Combustor assembly with primary and auxiliary injector fuel control

Patent metadata

Field	Value
Publication number	US-10815893-B2
Application number	US-201815862379-A
Country	US
Kind code	B2
Filing date	Jan 4, 2018
Priority date	Jan 4, 2018
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

A gas turbine combustor assembly includes: a primary combustion chamber in fluid communication with a primary fuel outlet of a primary fuel injector; a torch igniter coupled to the primary combustion chamber, the torch igniter including an auxiliary combustion chamber and an auxiliary fuel injector having an auxiliary fuel outlet in fluid communication with the auxiliary combustion chamber; and a fuel circuit including a first supply flowpath between a fuel inlet and the primary fuel injector, a second supply flowpath between the fuel inlet and the auxiliary fuel injector, and a bypass flowpath between the auxiliary fuel injector and the primary fuel injector.

First claim

What is claimed is:

1. A gas turbine combustor assembly, comprising:
a primary combustion chamber in fluid communication with a primary fuel outlet of a primary fuel injector;
a torch igniter coupled to the primary combustion chamber, the torch igniter comprising an auxiliary combustion chamber and an auxiliary fuel injector having an auxiliary fuel outlet in fluid communication with the auxiliary combustion chamber; and
a fuel circuit comprising a first supply flowpath between a fuel inlet and the primary fuel injector, a second supply flowpath between the fuel inlet and the auxiliary fuel injector, and a bypass flowpath extending from the auxiliary fuel injector directly to the primary fuel injector,
wherein the auxiliary fuel injector is configured to receive fuel flowing through the second supply flowpath, eject a portion of the fuel flow through the auxiliary fuel outlet and recirculate another portion of the fuel flow to the bypass flowpath.

2. The combustor assembly of claim 1 , wherein the first supply flowpath, the second supply flowpath, and the bypass flowpath are each defined by separate fluid conduits.

3. The combustor assembly of claim 2 , wherein the bypass flowpath is configured such that a pressure difference between the auxiliary fuel injector and the primary fuel injector defines a proportion of the fuel flow ejected through the auxiliary fuel outlet and the fuel flow recirculated to the bypass flowpath.

4. The combustor assembly of claim 2 , wherein the bypass flowpath comprises an electromechanically controlled flow regulation device.

5. The combustor assembly of claim 1 , wherein the bypass flowpath provides a direct line of fluid communication between the auxiliary fuel injector and the primary fuel injector.

6. The combustor assembly of claim 5 , wherein the bypass flowpath is configured to direct a bypass flow of fuel from the auxiliary fuel injector to the primary fuel injector.

7. The combustor assembly of claim 1 , wherein the fuel circuit further comprises a flow regulator configured to simultaneously adjust the rate of fuel flow from the fuel inlet to the respective first and second supply flowpaths, and the rate of fuel flow along the bypass flowpath.

8. The combustor assembly of claim 7 , wherein the primary fuel injector comprises one of multiple fuel injectors coupled to a common fuel intake manifold residing on the first supply flowpath downstream of the flow regulator.

9. The combustor assembly of claim 8 , wherein the bypass flowpath is in fluid communication with the fuel intake manifold.

10. The combustor assembly of claim 7 , wherein the flow regulator comprises a spring-biased piston valve having an inlet port in fluid communication with the fuel inlet and a reference port in fluid communication with a reference pressure source, and wherein a pressure difference between the inlet port and the reference port urges a piston against a biasing force of a spring to control fuel flow through the valve to the first and second supply flowpaths.

11. The combustor assembly of claim 1 , wherein the second supply flowpath comprises an electromechanically controlled flow regulation device.

12. A gas turbine engine, comprising:
a compressor configured to produce a high-pressure airflow;
a turbine coupled to the compressor and configured to drive the compressor; and
a combustor assembly configured to receive the high-pressure airflow from the compressor and produce a high-temperature, high-pressure airflow to the turbine, the combustor assembly comprising:
a primary combustion chamber in fluid communication with a primary fuel outlet of a primary fuel injector;
a torch igniter coupled to the primary combustion chamber, the torch igniter comprising an auxiliary combustion chamber and an auxiliary fuel injector having an auxiliary fuel outlet in fluid communication with the auxiliary combustion chamber; and
a fuel circuit comprising a first supply flowpath between a fuel inlet and the primary fuel injector, a second supply flowpath between the fuel inlet and the auxiliary fuel injector, and a bypass flowpath extending from the auxiliary fuel injector directly to the primary fuel injector,
wherein the auxiliary fuel injector is configured to receive fuel flowing through the second supply flowpath, eject a portion of the fuel flow through the auxiliary fuel outlet and recirculate another portion of the fuel flow to the bypass flowpath.

13. The gas turbine engine of claim 12 , wherein the first supply flowpath, the second supply flowpath, and the bypass flowpath are each defined by separate fluid conduits.

14. The gas turbine engine of claim 13 , wherein the bypass flowpath is configured such that a pressure difference between the auxiliary fuel injector and the primary fuel injector defines a proportion of the fuel flow ejected through the auxiliary fuel outlet and the fuel flow recirculated to the bypass flowpath.

15. The gas turbine engine of claim 13 , wherein the bypass flowpath comprises an electromechanically controlled flow regulation device.

16. The gas turbine engine of claim 12 , wherein the bypass flowpath provides a direct line of fluid communication between the auxiliary fuel injector and the primary fuel injector.

17. The gas turbine engine of claim 16 , wherein the bypass flowpath is configured to direct a bypass flow of fuel from the auxiliary fuel injector to the primary fuel injector.

18. The gas turbine engine of claim 12 , wherein the fuel circuit further comprises a flow regulator configured to simultaneously adjust the rate of fuel flow from the fuel inlet to the respective first and second supply flowpaths, and the rate of fuel flow along the bypass flowpath.

19. The gas turbine engine of claim 18 , wherein the primary fuel injector comprises one of multiple fuel injectors coupled to a common fuel intake manifold residing on the first supply flowpath downstream of the flow regulator.

20. The gas turbine engine of claim 19 , wherein the bypass flowpath is in fluid communication with the fuel intake manifold.

21. The gas turbine engine of claim 18 , wherein the flow regulator comprises a spring-biased piston valve having an inlet port in fluid communication with the fuel inlet and a reference port in fluid communication with a reference pressure source, and wherein a pressure difference between the inlet port and the reference port urges a piston against a biasing force of a spring to control fuel flow through the valve to the first and second supply flowpaths.

22. The gas turbine engine of claim 12 , wherein the second supply flowpath comprises an electromechanically controlled flow regulation device.

23. A method of delivering fuel to a torch igniter and a primary combustor in a combustor assembly, the method comprising:
receiving a total burn flow of fuel;
routing a torch supply fuel flow to an auxiliary fuel injector of the torch igniter, the torch supply fuel flow comprising at least a portion of the total burn flow;
ejecting a discharge portion of the torch supply fuel flow into an auxiliary combustion chamber of the torch igniter; and
recirculating a bypass portion of the torch supply fuel flow to a primary fuel injector of the primary combustor along a bypass flowpath extending from the auxiliary fuel injector directly to the primary fuel injector.

Assignees

• Woodward Inc

Inventors

• Kleckler Joel W
• Dam Bidhan

Classifications

• F23R3/28 Primary

  characterised by the fuel supply (burners F23D) · CPC title

• F02C9/34

  Joint control of separate flows to main and auxiliary burners · CPC title

• F23R3/34

  Feeding into different combustion zones · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• F02C3/06

  the compressor comprising only axial stages (F02C3/10 takes precedence) · CPC title