Combustor resonator section with an internal thermal barrier coating and method of fabricating the same

Patent metadata

Field	Value
Publication number	US-9395082-B2
Application number	US-201213622452-A
Country	US
Kind code	B2
Filing date	Sep 19, 2012
Priority date	Sep 23, 2011
Publication date	Jul 19, 2016
Grant date	Jul 19, 2016

Abstract

A combustor ( 100 ) for a gas turbine engine ( 30 ) has a circumferentially extending liner ( 109 ) defining at least a portion of an interior combustion chamber ( 107 ) and a hot gas path ( 115 ). The liner includes a resonator section ( 112 ) including at least one resonator ( 116 A, 116 B) having a resonator chamber ( 125 A, 125 B) formed on an exterior of the liner. A thermal barrier coating ( 118 ) is disposed along an inner surface of the liner including an inner surface ( 130 ) of the resonator section. The resonator further includes a plurality of apertures ( 117 ) and each aperture extends through the liner and the thermal barrier coating at the resonator section and there is fluid flow communication between the combustion chamber and the resonator chamber.

First claim

The invention claimed is:

1. A method of fabricating and assembling a combustor for a gas turbine engine, the combustor having a resonator section of a combustor liner and a second liner section of the combustor liner that is affixed to an upstream end of the resonator section, the combustor liner defining an interior combustion chamber and a hot gas path and having a plurality of resonators disposed circumferentially on an outer surface of the liner, the method comprising:
forming the resonator section from a generally rectangular metal plate, wherein the resonator section has an inner surface and an outer surface;
applying a thermal barrier coating to the inner surface of the resonator section and a corresponding inner surface of the second liner section;
forming a plurality of resonators on the outer surface of the resonator section, wherein each resonator of the plurality of resonators is formed by:
integrally forming respective one or more outwardly projecting sidewalls on the resonator section by machining the outer surface of the resonator section such that a thickness of the resonator section within a respective area defined by the respective one or more outwardly projecting sidewalls is less than a thickness of the resonator section respectively immediately outside the respective one or more outwardly projecting sidewalls;
forming a respective circumferentially arranged array of apertures through the thermal barrier coating and the resonator section within the respective area defined by the respective one or more outwardly projecting sidewalls, each aperture of the respective circumferentially arranged array of apertures having a neck length such that each aperture extends through the resonator section and the thermal barrier coating;
configuring a respective end cap such that the respective end cap has a height; and
affixing the respective end cap to a respective site on the respective one or more sidewalls surrounding the respective circumferentially arranged array of apertures, the site spaced radially outward from an outer surface of the first liner section; and

wherein a first plurality of resonators of the plurality of resonators have first resonator chambers with each first resonator chamber having a first volume;
wherein a second plurality of resonators of the plurality of resonators have second resonator chambers with each second resonator chamber having a second volume that is greater than the first volume;
wherein the first plurality of resonators have a first set of respective end caps and the second plurality of resonators have a second set of respective end caps; and
wherein the height of each respective end cap of the first set of respective end caps comprises a first height and the height of each respective end cap of the second set of respective end caps comprises a second height which is greater than the first height, thereby causing the second volume to be greater than the first volume.

2. The method of claim 1 , further comprising configuring each respective end cap to have a geometric peripheral shape that matches a corresponding geometric peripheral shape of the respective one or more outwardly projecting sidewalls.

3. The method of claim 2 , further comprising forming a respective plurality of impingement holes in each respective end cap.

4. The method of claim 3 , further comprising affixing a downstream end of the resonator section to a third liner section of the combustor liner.

5. A combustor for a gas turbine engine, comprising:
a circumferentially extending liner defining at least a portion of an interior combustion chamber;
a resonator section of the circumferentially extending liner comprising at least one resonator on the circumferentially extending liner, the at least one resonator including a resonator chamber formed on an outer surface of the circumferentially extending liner; and
a thermal barrier coating disposed along an inner surface of the circumferentially extending liner including an inner surface of the resonator section;
wherein the at least one resonator further comprises one or more outwardly projecting sidewalls surrounding a plurality of apertures and each aperture has a neck length such that each aperture extends through the circumferentially extending liner at the resonator section and through the thermal barrier coating and there being fluid flow communication between the interior combustion chamber and the resonator chamber;
wherein the one or more outwardly projecting sidewalls are integrally formed with the circumferentially extending liner, wherein a thickness of the circumferentially extending liner within the resonator chamber is less than a thickness of the circumferentially extending liner immediately outside of the resonator chamber at the resonator section; and
wherein the at least one resonator further comprises an end cap affixed to a site on the one or more outwardly projecting sidewalls, the site spaced radially outward from the outer surface of the circumferentially extending liner;
wherein the at least one resonator has a first volume that is greater than a second volume of a second resonator located on the circumferentially extending liner, the second resonator comprising respective one or more outwardly projecting sidewalls integrally formed with the circumferentially extending liner; and
wherein the end cap of the at least one resonator comprises a first height and a second end cap of the second resonator comprises a second height which is greater than the first height, thereby causing the first volume to be greater than the second volume, wherein the second end cap is affixed to the respective one or more outwardly projecting sidewalls of the second resonator.

6. The combustor of claim 5 , wherein the one or more outwardly projecting sidewalls are formed on the circumferentially extending liner by reducing a thickness of portions of the circumferentially extending liner.

7. The combustor of claim 6 , wherein the thickness of portions of the circumferentially extending liner is reduced by machining away the portions of the circumferentially extending liner.

8. A combustor for a gas turbine engine, comprising:
a circumferentially extending liner defining at least a portion of an interior combustion chamber and a hot gas path;
a resonator section of the circumferentially extending liner comprising at least one resonator on the circumferentially extending liner including one or more outwardly projecting sidewalls on an exterior surface of the circumferentially extending liner and an end cap affixed to the one or more outwardly projecting sidewalls forming a resonator chamber on the exterior surface of the circumferentially extending liner; and
the at least one resonator further comprises a plurality of apertures in the circumferentially extending liner within an area defined by the one or more outwardly projecting sidewalls, wherein the one or more outwardly projecting sidewalls are integrally formed with the circumferentially extending liner allowing fluid flow communication between the interior combustion chamber and the resonator chamber;
wherein the end cap is affixed to a site on the one or more outwardly projecting sidewalls spaced radially outward from the exterior surface of the circumferentially extending liner;
wherein the circumferentially extending liner has a thickness within the area defined by the one or more outwardly projecting sidewalls that is less than a thickness of the circumferentially extending liner immediately outside the area defined by the one or more outwardly projecting sidewalls;
the combustor further comprising a thermal barrier coating disposed along an inner surface of the circumferentially extending liner including an inner surface

Assignees

• Siemens Energy Inc
• Siemens Ag

Inventors

• Tiwary Abhijeet
• Ramier Stephen A
• Fox Timothy A
• Bertoncello James
• Williams Steven

Classifications

• F23R3/42

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

• F23M20/005

  Noise absorbing means · CPC title

• Y10T29/49323

  Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23M2900/05004

  Special materials for walls or lining · CPC title