Fuel nozzle for reducing modal coupling of combustion dynamics

1. A fuel nozzle, comprising:

a. a center body that extends axially along an axial centerline for a length;

b. a shroud that circumferentially surrounds the center body for at least a portion of the length of the center body;

c. a plurality of walls that extend radially between the center body and the shroud, wherein the walls extend continuously about a circumference of the center body between an upstream end of the shroud and a downstream end of the center body;

d. a plurality of helical passages at least partially defined by the center body, the shroud, and the plurality of walls, wherein each helical passage circumferentially surrounds the center body along at least a portion of the length of the center body; and

e. a fuel port in each helical passage, wherein each fuel port has a different axial position from remaining fuel ports in remaining helical passage of the plurality of helical passages with respect to an axial centerline of the fuel nozzle.

2. The fuel nozzle as in claim 1 , further comprising a fuel plenum inside the center body.

3. The fuel nozzle as in claim 1 , wherein the shroud extends axially downstream from the plurality of walls.

4. The fuel nozzle as in claim 1 , wherein the shroud defines a diameter, and the diameter decreases downstream from the plurality of walls.

5. The fuel nozzle as in claim 1 , wherein each wall extends axially upstream from the shroud.

6. The fuel nozzle as in claim 1 , wherein each fuel port provides fluid communication through the center body into a different helical passage.

7. The fuel nozzle as in claim 1 , wherein each fuel port comprises a conical outer surface that extends radially into each helical passage.

8. The fuel nozzle as in claim 1 , wherein each fuel port is equidistant from adjacent walls.

9. A fuel nozzle, comprising:

a. a center body that extends axially along an axial centerline for a length;

b. a shroud that circumferentially surrounds the center body for at least a portion of the length of the center body;

c. a plurality of helical passages that circumferentially surround the center body along at least a portion of the length of the center body wherein the helical passages extend continuously about a circumference of the center body between an upstream end of the shroud and a downstream end of the center body; and

d. a fuel port in each helical passage, wherein each fuel port has a different axial position from remaining fuel ports in remaining helical passages of the plurality of helical passages with respect to an axial centerline of the fuel nozzle.

10. The fuel nozzle as in claim 9 , Wherein the shroud extends axially downstream from the plurality of helical passages.

11. The fuel nozzle as in claim 9 , wherein the shroud defines a diameter, and the diameter decreases downstream from the plurality of helical passages.

12. The fuel nozzle as in claim 9 , wherein each helical passage extends axially upstream from the shroud.

13. The fuel nozzle as in claim 9 , wherein each fuel port comprises a conical outer surface that extends radially into each helical passage.

14. A gas turbine, comprising:

a. a compression section;

b. a combustion section downstream from the compression section;

c. a turbine section downstream from the combustion section;

d. a fuel nozzle in the combustion section;

e. a plurality of helical passages that extend axially in the fuel nozzle, wherein the helical passages extend continuously about a circumference of a center body of the fuel nozzle; and

f. a fuel port in each helical passage, wherein each fuel port has a different axial position from remaining fuel ports in remaining helical passages of the plurality of helical passages with respect to an axial centerline of the fuel nozzle.

15. The gas turbine as in claim 14 , further comprising a shroud that circumferentially surrounds the plurality of helical passages, wherein the shroud extends axially downstream from the plurality of helical passages.

16. The gas turbine as in claim 14 , further comprising a shroud that circumferentially surrounds the plurality of helical passages, wherein the shroud defines a diameter, and the diameter decreases downstream from the plurality of helical passages.

17. The gas turbine as in claim 14 , further comprising a shroud that circumferentially surrounds the plurality of helical passages, wherein each helical passage extends axially upstream from the shroud.

18. The gas turbine as in claim 14 , wherein each fuel port comprises a conical outer surface that extends radially into each helical passage.