Spiral cooled fuel nozzle

• US 8,272,218 B2
• Filed: 09/24/2008
• Issued: 09/25/2012
• Est. Priority Date: 09/24/2008
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Fox, Timothy, Schilp, Reinhard
• Primary Examiner(s): Gartenberg, Ehud
• Assistant Examiner(s): Goyal, Arun
• Application Number:
  US12/236,667
• Publication Number:
  US 20100071374A1
• Time in Patent Office: 1,462 Days
• Field of Search: 607/40, 607/42, 607/44, 607/47, 239/132, 239/533.2, 239/500, 239/502
• US Class Current: 60/742
• CPC Class Codes: F02C 7/22 Fuel supply systems
• CPC Class Codes: F05D 2250/25 helical
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: F23R 3/28 characterised by the fuel supply burners F23D
• CPC Class Codes: F23R 3/34 Feeding into different combustion zones

Abstract

A fuel nozzle for delivery of fuel to a gas turbine engine. The fuel nozzle includes an outer nozzle wall and a center body located centrally within the nozzle wall. A gap is defined between an inner wall surface of the nozzle wall and an outer body surface of the center body for providing fuel flow in a longitudinal direction from an inlet end to an outlet end of the fuel nozzle. A turbulating feature is defined on at least one of the central body and the inner wall for causing at least a portion of the fuel flow in the gap to flow transverse to the longitudinal direction. The gap is effective to provide a substantially uniform temperature distribution along the nozzle wall in the circumferential direction.

Claims

1. A fuel nozzle for delivery of fuel to a gas turbine engine, the fuel nozzle comprising:

a tubular nozzle member comprising an outer nozzle wall defining a longitudinal axis, the nozzle wall including an inner wall surface and an outer wall surface and having a fuel inlet end and a fuel outlet end;

a center body including an outer body surface, the center body having a longitudinal axis that is substantially collinear with the longitudinal axis of the nozzle wall;

a gap defined between the inner wall surface and the outer body surface and extending circumferentially about the outer body surface for providing fuel flow in a longitudinal direction from an upstream end adjacent the inlet end to a downstream end adjacent the outlet end, wherein at least a portion of the fuel flow in the gap flows in the longitudinal direction substantially parallel to the longitudinal axes of the wall surface and the nozzle wall, and

a turbulating feature on at least one of the inner wall surface and the outer body surface comprising a spiral configuration extending between the upstream end and the downstream end for causing at least a portion of the fuel flow in the gap to flow transverse to the longitudinal direction, the upstream end including a plurality of starts for supplying fuel to a plurality of flow paths defined on the spiral configuration, and the gap being effective to provide a substantially uniform temperature distribution along the nozzle wall in the circumferential direction.

2. The fuel nozzle as in claim 1, wherein the spiral configuration is formed on one of the inner wall surface and the outer body surface, and the other of the inner wall surface and the outer body surface comprises a substantially smooth surface located in spaced relation to the spiral configuration to define the gap.

3. The fuel nozzle as in claim 2, wherein the spiral configuration comprises a spiral thread surface.

4. The fuel nozzle as in claim 2, wherein the spiral configuration comprises a twisted rope configuration formed on the outer body surface.

5. The fuel nozzle as in claim 1, wherein each of the inner wall surface and outer body surface includes the spiral configuration and the spiral configuration comprises a spiral thread surface, the spiral thread surfaces being located in spaced relation to define the gap.

6. The fuel nozzle as in claim 1, wherein the upstream end includes four starts for supplying fuel to four flow paths.

7. The fuel nozzle as in claim 1, wherein the center body prevents fluid flow between the upstream end and the downstream end within an area circumscribed by the outer body surface.

8. The fuel nozzle as in claim 1, wherein the spiral configuration is defined by circumferentially and longitudinally extending crest and trough portions, the radial distance between the top of a crest and the bottom of a trough comprising a distance equal to or greater than the radial distance of the gap from the top of a crest to the inner wall surface.

9. The fuel nozzle as in claim 1, wherein the radial distance of the gap is at least approximately 5% of the radius of the inner wall surface.

10. The fuel nozzle as in claim 1, wherein the gap is effective to provide a substantially uniform heat transfer coefficient along the length of the nozzle.

11. In a gas turbine engine, a gas turbine engine fuel nozzle for delivery of fuel to a gas turbine engine, the fuel nozzle comprising:

a tubular nozzle member extending radially into a combustion zone of the gas turbine engine transverse to a flow of hot combustion products through the combustion zone, the nozzle member comprising an outer nozzle wall defining a longitudinal axis, the nozzle wall including an inner wall surface and an outer wall surface and having a fuel inlet end and a fuel outlet end;

a center body including an outer body surface, the center body having a longitudinal axis that is substantially collinear with the longitudinal axis of the nozzle wall;

a gap defined between the inner wall surface and the outer body surface and extending circumferentially about the outer body surface for providing fuel flow in a longitudinal direction from an upstream end adjacent the inlet end to a downstream end adjacent the outlet end; and

a turbulating feature located adjacent to the gap on at least one of the inner wall surface and the outer body surface comprising a spiral configuration extending between the upstream end and the downstream end for causing at least a portion of the fuel flow along the length of the gap to flow transverse to the longitudinal direction in a portion of the nozzle member located within the combustion zone, the upstream end including a plurality of starts for supplying fuel to a plurality of flow paths defined on the spiral configuration, and the gap being effective to provide a substantially uniform temperature distribution along the nozzle wall in the circumferential direction.

12. The fuel nozzle as in claim 11, wherein the turbulating feature comprises a spiral configuration extending between the upstream end and the downstream end, the spiral configuration effective to cause the fuel flow to circulate circumferentially along substantially the length of the center body.

13. The fuel nozzle as in claim 12, wherein the center body is spaced out of contact with the nozzle wall along substantially the length of the center body.

14. The fuel nozzle as in claim 13, wherein the spiral configuration is defined by circumferentially and longitudinally extending crest and trough portions defining a screw thread surface.

15. The fuel nozzle as in claim 14, wherein the radial distance between the top of a crest and the bottom of a trough comprises a distance equal to or greater than the radial distance of the gap from the top of a crest to the inner wall surface.

16. The fuel nozzle as in claim 15, wherein the radial distance of the gap is at least approximately 5% of the radius of the inner wall surface.

17. The fuel nozzle as in claim 12, wherein the upstream end includes a plurality of starts for supplying fuel to a plurality of flow paths defined on the spiral configuration.