Fuel/air mixing system for fuel nozzle

• US 9,297,535 B2
• Filed: 02/25/2013
• Issued: 03/29/2016
• Est. Priority Date: 02/25/2013
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Uhm, Jong Ho, Romig, Bryan Wesley, Chong, Yon Han
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): FORD, RENE D
• Application Number:
  US13/776,620
• Publication Number:
  US 20140238036A1
• Time in Patent Office: 1,128 Days
• US Class Current: 1/1
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 7/222 Fuel flow conduits, e.g. manifolds
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/127 Vortex generators, turbulators, or the like, for mixing by creating turbulence F05D2260/2212
• CPC Class Codes: F23C 2900/07001 Air swirling vanes incorporating fuel injectors
• CPC Class Codes: F23D 2900/14021 Premixing burners with swirling or vortices creating means for fuel or air
• CPC Class Codes: F23R 3/14 by using swirl vanes
• CPC Class Codes: F23R 3/286 having fuel-air premixing devices F23R3/30 takes precedence

Abstract

A fuel nozzle includes an inner wall defining a central passage extending in an axial direction of the fuel nozzle, a hub wall surrounding the inner wall and defining a first annular passage, an outer wall surrounding the hub wall and defining a second annular passage, and a shroud surrounding the outer wall and defining a third annular passage. A swirler may receive air and direct the air into the first annular passage. The swirler includes at least one swirl vane extending from the shroud to the hub wall that has an air passage extending between the shroud and the hub wall. The air passage is coupled to the first annular passage and has a first width adjacent the shroud and a second width adjacent the hub wall. The second width is larger than the first width defining a diverging outlet into the first annular passage.

Claims

1. A system, comprising:

a fuel nozzle, comprising;

an inner wall defining a central passage extending in an axial direction of the fuel nozzle;

a hub wall surrounding the inner wall and defining a first annular passage;

an outer wall surrounding the hub wall and defining a second annular passage;

a shroud surrounding the outer wall and defining a third annular passage; and

a swirler configured to receive air and to direct the air into the first annular passage, wherein the swirler comprises at least one swirl vane extending from the shroud to the hub wall, wherein the at least one swirl vane comprises an air passage extending between the shroud and the hub wall, and the air passage is coupled to the first annular passage and has a first width adjacent the shroud and a second width adjacent the hub wall, and the second width is larger than the first width defining a diverging outlet into the first annular passage.

2. The system of claim 1, wherein the swirler comprises a plurality of swirl vanes, and wherein each swirl vane of the plurality of swirl vanes comprises a respective air passage having a respective diverging outlet.

3. The system of claim 1, wherein the air passage comprises a first portion between the shroud and a transition point between the hub wall and the outer wall and a second portion between the transition point and the hub wall, and wherein a width of the air passage gradually expands along the second portion of the swirl vane in a radial direction toward the hub wall.

4. The system of claim 3, wherein the width of the air passage is approximately constant along the first portion of the swirl vane.

5. The system of claim 1, comprising a combustor having a plurality of outer fuel nozzles disposed about a central fuel nozzle, wherein the fuel nozzle comprises one of the plurality of outer fuel nozzles.

6. The system of claim 1, wherein the swirler is configured to receive the air in a radial direction crosswise to the first annular passage.

7. The system of claim 1, comprising a combustor having a plurality of outer fuel nozzles disposed about a central fuel nozzle, wherein the fuel nozzle comprises the central fuel nozzle.

8. The system of claim 1, wherein the at least one swirl vane comprises a fuel passage extending between the shroud and the hub wall, the air passage extending between the shroud and the outer wall, and wherein the fuel passage is configured to route the fuel through one or more fuel holes in the at least one swirl van into the third annular passage, and wherein the air passage is configured to route the air through the at least swirl vane axially into the third annular passage to mix with the fuel routed through the one or more fuel holes.

9. The system of claim 1, comprising a plurality of premixing tubes extending in the axial direction and coupled to the first annular passage, wherein the plurality of premixing tubes have one or more fuel holes configured to receive the fuel through the second annular passage, wherein the plurality of premixing tubes is configured to receive a generally uniform distribution of the air, to mix fuel and the air, and to direct a mixture of the fuel and the air to an outlet of the fuel nozzle.

10. The system of claim 9, wherein the first annular passage is configured to receive a flow of the air having a circumferential velocity, and wherein the diverging outlet of the air passage is configured to reduce the circumferential velocity upstream of the plurality of premixing tubes.

11. The system of claim 9, wherein the second annular passage is configured to receive a flow of the fuel, and wherein the fuel is routed through one or more fuel holes in the side wall of each premixing tube.

12. A method of using the system of claim 1, the method comprising:

directing a first portion of air through the third annular passage; and

directing a second portion of air through the air passage of the swirler into the first annular passage.

13. The method of claim 12, comprising directing a fuel through a fuel plenum of the swirler into a third annular passage between the outer wall and the hub wall.

14. The method of claim 13, comprising:

directing the fuel into one or more premixing tubes;

mixing the fuel with the second portion of the air; and

directing a mixture of the fuel and the second portion of the air into a combustion region of a combustor.

15. The method of claim 14, comprising directing the fuel though the third annular passage into the combustion region of the combustor.