Flow sleeve for a combustion module of a gas turbine

Patent metadata

Field	Value
Publication number	US-9360217-B2
Application number	US-201313845485-A
Country	US
Kind code	B2
Filing date	Mar 18, 2013
Priority date	Mar 18, 2013
Publication date	Jun 7, 2016
Grant date	Jun 7, 2016

Abstract

A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.

First claim

What is claimed is:

1. A combustion module for a combustor of a gas turbine, comprising:
a. an annular fuel distribution manifold disposed at an upstream end of the combustion module, the fuel distribution manifold including an annular support sleeve having an inner surface;
b. a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner, the flow sleeve extending downstream from the fuel distribution manifold and terminating at the aft frame, the flow sleeve extending continuously between the support sleeve and the aft frame; and
c. wherein a forward portion of the flow sleeve is positioned concentrically within the support sleeve such that the fuel distribution manifold forms an annulus around the forward portion of the flow sleeve, the forward portion being slidingly engaged with the inner surface of the support sleeve.

2. The combustion module as in claim 1 , further comprising a continuous cooling flow passage defined between the combustion liner and the flow sleeve that extends between the aft frame and the forward portion of the flow sleeve.

3. The combustion module as in claim 1 , wherein the combustion liner comprises a conical section and a transition section, the flow sleeve being radially separated from the combustion liner at a first radial distance with respect to the conical section and a second radial distance with respect to the transition section.

4. The combustion module as in claim 1 , wherein the flow sleeve is radially separated from the combustion liner at a radial distance that varies along the length of the combustion liner.

5. The combustion module as in claim 1 , wherein the flow sleeve at least partially defines a plurality of impingement cooling passages.

6. The combustion module as in claim 1 , wherein the fuel injection assembly further comprises a plurality of fuel injectors that extend through the flow sleeve and the combustion liner so as to provide for fluid communication into the combustion liner, each of the fuel injectors being fluidly connected to the fuel distribution manifold.

7. The combustion module as in claim 1 , wherein the flow sleeve comprises of two or more semi-annular flow sleeve sections joined together to surround the combustion liner.

8. The combustion module as in claim 1 , further comprising a compression seal that extends radially between the forward portion of the flow sleeve and the inner surface of the support sleeve.

9. A combustor comprising:
a. an end cover coupled to an outer casing that surrounds the combustor;
b. an axially extending fuel nozzle that extends downstream from the end cover;
c. an annular cap assembly that extends radially and axially within the combustor, the cap assembly at least partially surrounding the fuel nozzle; and
d. a combustion module having an annular fuel distribution manifold that circumferentially surrounds at least a portion of the cap assembly and a fuel injection assembly that extends downstream from the fuel distribution manifold, wherein the annular fuel distribution manifold is mounted between the end cover and the outer casing, the fuel injection assembly comprising:
i. an annular combustion liner that extends downstream from the cap assembly and that terminates at an aft frame; and
ii. an annular flow sleeve that surrounds the combustion liner, the flow sleeve having a forward portion positioned concentrically within the fuel distribution manifold and an aft end coupled to the aft frame, wherein the fuel distribution manifold forms an annulus around the forward portion of the flow sleeve, and wherein the flow sleeve extends continuously between the forward portion and the aft frame.

10. The combustor as in claim 9 , further comprising a continuous cooling flow passage defined between the combustion liner and the flow sleeve that extends between the aft frame and the forward portion of the flow sleeve.

11. The combustor as in claim 9 , wherein the combustion liner comprises a conical section and a transition section, the flow sleeve being radially separated from the combustion liner at a first radial distance with respect to the conical section and a second radial distance with respect to the transition section.

12. The combustor as in claim 9 , wherein the flow sleeve is radially separated from the combustion liner at a radial distance that varies along the length of the combustion liner.

13. The combustor as in claim 9 , wherein the flow sleeve at least partially defines a plurality of impingement cooling passages.

14. The combustor as in claim 9 , wherein the fuel injection assembly further comprises a plurality of fuel injectors that extend through the flow sleeve and the combustion liner so as to provide for fluid communication into the combustion liner downstream from the fuel nozzle, each of the fuel injectors being fluidly connected to the fuel distribution manifold.

15. The combustor as in claim 9 , wherein the flow sleeve comprises of two or more semi-annular flow sleeve sections joined together to surround the combustion liner.

16. The combustor as in claim 9 , further comprising a compression seal that extends radially between the forward portion of the flow sleeve and the fuel distribution manifold.

17. A gas turbine, comprising:
a. a compressor, a compressor discharge casing disposed downstream from the compressor and a turbine disposed downstream from the compressor discharge casing; and
b. a combustor that extends at least partially through the compressor discharge casing, the combustor having an end cover coupled to the compressor discharge casing, an axially extending fuel nozzle that extends downstream from the end cover, an annular cap assembly disposed downstream from the end cover and that at least partially surrounds the fuel nozzle, and a combustion module that extends downstream from the cap assembly, the combustion module comprising:
i. an annular fuel distribution manifold that circumferentially surrounds at least a portion of the cap assembly, the fuel distribution manifold having a radially extending mounting flange that is coupled to the compressor discharge casing and an axially extending annular support sleeve, the support sleeve having an inner surface, wherein the end cover is axially spaced from the compressor discharge casing via the radially extending mounting flange;
ii. a fuel injection assembly that extends downstream from the fuel distribution manifold, the fuel injection assembly having an annular combustion liner that extends downstream from the cap assembly and terminates at an aft frame, an annular flow sleeve that surrounds the combustion liner, and a plurality of fuel injectors that extend through the flow sleeve and the combustion liner downstream from the cap assembly, the fuel injectors being fluidly connected to the fuel distribution manifold; and
iii. wherein the flow sleeve includes a forward portion positioned concentrically within the support sleeve between the combustion liner and the inner surface of the support sleeve and an aft end that is coupled to the aft frame, the flow sleeve extending continuously between the forward portion of the flow sleeve and the aft frame.

18. The gas turbine as in claim 17 , further comprising a cooling flow passage defined between the combustion liner and the flow sleeve that extends continuously between the aft frame and the forward portion of the flow sleeve.

19. The g

Assignees

• Gen Electric

Inventors

• Dicintio Richard Martin
• Melton Patrick Benedict
• Stoia Lucas John
• Willis Christopher Paul
• Pentecost Ronnie Ray

Classifications

• F23R3/005 Primary

  Combined with pressure or heat exchangers · CPC title

• F23R2900/03045

  Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• F23R2900/03043

  Convection cooled combustion chamber walls with means for guiding the cooling air flow · CPC title

• F23R3/46

  Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings · CPC title