System and method for tuning resonators

Patent metadata

Field	Value
Publication number	US-10088165-B2
Application number	US-201514680995-A
Country	US
Kind code	B2
Filing date	Apr 7, 2015
Priority date	Apr 7, 2015
Publication date	Oct 2, 2018
Grant date	Oct 2, 2018

Abstract

A system includes a combustor having a combustion chamber and a combustor supply passage configured to supply a fluid flow into the combustion chamber. The system also includes a resonator configured to receive at least a portion of the fluid flow. The resonator comprises a frequency adjuster configured to change an attenuation frequency of the resonator.

First claim

The invention claimed is:

1. A system comprising:
a combustor having a combustion chamber and a combustor supply passage configured to supply a fluid flow into the combustion chamber; and
a plurality of resonators configured to receive at least a portion of the fluid flow, wherein each resonator of the plurality of resonators comprise a respective frequency adjuster configured to change an attenuation frequency of the resonator, wherein the plurality of resonators, comprise:
a piston;
a tube defining a resonator chamber, wherein the resonator chamber is configured to receive the piston, and wherein a maximum width of the tube extends to a combustor sidewall;

a plurality of actuators, wherein each piston couples to a respective actuator of the plurality of actuators to adjust a position of the piston in the resonator chamber to vary a size of the resonator chamber;
a plurality of vibration sensors configured to detect vibration; and
a controller communicatively coupled to the actuator and configured to receive signals from the plurality of vibration sensors and in response control one or more of the plurality of the actuators to control one or more of the plurality of resonators to reduce vibration.

2. The system of claim 1 , wherein the combustor comprises a gas turbine combustor.

3. The system of claim 2 , comprising a gas turbine engine having the gas turbine combustor.

4. The system of claim 2 , wherein the combustor supply passage comprises a head end chamber of the gas turbine combustor, a passage between a combustion liner and a flow sleeve, or a combination thereof.

5. The system of claim 1 , wherein the fluid flow comprises an oxidant.

6. The system of claim 1 , wherein the plurality of actuators comprise an electric drive, a pneumatic drive, a hydraulic drive, or a combination thereof.

7. The system of claim 1 , wherein the plurality of resonators are circumferentially spaced around the combustor.

8. A system comprising:
a plurality of resonators configured to receive at least a portion of a fluid flow being supplied to a combustion chamber of a combustor, wherein the plurality of resonators comprise a respective frequency adjuster configured to change an attenuation frequency of each resonator of the plurality of resonators, and wherein one or more of the frequency adjusters comprises a piston disposed in a tube and an actuator configured to adjust a position of the piston in the tube to vary a size of a resonator chamber;
a plurality of vibration sensors configured to detect vibration at least partially caused by combustion in the combustor; and
a controller comprising a memory operatively coupled to a processor configured to store data and instructions, wherein the controller is configured to receive signals from the plurality of vibration sensors and in response transmit instructions to one or more of the frequency adjusters to change the attenuation frequency of one or more of the plurality of resonators to reduce the vibration, and wherein the controller is communicatively coupled to the actuator.

9. The system of claim 8 , comprising a sensor communicatively coupled to the controller, wherein the sensor sends a signal to the controller indicative of an operating parameter of a gas turbine system having the combustor and the plurality of resonators, and the controller is configured to instruct one or more of the frequency adjusters to change the attenuation frequency of one or more of the plurality of resonators based on the operating parameter.

10. A method comprising:
receiving one or more signals from one or more vibration sensors; and
adjusting an attenuation frequency of one or more resonators of a plurality of resonators coupled to a combustor supply passage configured to supply a fluid flow into a combustion chamber of a combustor to reduce vibration at least partially caused by combustion in the combustor, wherein each resonator of the plurality of resonators is configured to receive at least a portion of the fluid flow, and wherein adjusting comprises actuating a piston disposed in a tube of one or more of the plurality of resonators with an actuator communicatively coupled to a controller.

11. The method of claim 10 , wherein adjusting comprises responding to sensor feedback indicative of at least one operating parameter of a gas turbine system having the combustor and the plurality of resonators.

12. The method of claim 10 , wherein the fluid flow comprises an oxidant flow being supplied to the combustion chamber of the combustor.

Assignees

• Gen Electric

Inventors

• Nguyen Quoc Hoai
• Kim Kwanwoo
• EPPERSON Whitney
• Pastecki Patrick Edward
• Mueller Mark Anthony

Classifications

• F23R3/28 Primary

  characterised by the fuel supply (burners F23D) · CPC title

• F23M20/005 Primary

  Noise absorbing means · CPC title

• F23R2900/00013

  Reducing thermo-acoustic vibrations by active means · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F01N1/02

  by using resonance · CPC title