engine, the gas turbine engine having a first fuel manifold and a second fuel manifold configured to supply fuel to a combustor of the gas turbine engine, the method comprising:
supplying fuel to the combustor by supplying fuel to the first and second fuel manifolds via a common flow divider valve; and
while supplying fuel to the combustor by supplying fuel to the first fuel manifold via the common flow divider valve:
stopping supplying fuel to the second fuel manifold via the common flow divider valve; and
flushing fuel in the second fuel manifold into the combustor by supplying pressurized gas to the second fuel manifold via the common flow divider valve.

2. The method of claim 1 , wherein the pressurized gas includes pressurized air discharged from a reservoir.

3. The method of claim 2 , comprising charging the reservoir with air pressurized by a compressor of the gas turbine engine before supplying the pressurized air to the second fuel manifold.

4. The method of claim 2 , comprising regulating a pressure of the air inside the reservoir.

5. The method of claim 1 , wherein the gas turbine engine is mounted to an aircraft and the method is executed during flight of the aircraft.

6. The method of claim 1 , comprising, when fuel in the second manifold is being flushed into the combustor, maintaining a fuel flow rate to the combustor via the second fuel manifold below a threshold by regulating the pressurized gas supplied to the second fuel manifold.

7. The method of claim 1 , comprising regulating a flow of the pressurized gas supplied to the second fuel manifold.

8. The method of claim 1 , comprising regulating a pressure of the pressurized gas supplied to the second fuel manifold.

9. The method of claim 1 , wherein the common flow divider valve is a spool valve.

10. The method of claim 1 , comprising, while supplying fuel to the first fuel manifold, reducing a fuel supply pressure or flow to the common flow divider valve to cause stopping supplying fuel to the second fuel manifold.

11. The method of claim 10 , comprising, while supplying fuel to the first fuel manifold, reducing the fuel supply pressure or flow to the common flow divider valve to cause the pressurized gas to be supplied to the second fuel manifold.

12. A method of operating a multi-engine power plant of an aircraft, the multi-engine power plant including a first gas turbine engine (FGTE) and a second gas turbine engine (SGTE), the FGTE and SGTE being drivingly connected to a common load, the method comprising:
operating the FGTE and the SGTE to drive the common load, wherein operating the SGTE includes supplying fuel to a combustor of the SGTE by supplying fuel to a first fuel manifold and a second fuel manifold of the SGTE via a common flow divider valve; and
while operating the FGTE and supplying fuel to the combustor of the SGTE by supplying fuel to the first fuel manifold of the SGTE via the common flow divider valve:
stopping supplying fuel to the second fuel manifold of the SGTE via the common flow divider valve, and
supplying pressurized gas to the second fuel manifold of the SGTE via the common flow divider valve to flush fuel in the second fuel manifold into the combustor of the SGTE.

13. The method of claim 12 , wherein the common load includes a rotary wing of the aircraft and the method is executed during flight of the aircraft.

14. The method of claim 12 , wherein the pressurized gas includes pressurized air discharged from a reservoir.

15. The method of claim 14 , comprising charging the reservoir with air pressurized by a compressor of the SGTE before supplying the pressurized air to the second fuel manifold of the SGTE.

16. The method of claim 14 , comprising charging the reservoir with air pressurized by a compressor of the FGTE before supplying the pressurized air to the second fuel manifold of the SGTE.

17. The method of claim 12 , comprising, when fuel in the second manifold is being flushed into the combustor of the SGTE, maintaining a fuel flow rate to the combustor via the second fuel manifold below a threshold by regulating the pressurized gas supplied to the second fuel manifold.

18. The method of claim 12 , comprising, while supplying fuel to the first fuel manifold of the SGTE, reducing a fuel supply pressure or flow to the common flow divider valve to cause both the stopping supplying fuel to the second fuel manifold of the SGTE and the supplying pressurized gas to the second fuel manifold of the SGTE.

Assignees

• Pratt & Whitney Canada

Inventors

• Jarvo James Robert
• Saintignan Cédric
• Cirtwill Joseph Daniel Maxim
• Mccaldon Kian
• Tremblay Marc-Andre
• Waddleton David

Classifications

• F05D2220/329

  in helicopters · CPC title

• F02C9/42

  specially adapted for the control of two or more plants simultaneously · CPC title

• F02C6/16

  for storing compressed air · CPC title

• F05D2260/602

  Drainage · CPC title

• F02C7/222

  Fuel flow conduits, e.g. manifolds · CPC title