Low Profile Axially Staged Fuel Injector

Patent metadata

Field	Value
Publication number	US-2018340689-A1
Application number	US-201715604780-A
Country	US
Kind code	A1
Filing date	May 25, 2017
Priority date	May 25, 2017
Publication date	Nov 29, 2018
Grant date	—

Abstract

An annularly shaped liner at least partially defines a hot gas path of a combustor. The combustor includes a first combustion zone and a second combustion zone downstream of the first combustion zone. A plurality of fuel injectors in fluid communication with the second combustion zone are integrally formed in the liner and arranged around the liner along the circumferential direction.

First claim

What is claimed is:

1 . A combustor for a turbomachine, the combustor comprising a central axis, the central axis of the combustor defines an axial direction, a radial direction perpendicular to the central axis, and a circumferential direction extending around the central axis, the combustor comprising:
an annularly shaped liner at least partially defining a hot gas path; a flow sleeve circumferentially surrounding at least a portion of the liner, wherein the flow sleeve is spaced from the liner along the radial direction to form a cooling flow annulus therebetween; a first combustion zone at least partially defined by the liner; a second combustion zone at least partially defined by the liner downstream of the first combustion zone; and a plurality of fuel injectors in fluid communication with the second combustion zone, the plurality of fuel injectors integrally formed in the liner and arranged around the liner along the circumferential direction.

2 . The combustor of claim 1 , further comprising a fuel port integrally formed in the liner, the fuel port in fluid communication with the plurality of fuel injectors and extending away from the liner along the radial direction.

3 . The combustor of claim 1 , further comprising a fuel plenum defined within the liner, the fuel plenum upstream of the plurality of fuel injectors and downstream of the fuel port.

4 . The combustor of claim 3 , wherein the fuel plenum extends along the circumferential direction between the plurality of fuel injectors.

5 . The combustor of claim 3 , wherein the fuel plenum extends partially around the liner along the circumferential direction.

6 . The combustor of claim 1 , wherein the plurality of fuel injectors comprises a first plurality of fuel injectors and the combustor further comprises a second plurality of fuel injectors in fluid communication with the second combustion zone, the second plurality of fuel injectors integrally formed in the liner and arranged around the liner along the circumferential direction.

7 . The combustor of claim 6 , wherein the first plurality of fuel injectors are in fluid communication with a first fuel plenum and a first fuel port and the second plurality of fuel injectors are in fluid communication with a second fuel plenum and a second fuel port.

8 . The combustor of claim 1 , wherein the plurality of fuel injectors comprises three fuel injectors equally spaced along a circumferential direction.

9 . The combustor of claim 1 , wherein the plurality of fuel injectors are slot injectors.

10 . A gas turbine, comprising:
a compressor; a turbine downstream from the compressor; and a combustor disposed downstream from the compressor and upstream from the turbine, the combustor comprising a central axis, the central axis of the combustor defines an axial direction, a radial direction perpendicular to the central axis, and a circumferential direction extending around the central axis, the combustor comprising: an annularly shaped liner at least partially defining a hot gas path; a flow sleeve circumferentially surrounding at least a portion of the liner, wherein the flow sleeve is spaced from the liner along the radial direction to form a cooling flow annulus therebetween; a first combustion zone at least partially defined by the liner; a second combustion zone at least partially defined by the liner downstream of the first combustion zone; and a plurality of fuel injectors in fluid communication with the second combustion zone, the plurality of fuel injectors integrally formed in the liner and arranged around the liner along the circumferential direction.

11 . The gas turbine of claim 10 , further comprising a fuel port integrally formed in the liner, the fuel port in fluid communication with the plurality of fuel injectors and extending away from the liner along the radial direction.

12 . The gas turbine of claim 10 , further comprising a fuel plenum defined within the liner, the fuel plenum upstream of the plurality of fuel injectors and downstream of the fuel port.

13 . The gas turbine of claim 12 , wherein the fuel plenum extends along the circumferential direction between the plurality of fuel injectors.

14 . The gas turbine of claim 12 , wherein the fuel plenum extends partially around the liner along the circumferential direction.

15 . The gas turbine of claim 10 , wherein the plurality of fuel injectors comprises a first plurality of fuel injectors and the combustor further comprises a second plurality of fuel injectors in fluid communication with the second combustion zone, the second plurality of fuel injectors integrally formed in the liner and arranged around the liner along the circumferential direction.

16 . The gas turbine of claim 15 , wherein the first plurality of fuel injectors are in fluid communication with a first fuel plenum and a first fuel port and the second plurality of fuel injectors are in fluid communication with a second fuel plenum and a second fuel port.

17 . The gas turbine of claim 10 , wherein the plurality of fuel injectors comprises three fuel injectors equally spaced along a circumferential direction.

18 . The gas turbine of claim 10 , wherein the plurality of fuel injectors are slot injectors.

Assignees

• Gen Electric

Inventors

• Woodlock Kevin
• Keenon John

Classifications

• F23R3/286

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

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/346 Primary

  for staged combustion · CPC title

• F02C7/228

  Dividing fuel between various burners · CPC title