System for reducing combustion dynamics and NOx in a combustor

Patent metadata

Field	Value
Publication number	US-9353950-B2
Application number	US-201213709320-A
Country	US
Kind code	B2
Filing date	Dec 10, 2012
Priority date	Dec 10, 2012
Publication date	May 31, 2016
Grant date	May 31, 2016

Abstract

A combustor includes an end cap that extends radially across at least a portion of the combustor. The end cap includes an upstream surface axially separated from a downstream surface. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap. Each tube in a first set of the plurality of tubes has an inlet proximate to the upstream surface and an outlet downstream from the downstream surface. Each outlet has a first portion that extends a different axial distance from the inlet than a second portion.

First claim

What is claimed is:

1. A combustor comprising:
an outer casing;
an end cap assembly disposed within the outer casing, the end cap assembly having an upstream surface defined by an upstream plate, a downstream surface defined by a downstream plate axially spaced from the upstream plate and a shroud that extends axially between the upstream plate and the downstream plate, the upstream plate, the downstream plate and the shroud at least partially defining a fuel plenum within the end cap assembly;
wherein the end cap assembly further comprises a plurality of tubes, each tube extending from the upstream plate, through the fuel plenum and through the downstream plate, each tube having a fuel port in fluid communication with the fuel plenum and an inlet defined along the upstream surface;
wherein the plurality of tubes comprises a first tube and a second tube, the first tube having an outlet defined at a downstream end of the first tube and the second tube having an outlet defined at a downstream end of the second tube, wherein the downstream end of the first tube is axially offset from the downstream end of the second tube with respect to an axial centerline of the end cap assembly; and
wherein the first tube converges radially inwardly between the downstream surface and the downstream end of the first tube, wherein the downstream end of the second tube has a first portion and a second portion, wherein the second portion converges radially inwardly between the downstream surface and the downstream end of the second tube along an axial centerline of the second tube while the first portion extends axially along the centerline of the second tube.

2. The combustor as in claim 1 , further comprising a third tube having an outlet defined at a downstream end of the third tube, wherein the downstream end of the third tube terminates at the downstream surface so that the outlet of the third tube coincides with the downstream surface and the downstream end of the second tube terminates at a point that is axially offset from the downstream surface.

3. The combustor as in claim 1 , wherein the downstream end of the first tube and the downstream end of the second tube are axially offset from the downstream surface.

4. The combustor as in claim 1 , further comprising a third tube having an axial centerline parallel to the axial centerline of the end cap assembly, a downstream end of the third tube having an outlet sloped at an acute angle to the axial centerline of the third tube.

5. The combustor as in claim 1 , further comprising a third tube, wherein a downstream end of a third tube has a first portion and a second portion, wherein the first portion is axially offset from the second portion to form a stepped outlet of the third tube.

6. The combustor as in claim 1 , further comprising a third tube and a fourth tube, the third tube having an outlet defined at a downstream end of the third tube, wherein the downstream end of the third tube terminates at the downstream surface so that the outlet of the third tube coincides with the downstream surface and a downstream end of the fourth tube has a first portion and a second portion, wherein the first portion is axially offset from the second portion to form a stepped outlet of the fourth tube.

7. The combustor as in claim 1 , further comprising a third tube, wherein the third tube converges radially inwardly between the downstream surface and a downstream end of the third tube.

8. The combustor as in claim 1 , wherein the plurality of tubes includes a first set of tubes annularly arranged around the axial centerline of the end cap assembly and a second set of tubes annularly arranged around the first set of tubes, wherein the first set of tubes includes the first tube and the second set of tubes includes the second tube.

9. A gas turbine, comprising:
a compressor;
a combustor having a combustion chamber downstream from the compressor;
a turbine downstream from the combustor;
an end cap assembly disposed within the combustor upstream from the combustion chamber, the end cap assembly having an upstream surface defined by an upstream plate, a downstream surface defined by a downstream plate and a shroud that extends axially between the upstream plate and the downstream plate, the upstream plate, the downstream plate and the shroud at least partially defining a fuel plenum within the end cap assembly;
wherein the end cap assembly further comprises a first plurality of tubes annularly arranged about an axial centerline of the end cap assembly, each tube of the first plurality of tubes extending from the upstream plate, through the fuel plenum and through the downstream plate, each tube having a fuel port in fluid communication with the fuel plenum, an inlet defined proximate to the upstream surface and an outlet defined at a downstream end of each tube;
wherein the end cap assembly further comprises a second plurality of tubes annularly arranged about the first plurality of tubes, each tube of the second plurality of tubes extending from the upstream plate, through the fuel plenum and through the downstream plate, each tube of the second plurality of tubes having a fuel port in fluid communication with the fuel plenum, an inlet defined proximate to the upstream surface and an outlet defined at a downstream end of each tube of the second plurality of tubes;
wherein the downstream end of one or more tubes of the first plurality of tubes is axially offset from the downstream end of one or more tubes of the second plurality of tubes with respect to the axial centerline of the end cap assembly; and
wherein at least one tube of the first plurality of tubes converges radially inwardly between the downstream surface and the downstream end of the at least one tube of the first plurality of tubes, wherein the downstream end of at least one tube of the second plurality of tubes has a first portion and a second portion, wherein the second portion converges radially inwardly between the downstream surface and the downstream end of the at least one tube of the second plurality of tubes along an axial centerline of the at least one tube of the second plurality of tubes while the first portion extends axially along the axial centerline of the at least one tube of the second plurality of tubes.

10. The gas turbine as in claim 9 , further comprising a third tube having an outlet defined at a downstream end of the third tube, wherein the downstream end of the third tube terminates at the downstream surface and the downstream end of one or more tubes of the first plurality of tubes terminates at a point that is axially offset from the downstream surface.

11. The gas turbine as in claim 9 , wherein the downstream end of one or more of the tubes of the first plurality of tubes and the downstream end of one or more tubes of the second plurality of tubes are axially offset from the downstream surface.

12. The gas turbine as in claim 9 , wherein a downstream end of at least one tube but not all tubes of the first plurality tubes has a first portion and a second portion, wherein, the first portion is axially offset from the second portion, and wherein a downstream end of at least one tube but not all tubes of the second plurality tubes has a first portion and a second portion, wherein the first portion at least one tube of the second plurality tubes is axially offset from the second portion at least one tube of the second plurality tubes.

13. The gas turbine as in claim 9 , wherein a downstream end of at least one tube but not all tubes of the first plurality of tubes has a first portion and a second portion, wherein the first portion is axially offset from the

Assignees

• Gen Electric

Inventors

• Uhm Jong Ho
• Ziminsky Willy Steve
• Johnson Thomas Edward
• Hughes Michael John
• York William David

Classifications

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R2900/00014

  Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators · CPC title

• F23D14/62

  Mixing devices; Mixing tubes · CPC title

• F23D14/58

  characterised by the shape or arrangement of the outlet or outlets from the nozzle, e.g. of annular configuration · CPC title

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title