System for secondary fuel injection in a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9228499-B2
Application number	US-201113509549-A
Country	US
Kind code	B2
Filing date	Aug 11, 2011
Priority date	Aug 11, 2011
Publication date	Jan 5, 2016
Grant date	Jan 5, 2016

Abstract

Embodiments of the present disclosure provide a turbine combustor having a primary fuel injection system, a first wall portion disposed about a primary combustion zone downstream from the primary fuel injection system, and a second wall portion disposed downstream from the first wall portion. The turbine combustor also has a secondary fuel injection system disposed between the first wall portion and the second wall portion, where the secondary fuel injection system is removable form the first and second wall portions.

First claim

What is claimed is:

1. A system, comprising:
a turbine combustor, comprising:
a primary fuel injection system;
a first wall portion disposed about a primary combustion zone downstream from the primary fuel injection system;

a second wall portion disposed downstream from the first wall portion; and a modular secondary fuel injection system disposed between the first wall portion and the second wall portion, wherein the modular secondary fuel injection system is removably coupled to the first and second wall portions, and the modular secondary fuel injection system comprises a fuel injector and an axial mounting recess, wherein the axial mounting recess is axial relative to a central axis of the turbine combustor; and
a fastener having a central axis extending substantially parallel to the central axis of the turbine combustor and into the axial mounting recess to couple the modular secondary fuel injection system to the first wall portion or the second wall portion.

2. The system of claim 1 , wherein the first wall portion comprises a liner and the second wall portion comprises a transition piece.

3. The system of claim 2 , wherein the first wall portion further comprises a sleeve or case disposed about the liner, and the second wall portion further comprises an impingement sleeve disposed about the transition piece.

4. The system of claim 1 , further comprising a first seal disposed between the first wall portion and the modular secondary fuel injection system, wherein the first seal is configured to enable movement of the first wall portion relative to the modular secondary fuel injection system.

5. The system of claim 1 , further comprising a second seal disposed between the second wall portion and the modular secondary fuel injection system, wherein the second seal is configured to enable movement of the second wall portion relative to the modular secondary fuel injection system.

6. The system of claim 1 , wherein the modular secondary fuel injection system comprises a plurality of fuel injectors coupled to a support structure, wherein the support structure comprises an inner wall, an outer wall disposed about the inner wall, and an air passage between the inner and outer walls, and the outer wall comprises the axial mounting recess.

7. The system of claim 6 , wherein each fuel injector extends through the outer wall, the air passage, and the inner wall, wherein each fuel injector has a peripheral end substantially flush with the inner wall.

8. The system of claim 6 , wherein each fuel injector extends through the outer wall, the air passage, and the inner wall, wherein each fuel injector has a peripheral end at an offset distance from the inner wall.

9. The system of claim 1 , wherein the modular secondary fuel injection system comprises first and second fuel injectors coupled to a support structure, a first fuel supply line coupled to the first fuel injector, and a second fuel supply line coupled to the second fuel injector, wherein the first and second fuel supply lines are configured to supply fuel independently to the first and second fuel injectors.

10. A system, comprising:
a secondary fuel injection system, comprising:
a support structure comprising an axial mounting recess, wherein the axial mounting recess is axial relative to a central axis of the secondary fuel injection system; and
a plurality of fuel injectors coupled to the support structure, wherein the support structure is configured to removably mount axially between a first wall portion and a second wall portion of a turbine combustor downstream from a primary fuel injection system via a removable fastener having a central axis extending substantially parallel to a central axis of the turbine combustor into the axial mounting recess.

11. The system of claim 10 , wherein the axial mounting recess is configured to axially abut the first wall portion, and the first wall portion is disposed upstream from the second wall portion.

12. The system of claim 11 , further comprising a first seal configured to mount between the first wall portion and the support structure, and a second seal configured to mount between the second wall portion and the support structure, wherein the first and second seals are configured to enable movement of the first and second wall portions relative to one another.

13. The system of claim 10 , wherein the support structure comprises an inner wall, an outer wall disposed about the inner wall, and an air passage between the inner and outer walls, and the outer wall comprises the axial mounting recess.

14. The system of claim 13 , wherein each fuel injector extends through the outer wall, the air passage, and the inner wall, wherein each fuel injector has a peripheral end substantially flush with the inner wall.

15. The system of claim 13 , wherein each fuel injector extends through the outer wall, the air passage, and the inner wall, wherein each fuel injector has a peripheral end at an offset distance from the inner wall.

16. The system of claim 10 , wherein the secondary fuel injection system further comprises a first fuel supply line coupled to a first fuel injector of the plurality of fuel injectors, and a second fuel supply line coupled to the first fuel injector of the plurality of fuel injectors, wherein the first and second fuel supply lines are configured to supply fuel independently to the first fuel injector.

17. The system of claim 10 , wherein each fuel injector comprises a mounting flange, an air tube protruding from the mounting flange, and at least one fuel injection port leading into the air tube.

18. A system, comprising:
a turbine fuel injection module, comprising:
an annular support structure comprising an inner annular wall, an outer annular wall disposed about the inner annular wall, and an air passage extending between the inner and outer annular walls, wherein the air passage is configured to fluidly couple with an annulus defined by a liner and a flow sleeve of a turbine combustor;
a plurality of fuel injectors coupled to the annular support structure, wherein each fuel injector extends through the outer annular wall, the air passage, and the inner annular wall; and

wherein the outer annular wall comprises at least one axial mounting recess configured to receive a fastener to removably mount the outer annular wall of the annular support structure to the turbine combustor, wherein the axial mounting recess is axial relative to a central axis of the turbine combustor and wherein the fastener has a central axis that extends substantially parallel to the central axis of the turbine combustor.

19. The system of claim 18 , wherein the turbine fuel injection module comprises at least one movable seal configured to seal the annular support structure to the turbine combustor while enabling movement of the turbine combustor relative to the annular support structure.

20. The system of claim 19 , wherein the at least one movable seal comprises at least one hula seal disposed along the inner annular wall and at least one piston ring seal disposed along the outer annular wall.

21. The system of claim 8 , wherein the offset distance is equal for each fuel injector.

22. The system of claim 8 , wherein the offset distance is not equal for each fuel injector.

23. The system of claim 8 , wherein the offset distance for each fuel injector alternates between a first offset distance and a second offset distance about a circumference of the turbine combustor.

Assignees

• Stryapunin Sergey Aleksandrovich
• Gen Electric

Inventors

• Stryapunin Sergey Aleksandrovich

Classifications

• F23R3/346

  for staged combustion · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R3/286 Primary

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

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R3/34

  Feeding into different combustion zones · CPC title