Damper for gas turbine

Patent metadata

Field	Value
Publication number	US-10228134-B2
Application number	US-201514742839-A
Country	US
Kind code	B2
Filing date	Jun 18, 2015
Priority date	Jun 30, 2014
Publication date	Mar 12, 2019
Grant date	Mar 12, 2019

Abstract

The present invention generally relates to a gas turbine and more in particular it is related to a damper assembly for a combustion chamber of a gas turbine. According to preferred embodiments, the present solution provides a damper assembly including protrusions on a wall of the neck. These protrusions result in a side wall reactance to the acoustic field that has the effect of decreasing the effective speed of sound in the neck. The decrease of the effective speed of sound in the neck is equivalent to an increase of the effective neck length.

First claim

The invention claimed is:

1. A damper assembly for a gas turbine, the damper assembly comprising:
a resonator cavity and a neck in flow communication with said resonator cavity, said damper assembly including a plurality of protrusions located on a wall of said neck to contact a flow of a fluid from a combustion chamber to define a side wall reactance to an acoustic field to decrease an effective speed of sound in the neck as the fluid flows through the neck to the resonator cavity;
wherein the neck is mounted to a wall of the combustion chamber and is in flow communication with the combustion chamber such that the neck is between the combustion chamber and the resonator cavity so that the flow of the fluid passes from the combustion chamber and into the resonator cavity via the neck; and
wherein the plurality of protrusions define a corrugated flow channel for the flow of the fluid as the flow of the fluid passes through the neck to the resonator cavity, the corrugated flow channel being configured to permit relative movement between the resonator cavity and the combustion chamber and accommodate movement of the combustion chamber due to thermal gradients acting in the combustion chamber without negatively impacting a structural integrity of the damper assembly.

2. The damper assembly according to claim 1 , wherein said plurality of protrusions are annular-shaped and arranged about a circumference of said neck.

3. The damper assembly according to claim 1 , wherein said plurality of protrusions are equally distanced along said neck.

4. The damper assembly according to claim 1 , wherein said plurality of protrusions each have a rectangular cross-section.

5. The damper assembly according to claim 1 , wherein said plurality of protrusions each have a curved cross-section.

6. The damper assembly according to claim 1 , wherein said resonator cavity comprises two volumes in flow communication with each other.

7. The damper assembly according to claim 6 , wherein the neck is a first neck and there is a second intermediate neck extending between the two volumes to fluidly connect the two volumes of the resonator cavity, the second intermediate neck configured to decrease an effective speed of sound in the second intermediate neck as fluid flows through the second intermediate neck.

8. The damper assembly according to claim 1 , wherein said plurality of protrusions are directed outward of the neck.

9. A damper assembly in a gas turbine, the damper assembly comprising:
a first neck in flow communication with a resonator cavity,
a plurality of protrusions located on an inner side wall of said first neck which contact fluid passing through the first neck as the fluid moves through the first neck toward or away from the resonator cavity to define; a side wall reactance to an acoustic field to decrease an effective speed of sound in the first neck as the fluid flows through the first neck;
wherein the first neck is mounted to a wall of a combustion chamber and is in flow communication with the combustion chamber such that the first neck is between the combustion chamber and the resonator cavity so that the fluid passes from the combustion chamber and into the resonator cavity via the first neck; and
wherein the plurality of protrusions define a corrugated flow channel in the first neck through which the fluid flows as the fluid passes through the first neck to the resonator cavity, the corrugated flow channel being configured to permit relative motion between the resonator cavity and the combustion chamber and accommodate movement of the combustion chamber due to thermal gradients acting in the combustion chamber without negatively impacting a structural integrity of the damper assembly.

10. The damper assembly of claim 9 , wherein the resonator cavity has a first volume and a second volume that is in fluid communication with the first volume via an intermediate second neck positioned between the first volume and the second volume, the intermediate second neck having a plurality of protrusions that define a corrugated flow path that extends between the first volume of the resonator cavity and the second volume of the resonator cavity, the corrugated flow path of the intermediate second neck being configured to decrease an effective speed of sound in the second intermediate neck as fluid flows through the second intermediate neck.

11. The damper assembly of claim 9 , wherein said resonator cavity has a first volume and a second volume that is in fluid communication with the first volume via an intermediate second neck positioned between the first volume and the second volume, the intermediate second neck having a plurality of protrusions that define a corrugated flow path that extends between the first volume of the resonator cavity and the second volume of the resonator cavity, wherein fluid flows along the corrugated flow path of the intermediate second neck as the fluid passes through the second intermediate neck.

12. The damper assembly of claim 9 , wherein the plurality of protrusions are annular-shaped and equally distanced along the first neck.

13. The damper assembly of claim 9 , wherein the plurality of protrusions have rectangular cross-sections or curved cross-sections.

14. The damper assembly of claim 9 , wherein the plurality of protrusions are equally distanced along the first neck.

15. The damper assembly according to claim 1 , wherein said neck is a first neck and the resonator cavity has a first volume and a second volume that is in fluid communication with the first volume via an intermediate second neck positioned between the first volume and the second volume, the intermediate second neck having a plurality of protrusions that define a corrugated flow path that extends between the first volume of the resonator cavity and the second volume of the resonator cavity, wherein fluid flows along the corrugated flow path of the intermediate second neck as the fluid passes through the second intermediate neck.

Assignees

• Alstom Technology Ltd
• Ansaldo Energia Switzerland AG

Inventors

• Tonon Devis
• Bothien Mirko Ruben

Classifications

• F05D2260/963

  by Helmholtz resonators · CPC title

• F23R3/44

  Combustion chambers comprising a {single} tubular flame tube within a tubular casing (reverse-flow combustion chambers F23R3/54) · CPC title

• F23R2900/00014

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

• F01N1/02

  by using resonance · CPC title

• F23M20/005

  Noise absorbing means · CPC title