Fuel nozzle for a gas turbine engine and method for fabricating the same

• US 20090199561A1
• Filed: 02/12/2008
• Published: 08/13/2009
• Est. Priority Date: 02/12/2008
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Hessler, William Kirk
• Granted Patent: US 7,908,863 B2
• Time in Patent Office: Days
• US Class Current: 60/734
• CPC Class Codes: F23D 11/24 by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
• CPC Class Codes: F23D 11/38 Nozzles; Cleaning devices therefor
• CPC Class Codes: F23D 2900/11001 Impinging-jet injectors or jet impinging on a surface
• CPC Class Codes: F23D 2900/14004 with radially extending gas distribution spokes
• CPC Class Codes: F23R 3/18 Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
• CPC Class Codes: F23R 3/28 characterised by the fuel supply burners F23D
• 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
• CPC Class Codes: Y10T 29/49432 Nozzle making

Abstract

A method for fabricating a secondary fuel nozzle assembly includes providing a nozzle portion defining a passageway configured to supply fuel. At least one peg is operatively coupled in fuel flow communication with the passageway. The at least one peg extends radially outward from the nozzle portion and defines at least one opening configured to direct a flow of fuel in a substantially upstream direction. A disc is positioned about the nozzle portion upstream of the at least one peg. The disc is positioned in communication with the at least one opening and configured to interfere with the flow of fuel to facilitate fuel atomization.

Claims

1. A method for fabricating a secondary fuel nozzle assembly, said method comprising:

providing a nozzle portion defining a passageway configured to supply fuel;

operatively coupling at least one peg in fuel flow communication with the passageway, the at least one peg extending radially outward from the nozzle portion and defining at least one opening configured to direct a flow of fuel in a substantially upstream direction; and

positioning a disc about the nozzle portion upstream of the at least one peg, the disc positioned in communication with the at least one opening and configured to interfere with the flow of fuel to facilitate fuel atomization.

2. A method in accordance with claim 1 wherein said positioning a disc about the nozzle portion upstream of the at least one peg further comprises coupling a semi-toroidal shaped disc to the nozzle portion.

3. A method in accordance with claim 2 further comprising circumferentially positioning the semi-toroidal shaped disc about the nozzle portion.

4. A method in accordance with claim 2 wherein said positioning a disc about the nozzle portion upstream of the at least one peg further comprises forming a downstream surface of the semi-toroidal shaped disc having an arcuate cross-sectional profile to facilitate redirecting the flow of fuel in a direction of a flow of combustion gases.

5. A method in accordance with claim 1 further comprising coupling a head portion to the nozzle portion, the head portion including a plurality of inlets, wherein each inlet of said plurality of inlets is in flow communication with at least one of a plurality of nozzle passageways.

6. A secondary fuel nozzle assembly comprising:

a nozzle portion;

at least one peg extending radially outward from said nozzle portion, said at least one peg defining at least one opening configured to direct a flow of fuel in a substantially upstream direction; and

a disc positioned about said nozzle portion upstream of said at least one peg, said disc positioned in flow communication with the said at least one opening and configured to interfere with the flow of fuel to facilitate fuel atomization.

7. A secondary fuel nozzle assembly in accordance with claim 6 wherein said disc further comprises a semi-toroidal shaped disc.

8. A secondary fuel nozzle assembly in accordance with claim 7 wherein said semi-toroidal shaped disc is circumferentially positioned about said nozzle portion.

9. A secondary fuel nozzle assembly in accordance with claim 8 wherein said semi-toroidal shaped disc is segmented.

10. A secondary fuel nozzle assembly in accordance with claim 7 wherein a downstream surface of said semi-toroidal shaped disc has an arcuate cross-sectional profile to facilitate redirecting the flow of fuel in a direction of a flow of combustion gases.

11. A secondary fuel nozzle assembly in accordance with claim 6 wherein said disc is circumferentially positioned about said nozzle portion, said disc having a substantially planar downstream surface configured to interfere with the flow of fuel to facilitate fuel atomization.

12. A secondary fuel nozzle assembly in accordance with claim 11 wherein said substantially planar downstream surface is positioned at one of a perpendicular angle and an oblique angle with respect to the flow of fuel from said at least one peg.

13. A secondary fuel nozzle assembly in accordance with claim 6 further comprising a head portion coupled to said nozzle portion, said head portion comprising a plurality of inlets, wherein each inlet of said plurality of inlets is in flow communication with at least one nozzle passageway of a plurality of nozzle passageways.

14. A combustor assembly for use with a gas turbine engine, said combustor assembly comprising:

a combustor liner defining a primary combustion zone and a secondary combustion zone, said combustor liner configured to direct a flow of combustion gases substantially in a downstream direction;

a primary fuel nozzle assembly extending into said primary combustion zone; and

a secondary fuel nozzle assembly extending through said primary combustion zone and into said secondary combustion zone, said secondary fuel nozzle assembly comprising;

a nozzle portion;

at least one peg extending radially outward from said nozzle portion, said at least one peg defining at least one opening configured to direct a flow of fuel in an upstream direction opposing the downstream direction; and

a disc positioned about said nozzle portion upstream of said at least one peg, said disc configured to interfere with the flow of fuel to facilitate fuel atomization.

15. A combustor assembly in accordance with claim 14 wherein said disc comprises a semi-toroidal shaped disc.

16. A combustor assembly in accordance with claim 15 wherein a downstream surface of said semi-toroidal shaped disc has an arcuate cross-sectional profile to facilitate redirecting the flow of fuel in the direction of the flow of combustion gases.

17. A combustor assembly in accordance with claim 14 wherein said secondary fuel nozzle assembly further comprises a head portion coupled to said nozzle portion, said head portion comprising a plurality of inlets, wherein each inlet of said plurality inlets is in flow communication with at least one nozzle passageway of said plurality of nozzle passageways.

18. A combustor assembly in accordance with claim 14 wherein said nozzle portion further comprises a central passageway and a plurality of passageways that are each concentrically-aligned with said central passageway.

19. A combustor assembly in accordance with claim 18 wherein said secondary fuel nozzle assembly nozzle portion is configured to inject a selected amount of pilot fuel through a first passageway of said plurality of passageways and inject a selected amount of main fuel through a second passageway of said plurality of passageways, wherein each passageway of said plurality of passageways is configured to be controlled independently.