Systems and methods for a fuel pressure oscillation device for reduction of coherence

Patent metadata

Field	Value
Publication number	US-9551283-B2
Application number	US-201414316616-A
Country	US
Kind code	B2
Filing date	Jun 26, 2014
Priority date	Jun 26, 2014
Publication date	Jan 24, 2017
Grant date	Jan 24, 2017

Abstract

A system with a gas turbine engine is provided. The gas turbine engine includes a first combustor comprising a first fuel nozzle, a second combustor comprising a second fuel nozzle, and a first fuel pressure oscillation system. The first fuel pressure oscillation system includes a first rotary device coupled to a first fuel circuit. The first fuel circuit is disposed along a first fuel passage leading to the first fuel nozzle. The first rotary device is configured to generate a first fuel pressure oscillation through the first fuel nozzle. The gas turbine engine also includes a second fuel pressure oscillation system having a second rotary device coupled to a second fuel circuit. The second fuel circuit is disposed along a second fuel passage leading to the second fuel nozzle, and the second rotary device is configured to generate a second fuel pressure oscillation through the second fuel nozzle.

First claim

The invention claimed is:

1. A system, comprising:
a gas turbine engine, comprising:
a first combustor comprising a first fuel nozzle;
a second combustor comprising a second fuel nozzle;
a first fuel pressure oscillation system having a first rotary device coupled to a first fuel circuit configured to deliver fuel to the first fuel nozzle, wherein the first fuel circuit is disposed along a first fuel passage leading to the first fuel nozzle, and wherein the first rotary device comprises a first spinning disk and at least one orifice disposed within the first spinning disk, and wherein the first rotary device is configured to generate a first fuel pressure oscillation within the first fuel nozzle when the first fuel passes through the at least one orifice of the first spinning disk; and
a second fuel pressure oscillation system having a second rotary device coupled to a second fuel circuit configured to deliver the fuel to the second fuel nozzle, wherein the second fuel circuit is disposed along a second fuel passage leading to the second fuel nozzle, and wherein the second rotary device comprises a second spinning disk and at least one orifice disposed within the second spinning disk, and wherein the second rotary device is configured to generate a second fuel pressure oscillation within the second fuel nozzle when the second fuel passes through the at least one orifice of the second spinning disk wherein at least one of the first and second combustors comprises an endcover and at least one of the first and second fuel nozzles axially extending away from the endcover.

2. The system of claim 1 , wherein the first fuel pressure oscillation is different than the second fuel pressure oscillation, and the difference in fuel pressure oscillation is configured to help reduce modal coupling between the first combustor and the second combustor.

3. The system of claim 1 , wherein the first fuel pressure oscillation is different than the second fuel pressure oscillation, and the difference in fuel pressure oscillation is configured to help alter a phase between the first combustor and the second combustor.

4. The system of claim 1 , wherein a first plurality of orifices are disposed on the first spinning disk of the first rotary device and a second plurality of orifices are disposed on the second spinning disk of the second rotary device.

5. The system of claim 4 , wherein a first geometry of the first plurality of orifices has at least one geometrical difference relative to a second geometry of the second plurality of orifices.

6. The system of claim 5 , wherein the at least one geometrical difference is at least one of a different size, a different shape, a different dimension, a different effective area, or a different spacing, a different pattern, or any combination thereof.

7. The system of claim 1 , wherein the gas turbine engine comprises a controller configured to control a first drive of the first rotary device, or a second drive of the second rotary device, or both, and wherein the first and second drives are configured to rotate the first and second spinning disks of the first and second rotary devices, respectively.

8. The system of claim 7 , wherein the controller is configured to vary a first rotational speed of the first rotary device differently from a second rotational speed of the second rotary device.

9. A system, comprising: a first combustor, comprising: an endcover; a first fuel circuit comprising a first fuel nozzle axially extending away from the endcover; a second fuel circuit comprising a second fuel nozzle axially extending away from the endcover; and a first fuel pressure oscillation system disposed upstream of the first fuel nozzle and the second fuel nozzle, wherein the first fuel pressure oscillation system is configured to generate pressure oscillations within a fuel, and wherein the first fuel pressure oscillation system comprises: a first rotary device disposed along a first fuel passage of the first fuel circuit and leading to the first fuel nozzle; a second rotary device disposed along a second fuel passage of the second fuel circuit and leading to the second fuel nozzle; and a first drive coupled to a first gear, wherein the first gear is configured to provide a rotational force that rotates the first rotary device and the second rotary device.

10. The system of claim 9 , wherein the first rotary device is configured to generate a first fuel pressure oscillation within the first fuel nozzle and the second rotary device is configured to generate a second fuel pressure oscillation within the second fuel nozzle.

11. The system of claim 10 , wherein the first fuel pressure oscillation is different than the second fuel pressure oscillation, and the difference in fuel pressure oscillation is configured to help reduce modal coupling between the first combustor and a second combustor.

12. The system of claim 9 , wherein the first fuel pressure oscillation is different than the second fuel pressure oscillation, and the difference in fuel pressure oscillation is configured to help alter a phase between the first combustor and a second combustor.

13. The system of claim 9 , wherein the first rotary device comprises a first plurality of orifices and the second rotary device comprises a second plurality of orifices, and wherein the first and second plurality of orifices are configured to pulse the fuel as the fuel moves through the first and second fuel passages, respectively.

14. The system of claim 13 , wherein the first plurality of orifices has at least one geometrical difference relative to the second plurality of orifices, and wherein the at least one geometrical difference is configured to generate a first fuel pressure oscillation of the first fuel nozzle that is out of phase from a second fuel pressure oscillation of the second fuel nozzle.

15. The system of claim 14 , wherein the at least one geometrical difference is at least one of a different size, a different shape, a different dimension, a different effective area, or a different pattern, a different spacing, or any combination thereof.

16. The system of claim 9 , wherein the system comprises a controller configured to control the first drive, thereby controlling the rotational speed of the first rotary device and the second rotary device.

17. A method, comprising: generating a first fuel pressure oscillation with a first rotary device of a fuel pressure oscillation system, wherein the first rotary device is disposed along a first fuel passage of a first fuel circuit leading to a first fuel nozzle of a combustor, wherein the first fuel nozzle axially extends away from an endcover of the combustor; and generating a second fuel pressure oscillation with a second rotary device of the fuel pressure oscillation system, wherein the second rotary device is disposed along a second fuel passage of a second fuel circuit leading to a second fuel nozzle of the combustor, wherein the second fuel nozzle axially extends away from the endcover of the combustor, and wherein the fuel pressure oscillation system disposed upstream of the first fuel nozzle and the second fuel nozzle, and wherein the fuel pressure oscillation system comprises a first drive coupled to a first gear, and wherein the first gear is configured to provide a rotational force that rotates the first rotary device and the second rotary device.

18. The method of claim 17 , wherein the first rotary device comprises a first plurality of orifices, wherein the second rotary device comprises a second plurality of orifices, wherein the first plurality o

Assignees

• Gen Electric

Inventors

• Crothers Sarah Lori
• Flanagan James Scott
• Davis Jr Lewis Berkley

Classifications

• F02C7/22 Primary

  Fuel supply systems · CPC title

• F23R2900/00013

  Reducing thermo-acoustic vibrations by active means · CPC title

• F05D2260/964

  counteracting thermoacoustic noise · CPC title