Multi-point centerbody injector mini mixing fuel nozzle assembly

Patent metadata

Field	Value
Publication number	US-10352569-B2
Application number	US-201615343672-A
Country	US
Kind code	B2
Filing date	Nov 4, 2016
Priority date	Nov 4, 2016
Publication date	Jul 16, 2019
Grant date	Jul 16, 2019

Abstract

The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall defining a fluid chamber, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector, and a fluid cavity wall. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward the downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve further defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve, and a plurality of radially oriented second air inlet ports in circumferential arrangement at a second axial portion of the outer sleeve. The fluid cavity wall is disposed axially between the first air inlet port and the second air inlet port and extends radially from the outer sleeve toward the centerbody. The fluid cavity wall defines a fluid cavity and a second fluid injection port in fluid communication with the fluid cavity. The second fluid injection port is in fluid communication with the premix passage.

First claim

What is claimed is:

1. A fuel injector for a gas turbine engine, the fuel injector comprising:
an end wall defining a fluid chamber;
a centerbody comprising an axially extended outer wall and inner wall, wherein the outer wall and inner wall extend from the end wall toward a downstream end of the fuel injector, and wherein the outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector, the fluid conduit in fluid communication with the fluid chamber, and wherein the outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit;
an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, wherein the outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage, and wherein the outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve, and wherein the outer sleeve defines a plurality of radially oriented second air inlet ports in circumferential arrangement at a second axial portion of the outer sleeve; and
a fluid cavity wall, wherein the fluid cavity wall is disposed axially between the first air inlet port and the second air inlet port and extends radially from the outer sleeve toward the centerbody, and wherein the fluid cavity wall defines a fluid cavity and a second fluid injection port in fluid communication with the fluid cavity, and wherein the second fluid injection port is in fluid communication with the premix passage.

2. The fuel injector of claim 1 , wherein the second fluid injection port is axially oriented co-linearly with a longitudinal centerline of the fuel injector, and wherein the second fluid injection port is disposed between the outer sleeve and the centerbody.

3. The fuel injector of claim 1 , wherein the end wall further defines a fluid plenum extended at least partially circumferentially through the end wall, and wherein the outer sleeve further defines a plurality of first air inlet port walls extending radially through the outer sleeve and axially from the end wall.

4. The fuel injector of claim 3 , wherein the plurality of first air inlet port walls define a swirl angle relative to a vertical reference line extending radially from a longitudinal centerline of the fuel injector, and wherein the swirl angle is 35 degrees to 65 degrees or −35 degrees to −65 degrees.

5. The fuel injector of claim 3 , wherein the fluid cavity defined by the fluid cavity wall is further defined by at least one first air inlet port wall of the plurality of first air inlet port walls, and wherein the fluid cavity extends from the fluid cavity wall through the at least one first air inlet port wall to provide fluid communication with the fluid plenum.

6. The fuel injector of claim 5 , wherein the fluid cavity extends at least partially circumferentially within the fluid cavity wall and axially from the fluid cavity wall to the end wall.

7. The fuel injector of claim 1 , wherein the outer sleeve further defines a plurality of second air inlet port walls, and wherein the plurality of second air inlet port walls define a swirl angle relative to a vertical reference line extending radially from a longitudinal centerline of the fuel injector, and wherein the swirl angle is 35 degrees to 65 degrees or −35 degrees to −65 degrees.

8. The fuel injector of claim 1 , the fuel injector further comprising:
a shroud disposed at the downstream end of the centerbody, wherein the shroud extends axially from the downstream end of the outer wall of the centerbody, and wherein the shroud is annular around the downstream end of the outer wall.

9. The fuel injector of claim 8 , wherein the shroud further includes a shroud wall radially inward of the outer wall, wherein the shroud wall protrudes upstream into the centerbody.

10. The fuel injector of claim 1 , wherein a mixing length is defined within the premix passage from the fluid injection port to the outlet of the premix passage, and wherein the centerbody further defines a centerbody surface radially outward of the outer wall and along the premix passage, and wherein the outer sleeve further defines an outer sleeve surface radially inward of the outer sleeve and along the premix passage, and wherein the centerbody surface and the outer sleeve surface define an annular hydraulic diameter.

11. The fuel injector of claim 10 , wherein a ratio of the mixing length over the annular hydraulic diameter is 3.5 or less.

12. The fuel injector of claim 10 , wherein the annular hydraulic diameter is 7.65 millimeters or less.

13. The fuel injector of claim 10 , wherein at least a portion of the outer sleeve surface along the mixing length extends radially outward of a longitudinal centerline of the fuel injector.

14. The fuel injector of claim 10 , wherein the centerbody surface and the outer sleeve surface define a parallel relationship such that the annular hydraulic diameter remains constant through the mixing length of the premix passage.

15. The fuel injector of claim 1 , wherein the centerbody further defines a first outlet port and a second outlet port of the radially oriented fluid injection port, wherein the first outlet port is radially inward of the second outlet port, and wherein the first outlet port is adjacent to the fluid conduit and the second outlet port is adjacent to the premix passage.

16. The fuel injector of claim 15 , wherein the first outlet port is radially eccentric relative to the second outlet port.

17. The fuel injector of claim 15 , wherein the first outlet port is axially eccentric relative to the second outlet port.

18. A fuel nozzle for a gas turbine engine, the fuel nozzle comprising:
an end wall defining a fluid chamber and a fluid plenum, wherein the fluid plenum extends at least partially circumferentially through the end wall;
a plurality of fuel injectors in axially and radially adjacent arrangement, wherein each fuel injector comprises:
a centerbody comprising an axially extended outer wall and inner wall, wherein the outer wall and inner wall extend from the end wall toward a downstream end of the fuel injector, and wherein the outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector, the fluid conduit in fluid communication with the fluid chamber, and wherein the centerbody defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit;
an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, wherein the outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage, and wherein the outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve, and wherein the outer sleeve defines a plurality of radially oriented second air inlet ports in circumferential arrangement at a second axial portion of the outer sleeve; and
a fluid cavity wall, wherein the fluid cavity wall is disposed axially between the first air inlet port and the second air inlet port and exte

Assignees

• Gen Electric

Inventors

• Boardman Gregory Allen
• Naik Pradeep
• Giridharan Manampathy Gangadharan
• Lind David Albin
• Martini Jeffrey Michael

Classifications

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title

• F23R3/28

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

• F23R3/286 Primary

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

• F23R3/04

  Air inlet arrangements · CPC title

• F23R3/12

  inducing a vortex · CPC title