System and method for control of combustion dynamics in combustion system

Patent metadata

Field	Value
Publication number	US-9709279-B2
Application number	US-201414192687-A
Country	US
Kind code	B2
Filing date	Feb 27, 2014
Priority date	Feb 27, 2014
Publication date	Jul 18, 2017
Grant date	Jul 18, 2017

Abstract

A system includes a gas turbine engine that includes a first combustor and a second combustor. The first combustor includes a first oxidant flow path and a first perforated structure comprising a first plurality of oxidant ports, wherein the first perforated structure is disposed in the first oxidant flow path. The second combustor includes a second oxidant flow path and a second perforated structure comprising a second plurality of oxidant ports. The second perforated structure is disposed in the second oxidant flow path and the first perforated structure has at least one difference relative to the second perforated structure.

First claim

The invention claimed is:

1. A system, comprising:
a gas turbine engine comprising:
a first combustor comprising:
a first wall circumscribing a first combustion chamber;
a second wall disposed at least partially about the first wall;
a first head end chamber including at least one first fuel nozzle configured to supply an oxidant and a fuel to the first combustion chamber;
a first outer wall disposed at least partially about the first inner wall;
a first oxidant flow path extending between the first wall and the second wall and continuing into the first head end chamber; and
a first perforated structure comprising a first plurality of oxidant ports, the first perforated structure being disposed along the first oxidant flow path upstream of the at least one first fuel nozzle; and

a second combustor comprising:
a third wall circumscribing a second combustion chamber;
a fourth wall disposed at least partially about the third wall;
a second head end chamber including at least one second fuel nozzle configured to supply the oxidant and the fuel to the second combustion chamber;
a second oxidant flow path extending between the third wall and the fourth wall and continuing into the second head end chamber; and
a second perforated structure comprising a second plurality of oxidant ports, the second perforated structure being disposed along the second oxidant flow path upstream of the at least one second fuel nozzle; and
wherein the first perforated structure has at least one difference relative to the second perforated structure.

2. The system of claim 1 , wherein the at least one difference is configured to help reduce modal coupling of combustion dynamics between the first combustor and the second combustor.

3. The system of claim 1 , wherein the first perforated structure comprises a first perforated structure disposed at least one of between the second wall comprising a first flow sleeve of the first combustor and the first wall comprising a first combustion liner of the first combustor, between the second wall comprising a first impingement sleeve of the first combustor and the first wall comprising a first transition piece of the first combustor, or in the first head end chamber of the first combustor, or any combination thereof; and
wherein the second perforated structure comprises a second perforated structure disposed at least one of between the fourth wall comprising a second flow sleeve of the second combustor and the third wall comprising a second combustion liner of the second combustor, between the fourth wall comprising a second impingement sleeve of the second combustor and the third wall comprising a second transition piece of the second combustor, or in the second head end chamber of the second combustor, or any combination thereof.

4. The system of claim 1 , wherein the first perforated structure comprises at least part of the second wall comprising at least one of a first flow sleeve of the first combustor, or a first impingement sleeve of the first combustor, or any combination thereof, and the second perforated structure comprises at least part of the fourth wall comprising at least one of a second flow sleeve of the second combustor, or a second impingement sleeve of the second combustor, or any combination thereof.

5. The system of claim 1 , wherein the at least one difference comprises a different number of oxidant ports in the first plurality of oxidant ports relative to the second plurality of oxidant ports.

6. The system of claim 1 , wherein the at least one difference comprises different geometrical arrangements of oxidant ports in the first plurality of oxidant ports relative to the second plurality of oxidant ports.

7. The system of claim 1 , wherein the at least one difference comprises different diameters of oxidant ports in the first plurality of oxidant ports relative to the second plurality of oxidant ports.

8. The system of claim 1 , wherein the at least one difference comprises different distances between adjacent oxidant ports in the first plurality of oxidant ports relative to the second plurality of oxidant ports.

9. The system of claim 1 , wherein the at least one difference comprises different shapes of oxidant ports in the first plurality of oxidant ports relative to the second plurality of oxidant ports.

10. The system of claim 1 , wherein the at least one difference comprises different total oxidant effective flow areas of the first perforated structure relative to the second perforated structure.

11. The system of claim 1 , wherein the first perforated structure is configured to at least partially alter first combustion dynamics in the first combustor, the second perforated structure is configured to at least partially alter second combustion dynamics in the second combustor, and the at least one geometrical difference between the first and second perforated structures causes differences between the first and second combustion dynamics.

12. The system of claim 1 , wherein the first perforated structure is disposed in the first head end chamber of the first combustor, and the second wall defines a third perforated structure having a third plurality of oxidant ports; and
wherein the second perforated structure is disposed in the second head end chamber of the second combustor, and the fourth wall defines a fourth perforated structure having a fourth plurality of oxidant ports, the third perforated structure having at least one difference from the fourth perforated structure.

13. A method, comprising:
controlling first combustion dynamics in a first combustor with a first perforated structure comprising a first plurality of oxidant ports, wherein the first perforated structure is disposed along a first oxidant flow path extending between a first inner wall and a first outer wall of the first combustor, wherein the first inner wall is disposed about a first a first combustion chamber, the first outer wall is disposed at least partially about the first inner wall, and the first oxidant flow path extends into a first head end of the first combustor; and
controlling second combustion dynamics in a second combustor with a second perforated structure comprising a second plurality of oxidant ports, wherein the second perforated structure is disposed along a second oxidant flow path of the second combustor extending between a second inner wall and a second outer wall of the second combustor, wherein the second inner wall is disposed about a second combustion chamber, the second outer wall is disposed at least partially about the second inner wall, and the second oxidant flow path extends into a second head end of the second combustor; and
wherein the first and second perforated structures have at least one difference to vary the second combustion dynamics relative to the first combustion dynamics, wherein the first perforated structure is upstream of a first fuel nozzle disposed in a first head end of the first combustor and the second perforated structure is upstream of a second fuel nozzle disposed in a second head end chamber.

14. The method of claim 13 , comprising reducing modal coupling between the first and second combustors via the at least one difference between the first and second perforated structures.

15. The method of claim 13 , wherein the at least one difference between the first and second perforated structures comprises differences in at least one of a number of oxidant ports, a diameter of oxidant ports, a shape of oxidant ports, a distance between adjacent oxidant ports, a total oxidant effective flow areas, a geometric arrangement, or geometric characte

Assignees

• Gen Electric

Inventors

• Crothers Sarah Lori
• Stoia Lucas John
• Carnell Jr William Francis

Classifications

• F23R2900/00014

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

• F23R3/46

  Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings · CPC title

• F23R3/04 Primary

  Air inlet arrangements · CPC title

• F23R3/42 Primary

  characterised by the arrangement or form of the flame tubes or combustion chambers · CPC title

• F23R3/26

  Controlling the air flow · CPC title