Systems and methods for control of combustion dynamics in combustion system

Patent metadata

Field	Value
Publication number	US-2016305337-A1
Application number	US-201514687866-A
Country	US
Kind code	A1
Filing date	Apr 15, 2015
Priority date	Apr 15, 2015
Publication date	Oct 20, 2016
Grant date	—

Abstract

The present disclosure generally relates to a system with a gas turbine engine. The gas turbine engine includes a first combustor having a first fuel injector and a second combustor having a second fuel injector. The gas turbine engine further includes a first fuel conduit extending from a first orifice to a first fuel outlet of the first fuel injector. The first fuel conduit has a first acoustic volume between the first orifice and the first fuel outlet. The gas turbine engine further includes a second fuel conduit extending from a second orifice to a second fuel outlet of the second fuel injector. The second fuel conduit has a second acoustic volume between the second orifice and the second fuel outlet, and the first acoustic volume and the second acoustic volume are different from one another.

First claim

1 . A system, comprising:
a gas turbine engine, comprising:
a first combustor comprising a first fuel injector;
a second combustor comprising a second fuel injector;
a first fuel conduit extending from a first orifice to a first fuel outlet of the first fuel injector, wherein the first fuel conduit has a first acoustic volume between the first orifice and the first fuel outlet; and
a second fuel conduit extending from a second orifice to a second fuel outlet of the second fuel injector, wherein the second fuel conduit has a second acoustic volume between the second orifice and the second fuel outlet, wherein the first acoustic volume and the second acoustic volume are different from one another.

2 . The system of claim 1 , wherein the first combustor comprises a first fuel nozzle upstream from the first fuel injector, and the second combustor comprises a second fuel nozzle upstream from the second fuel injector.

3 . The system of claim 1 , wherein one or more geometric differences between a first geometry of the first orifice and a second geometry of the second orifice comprises a length, a width, or a height of the first orifice or the second orifice.

4 . The system of claim 1 , wherein the first orifice comprises a first orifice and the second orifice comprises a second orifice, wherein one or more geometric differences between the first orifice and the second orifice reduce coherence between the first combustor and the second combustor or alter the phase between the first combustor and the second combustor.

5 . The system of claim 4 , wherein the one or more geometric differences between the first orifice and the second orifice comprises a shape, a thickness, a dimension, a hole shape, a hole size, a hole number, or an arrangement of a plurality of holes.

6 . The system of claim 1 , wherein the first fuel conduit comprises a first conduit geometry and the second fuel conduit comprises second conduit geometry, and wherein one or more geometric differences between the first conduit geometry and the second conduit geometry alter the phase and/or reduce coherence between the first combustor and the second combustor.

7 . The system of claim 6 , wherein the one or more geometric differences between the first conduit geometry and the second conduit geometry comprise a length, a width, a diameter, an acoustic volume, an inner surface, a shape, or any combination thereof.

8 . A system, comprising:
a first combustor of a gas turbine system, comprising:
a first fuel injector comprising a first fuel outlet;
a second fuel injector comprising a second fuel outlet;
a first fuel conduit extending from a first orifice to the first fuel outlet of the first fuel injector, wherein the first fuel conduit has a first conduit geometry between the first orifice and the first fuel outlet, and wherein the first orifice has a first orifice geometry; and
a second fuel conduit extending from a second orifice to the second fuel outlet of the second fuel injector, wherein the second fuel conduit has a second conduit geometry between the second orifice and the second fuel outlet, wherein the second orifice has a second orifice geometry, wherein the first conduit geometry and the second conduit geometry are different from one another, or the first orifice geometry and the second orifice geometry are different from one another, or a combination thereof.

9 . The system of claim 8 , wherein one or more geometric differences between the first orifice geometry of the first orifice and the second orifice geometry of the second orifice comprise differences in a shape, a thickness, a hole shape, a hole size, a hole number, or an arrangement of a plurality of holes.

10 . The system of claim 8 , wherein one or more differences between the first orifice geometry of the first orifice and the second orifice geometry of the second orifice help vary a heat release between the first fuel injector and the second fuel injector.

11 . The system of claim 8 , wherein the first fuel outlet comprises a first fuel outlet with a third orifice geometry and the second fuel outlet comprises a second fuel outlet with a fourth orifice geometry, wherein the third orifice geometry is different from the fourth orifice geometry.

12 . The system of claim 8 , wherein the first conduit geometry between the first orifice and the first fuel outlet corresponds to a first acoustic volume between the first orifice and the first fuel outlet, and wherein the second conduit geometry between the second orifice and the second fuel outlet corresponds to a second acoustic volume between the second orifice and the second fuel outlet, and wherein the second acoustic volume is different from the first acoustic volume.

13 . The system of claim 12 , wherein one or more differences between the first acoustic volume and the second acoustic volume help to reduce combustion dynamics amplitudes between the first fuel injector and the second fuel injector of the first combustor.

14 . The system of claim 8 , wherein the system comprises two or more combustors each equipped with one or more fuel supply systems, and wherein each combustor comprises a first fuel supply system with one or more geometric differences relative to a second fuel supply system of another combustor.

15 . A system, comprising:
a first fuel conduit extending from a first orifice to a first fuel outlet of a first fuel injector of a gas turbine engine, wherein the first fuel conduit has a first conduit geometry between the first orifice and the first fuel outlet, and the first orifice has a first orifice geometry; and a second fuel conduit extending from a second orifice to a second fuel outlet of a second fuel injector of the gas turbine engine, wherein the second fuel conduit has a second conduit geometry between the second orifice and the second fuel outlet, wherein the second orifice has a second orifice geometry different from the first orifice geometry, or the second conduit geometry is different from the first conduit geometry.

16 . The system of claim 15 , wherein the first conduit geometry is different from the second conduit geometry.

17 . The system of claim 16 , wherein one or more differences between the first conduit geometry and the second conduit geometry comprise a length, a width, a diameter, an inner surface, a shape, or any combination thereof.

18 . The system of claim 15 , wherein the first and second orifice geometries are different from one another.

19 . The system of claim 15 , wherein one or more differences between the first and second conduit geometries and/or the first and second orifice geometries help to reduce combustion dynamics amplitudes between the first fuel injector and the second fuel injector.

20 . The system of claim 15 , wherein the first fuel injector is coupled to a first combustor and the second fuel injector is coupled to a second combustor.

Assignees

• Gen Electric

Inventors

• Crothers Sarah Lori
• Karim Hasan
• Hall Joel Meador

Classifications

• F05D2260/964

  counteracting thermoacoustic noise · CPC title

• F23R2900/00014

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

• F23R3/20

  incorporating fuel injection means · CPC title

• F23R3/36 Primary

  Supply of different fuels · CPC title

• F23N5/247

  using mechanical means · CPC title