# US 2014/0150435 A1 · Damping device for a gas turbine combustor > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0150435 A1 - Document ID: US20140150435A1 - Status: Published application - Kind: A1 - Application number: 14/088,527 - Filed: 2013-11-25 - Published: 2014-06-05 - Earliest claimed: 2012-11-30 - Assignees: ALSTOM Technology Ltd - Applicants: ALSTOM Technology Ltd - Inventors: Thomas Michael MAURER; Urs Benz; Mirko Ruben Bothien - Web page: https://patentgrep.com/patent/US20140150435A1 ## CPC - F23R 3/42: characterised by the arrangement or form of the flame tubes or combustion chambers - F23M 20/005: {Noise absorbing means} - F23R 3/00: Continuous combustion chambers using liquid or gaseous fuel - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F05D 2260/963: by Helmholtz resonators - F23R 2900/00014: Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F23M: CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract The invention relates to a damping device for a gas turbine combustor with significantly reduced cooling air mass flow requirements. The damping device includes a wall with a first inner wall and a second outer wall, arranged in a distance to each other. The inner wall is subjected to high temperatures on a side with a hot gas flow. A plurality of cooling channels extend essentially parallel between the first inner wall and the second outer wall, and at least one damping volume bordered by cooling channels. Furthermore, the damping device includes a first passage for supplying a cooling medium from a cooling channel into the damping volume and a second passage for connecting the damping volume to the combustion chamber. An end plate, fixed to the inner wall, separates the damping volume from the combustion chamber. ## Claims ### Claim 1 Damping device for a gas turbine combustor, comprising a wall with a first inner wall and a second outer wall, arranged in a distance to each other, wherein said inner wall is subjected to high temperatures on a side with a hot gas flow, a plurality of cooling channels extending essentially parallel between the first inner wall and the second outer wall, and at least one damping volume bordered by cooling channels, a first passage for supplying a cooling medium from a cooling channel into the damping volume and a neck passage for connecting the damping volume to the combustion chamber, an end plate fixed to the inner wall, separating the damping volume from the combustion chamber, said end plate is provided with the neck passage, and additionally provided with at least one feed plenum for the cooling medium, at least one exit plenum for the cooling medium and at least one cooling passage enabling a flow of cooling medium from the at least one first feed plenum to a second feed plenum or to the at least one exit plenum. ### Claim 2 (depends on 1) Damping device according to claim 1, wherein the said at least one cooling passage acts as a near wall cooling channel. ### Claim 3 (depends on 2) Damping device according to claim 2, wherein the end plate comprises a plurality of near wall cooling channels. ### Claim 4 (depends on 3) Damping device according to claim 3, wherein the near wall cooling channels have essentially the same cross-section. ### Claim 5 (depends on 1) Damping device according to claim 1, wherein at least one feed plenum communicates via feeding passage in wall with a cooling channel. ### Claim 6 (depends on 1) Damping device according to claim 1, wherein at least two feed plena are connected in series by one or more cooling passages. ### Claim 7 (depends on 6) Damping device according to claim 6, wherein at least three feed plena are connected in series. ### Claim 8 (depends on 6) Damping device according to claim 6, wherein consecutive plena are arranged at different lateral edges of the end plate. ### Claim 9 (depends on 8) Damping device according to claim 8, wherein consecutive plena are arranged at opposite edges of the end plate. ### Claim 10 (depends on 9) Damping device according to claim 9, wherein cooling passages run parallel. ### Claim 11 (depends on 1) Damping device according to claim 1, wherein the at least one exit plenum communicates with either the damping volume or the combustion chamber. ### Claim 12 (depends on 1) Damping device according to claim 1, wherein the lateral edges of the end plate are provided with recesses, and in interaction with the connected inner wall these recesses form the plena. ### Claim 13 (depends on 1) Damping device according to claim 1, wherein the end plate is fixed to the inner wall by welding. ### Claim 14 (depends on 1) Damping device according to claim 1, wherein the inner wall is a liner of a gas turbine combustor. ### Claim 15 (depends on 1) Damping device according to claim 1, wherein the wall comprises more than one individual damping volumes. ### Claim 16 (depends on 15) Damping device according to claim 15, wherein the more than one individual damping volumes are arranged in axial direction (in relation to the combustor axis). ### Claim 17 (depends on 15) Damping device according to claim 15, wherein the individual damping volumes have different parameters.