Combustor with axial fuel staging system and gas turbine having the same

Patent metadata

Field	Value
Publication number	US-11313561-B2
Application number	US-202016854953-A
Country	US
Kind code	B2
Filing date	Apr 22, 2020
Priority date	May 30, 2019
Publication date	Apr 26, 2022
Grant date	Apr 26, 2022

Abstract

A combustor has an axial fuel staging system to allow a fuel-air mixture to be injected from two axially spaced stages using an injector for injection of a secondary fuel-air mixture. The combustor includes a liner defining a combustion chamber; a transition piece coupled to a rear end of the liner; a flow sleeve defining an annular channel by surrounding the liner and the transition piece; and at least one injector disposed on a circumferential position of the flow sleeve to inject a mixture of fuel and air into the combustion chamber. Each of the at least one injector includes an injection pipe extending radially and passing through both the flow sleeve and either of the liner and the transition piece; a plate coupled to the injection pipe; and a plurality of mixing passages formed through the plate. The combustor improves fuel-air mixing and prevents flash back.

First claim

What is claimed is:

1. A combustor comprising:
a liner defining a combustion chamber;
a transition piece coupled to a rear end of the liner;
a flow sleeve defining an annular channel by surrounding the liner and the transition piece; and
at least one injector disposed on a circumferential position of the flow sleeve and configured to inject a mixture of fuel and air into the combustion chamber, each of the at least one injector comprising:
an injection pipe extending radially and passing through both the flow sleeve and either of the liner and the transition piece;
a plate coupled to the injection pipe;
a plurality of mixing passages formed through the plate;
a damper for defining a constant volume, the damper establishing an internal volume of the damper that is separate from an external volume of the damper and having at least one communication hole enabling communication between the internal and external volumes;
a cylinder slidably coupled through each communication hole of the at least one communication hole; and
a communication channel formed through the cylinder and configured to communicate with the internal and external volumes,

wherein each of the at least one injector further comprises a plurality of fuel ports through which the fuel is injected into the plurality of mixing passages from a fuel plenum defined in the plate,
wherein the fuel ports are disposed to face each other in each of the plurality of mixing passages of the plate to improve a degree of mixing by mutual impingement of the fuel, and
wherein the cylinder comprises a flange on each end of the cylinder.

2. The combustor according to claim 1 , further comprising a fuel supply channel that extends in an axial direction of the flow sleeve and is configured to supply the fuel to the fuel plenum.

3. The combustor according to claim 1 , wherein the injection pipe includes a cylindrical pipe.

4. The combustor according to claim 1 , wherein the injection pipe includes a narrowed portion formed on a downstream side of the plate, the narrowed portion including a first end disposed toward the flow sleeve and a second end disposed toward the liner or the transition piece, the narrowed portion becoming narrower from the first end to the second end.

5. The combustor according to claim 4 , wherein the narrowed portion of the injection pipe has an inclination of 30° to 60°.

6. The combustor according to claim 4 , further comprising a guide member coupled to the plate and configured to guide the mixture of the fuel and the air exiting the plurality of mixing passages to a radial center of the injection pipe.

7. The combustor according to claim 6 , wherein the guide member has a cone shape.

8. The combustor according to claim 6 ,
wherein the narrowed portion of the injection pipe includes outer surfaces that are inclined with respect to the liner or the transition piece,
wherein the guide member includes outer surfaces that are inclined with respect to an axial center line of the annular channel, and
wherein the inclination of the narrowed portion is substantially equal to the inclination of the guide member.

9. The combustor according to claim 1 , wherein the damper is coupled to the plate and is configured to cover the plate.

10. The combustor according to claim 1 , wherein the at least one injector consists of a plurality of injectors disposed on a single plane that passes through a circumference of the flow sleeve.

11. The combustor according to claim 10 ,
wherein each of the plurality of injectors of the at least one injector has an axial center line and is disposed at an inclined angle formed by the axial center line intersecting a tangent line of the flow sleeve drawn to intersect the axial center line, and
wherein the plurality of injectors include one or more injectors disposed at an inclined angle that is different from the inclined angle of other injectors of the plurality of injectors.

12. The combustor according to claim 1 , wherein the plurality of mixing passages are arranged so as to be uniformly distributed in the plate.

13. The combustor according to claim 1 , further comprising a plurality of nozzle assemblies coupled to the liner and configured to inject a primary fuel and air mixture into a primary combustion zone for one of two axial fuel stages.

14. The combustor according to claim 13 , wherein the mixture of the fuel and the air of the at least one injector is a secondary fuel and air mixture to be injected into a secondary combustion zone occurring in the combustion chamber downstream from the primary combustion zone.

15. A gas turbine comprising a compressor configured to compress air and form compressed air; a combustor configured to produce combustion gas by mixing fuel with the compressed air and burning a mixture of the fuel and the air; and a turbine configured to generate a rotational force from the combustion gas,
wherein the combustor comprises a liner defining a combustion chamber; a transition piece coupled to a rear end of the liner; a flow sleeve defining an annular channel by surrounding the liner and the transition piece; and at least one injector disposed on a circumferential position of the flow sleeve and configured to inject the mixture of the fuel and the air into the combustion chamber, and
wherein each of the at least one injector comprises:
an injection pipe extending radially and passing through both the flow sleeve and either of the liner and the transition piece;
a plate coupled to the injection pipe;
a plurality of mixing passages formed through the plate;
a damper for defining a constant volume, the damper establishing an internal volume of the damper that is separate from an external volume of the damper and having at least one communication hole enabling communication between the internal and external volumes;
a cylinder slidably coupled through each communication hole of the at least one communication hole; and
a communication channel formed through the cylinder and configured to communicate with the internal and external volumes,

wherein each of the at least one injector further comprises a plurality of fuel ports through which the fuel is injected into the plurality of mixing passages from a fuel plenum defined in the plate,
wherein the fuel ports are disposed to face each other in each of the plurality of mixing passages of the plate to improve a degree of mixing by mutual impingement of the fuel, and
wherein the cylinder comprises a flange on each end of the cylinder.

16. The gas turbine according to claim 15 ,
wherein the combustor further comprises a plurality of nozzle assemblies coupled to the liner and configured to inject a primary fuel and air mixture into a primary combustion zone for one of two axial fuel stages, and
wherein the mixture of the fuel and the air of the at least one injector is a secondary fuel and air mixture to be injected into a secondary combustion zone occurring in the combustion chamber downstream from the primary combustion zone.

Assignees

• Doosan Heavy Ind & Construction Co Ltd

Inventors

• Roh U Jin

Classifications

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F23R2900/00014

  Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators · CPC title

• F23R3/346 Primary

  for staged combustion · CPC title

• Y02T50/60

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