PILOT PREMIX NOZZLE AND FUEL NOZZLE ASSEMBLY

• US 20170363293A1
• Filed: 06/21/2016
• Published: 12/21/2017
• Est. Priority Date: 06/21/2016
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Grooms, Neal William, Harper, James, Chong, Yon Han
• Granted Patent: US 10,443,854 B2
• Time in Patent Office: Days
• CPC Class Codes: F02C 7/222 Fuel flow conduits, e.g. manifolds
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F23R 2900/03343 Pilot burners operating in premixed mode
• CPC Class Codes: F23R 3/286 having fuel-air premixing devices F23R3/30 takes precedence
• CPC Class Codes: F23R 3/343 Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00

Abstract

A premix pilot nozzle is disclosed herein. The premix pilot nozzle includes a nozzle body. The nozzle body includes a forward wall, an aft wall, an outer band that extends between the forward wall and the aft wall and a tip portion that extends axially downstream from the aft wall. The nozzle body further defines a fuel inlet plenum that extends coaxially within the nozzle body, a fuel distribution plenum that is defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum, a plurality of premix passages that extend helically around the fuel inlet plenum within the fuel distribution plenum and a plurality of air passages annularly arranged around the plurality of premix passages. One or more premix passages of the plurality of premix passages are in fluid communication with the fuel distribution plenum.

Claims

1. A premix pilot nozzle, comprising:

a nozzle body having a forward wall axially spaced from an aft wall, an outer band that extends between the forward wall and the aft wall, a tip portion extending axially downstream from the aft wall wherein the tip portion terminates at a downstream wall, a fuel inlet plenum that extends coaxially within the nozzle body and that is partially defined by an inner surface of the downstream wall, a fuel distribution plenum defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum, a plurality of premix passages extending helically around the fuel inlet plenum within the fuel distribution plenum; and

a plurality of air passages annularly arranged around the plurality of premix passages, wherein one or more premix passages of the plurality of premix passages is in fluid communication with the fuel distribution plenum.

2. The premix pilot nozzle as in claim 1, wherein each air passage of the plurality of air passages comprises a respective inlet defined along the forward wall and respective outlet defined along the aft wall of the nozzle body.

3. The premix pilot nozzle as in claim 1, wherein each premix passage of the plurality of premix passages comprises a respective inlet defined along the forward wall and a respective outlet defined along the downstream wall of the tip portion of the nozzle body.

4. The premix pilot nozzle as in claim 3, wherein a portion of the downstream wall defined radially inwardly from the respective outlets of the premix passages is dimpled inwardly along an axial centerline of the nozzle body towards the forward wall.

5. The premix pilot nozzle as in claim 1, wherein the nozzle body includes a plurality of pins protruding outwardly from the inner surface of the downstream wall within the fuel inlet plenum.

6. The premix pilot nozzle as in claim 1, wherein a radially outer surface of the tip portion of the nozzle body includes a plurality of grooves that extend between the aft wall and the downstream wall of the nozzle body.

7. The premix pilot nozzle as in claim 1, wherein a radially outer surface of the tip portion of the nozzle body includes a plurality of grooves that extend helically along the outer surface between the aft wall and the downstream wall of the nozzle body.

8. The premix pilot nozzle as in claim 1, wherein the tip portion of the nozzle body is cylindrical.

9. The premix pilot nozzle as in claim 1, wherein each premix passage includes a respective fuel port in fluid communication with the fuel distribution plenum.

10. A fuel nozzle, comprising:

an outer tube having an upstream end axially spaced from a downstream end;

an inner tube extending axially within the outer tube, wherein the inner tube is radially spaced from the outer tube so as to define an annular air passage therebetween; and

a premix pilot nozzle coupled to the downstream end of the outer tube, the premix pilot nozzle comprising;

a nozzle body having a forward wall axially spaced from an aft wall, an outer band coupled to the downstream end of the outer tube, the outer band extending axially between the forward wall and the aft wall, a tip portion extending axially downstream from the aft wall wherein the tip portion includes a downstream wall, a fuel tube defining a fuel inlet plenum that extends coaxially within the nozzle body and that is partially defined by an inner surface of the downstream wall wherein the fuel inlet plenum is in fluid communication with the inner tube, a fuel distribution plenum defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum and a plurality of premix passages extending helically around the fuel inlet plenum within the fuel distribution plenum; and

a plurality of air passages annularly arranged around the plurality of premix passages, wherein each premix passage of the plurality of premix passages is in fluid communication with the fuel distribution plenum.

11. The fuel nozzle as in claim 10, wherein each air passage of the plurality of air passages comprises a respective inlet defined along the forward wall and respective outlet defined along the aft wall of the nozzle body.

12. The fuel nozzle as in claim 10, wherein each premix passage of the plurality of premix passages comprises a respective inlet defined along the forward wall and a respective outlet defined along the downstream wall of the tip portion of the nozzle body.

13. The fuel nozzle as in claim 12, wherein a portion of the downstream wall defined radially inwardly from the respective outlets of the premix passages is dimpled inwardly along an axial centerline of the nozzle body towards the forward wall.

14. The fuel nozzle as in claim 10, wherein the nozzle body includes a plurality of pins protruding outwardly from the inner surface of the downstream wall within the fuel inlet plenum.

15. The fuel nozzle as in claim 10, wherein a radially outer surface of the tip portion of the nozzle body includes a plurality of grooves that extend between the aft wall and the downstream wall of the nozzle body.

16. The fuel nozzle as in claim 10, wherein a radially outer surface of the tip portion of the nozzle body includes a plurality of grooves that extend helically along the outer surface between the aft wall and the downstream wall of the nozzle body.

17. The fuel nozzle as in claim 10, wherein the tip portion of the nozzle body is cylindrical.

18. The fuel nozzle as in claim 10, wherein each premix passage includes a respective fuel port in fluid communication with the fuel distribution plenum.

19. The fuel nozzle as in claim 10, further comprising a plurality of fuel pegs circumferentially spaced about and extending radially outwardly from the outer tube.

20. The fuel nozzle as in claim 10, wherein the fuel nozzle is mounted to an end cover of a combustor of a gas turbine, wherein the combustor includes a plurality of primary fuel nozzles circumferentially spaced around the fuel nozzle.