# US 2014/0150436 A1 · Gas turbine part comprising a near wall cooling arrangement > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0150436 A1 - Document ID: US20140150436A1 - Status: Published application - Kind: A1 - Application number: 14/091,621 - Filed: 2013-11-27 - Published: 2014-06-05 - Earliest claimed: 2012-11-30 - Assignees: ALSTOM Technology Ltd - Applicants: ALSTOM Technology Ltd - Inventors: Adnan EROGLU; Michael Thomas MAURER; Diane LAUFFER - Web page: https://patentgrep.com/patent/US20140150436A1 ## CPC - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F01D 25/12: Cooling - F23M 5/085: {using air or other gas as the cooling medium} - F23R 3/005: {Combined with pressure or heat exchangers} - F23R 3/06: Arrangement of apertures along the flame tube - F05D 2260/20: Heat transfer, e.g. cooling - F05D 2260/201: by impingement of a fluid - F23R 2900/03043: Convection cooled combustion chamber walls with means for guiding the cooling air flow - 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) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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 A gas turbine combustor part of a gas turbine includes a wall, containing a plurality of near wall cooling channels extending essentially parallel to each other in a first direction within the wall in close vicinity to the hot side and being arranged in at least one row extending in a second direction. The near wall cooling channels are each provided at one end with an inlet for the supply of cooling air, and on the other end with an outlet for the discharge of cooling air. The inlets open into a common feeding channel for cooling air supply, and the outlets open into a common discharge channel for cooling air discharge. The feeding channel and the discharge channel extend in the second direction. ## Claims ### Claim 1 A gas turbine part, especially combustor part of a gas turbine, comprising a wall, which is subjected to high temperature gas on a hot side and a near wall cooling arrangement, with the wall containing a plurality of near wall cooling channels extending essentially parallel to each other in a first direction within the wall in close vicinity to the hot side and being arranged in at least one row extending in a second direction essentially perpendicular to said first direction, whereby said near wall cooling channels are each provided at one end with an inlet for the supply of cooling air, and on the other end with an outlet for the discharge of cooling air, whereby said inlets open into a common feeding channel for cooling air supply, and said outlets open into a common discharge channel for cooling air discharge, said feeding channel and said discharge channel extending in said second direction, said feeding channel being open at a first end to receive supplied cooling air and guide it the row of cooling channel inlets, and said discharge channel being open at a second end to discharge cooling air from the row of cooling air outlets, and means are provided within said near wall cooling arrangement to equalize the cooling air mass flow through the near wall cooling channels having a common feeding channel and/or discharge channel. ### Claim 2 (depends on 1) The gas turbine part according to claim 1, wherein all near wall cooling channels of said near wall cooling arrangement have essentially the same cross section (D). ### Claim 3 (depends on 1) The gas turbine part according to claim 1, wherein all near wall cooling channels of said near wall cooling arrangement are arranged within said row with an essentially constant inter-channel distance (d). ### Claim 4 (depends on 2) The gas turbine part according to claim 2, wherein the feeding channel has a cross section, which decreases in the second direction with increasing distance from said first end. ### Claim 5 (depends on 4) The gas turbine part according to claim 4, wherein the discharge channel has a cross section, which increases in the second direction with decreasing distance from said second end. ### Claim 6 (depends on 4) The gas turbine part according to claim 4, wherein the variation of the cross section with distance is linear. ### Claim 7 (depends on 6) The gas turbine part according to claim 6, wherein the feeding channel and the discharge channel are separated by a common separation wall, that the cross sections of the feeding channel and the discharge channel are each defined by said common separation wall and a respective outer channel wall, and that the variation of the cross section in the second direction is effected by an oblique orientation between the common separation wall and the outer channel walls. ### Claim 8 (depends on 7) The gas turbine part according to claim 7, wherein the direction of the common separation wall is parallel to the second direction, and that the directions of the outer channel walls are oblique with respect to the second direction. ### Claim 9 (depends on 7) The gas turbine part according to claim 7, wherein the direction of the common separation wall, and that the directions of the outer channel walls are parallel to the second direction, and that the direction of the common separation wall is oblique with respect to the second direction. ### Claim 10 (depends on 2) The gas turbine part according to claim 2, wherein the feeding channel and the discharge channel each have a constant cross section in the second direction, and that the number of cooling channels per unit length in the second direction decreases from the first end to the second end. ### Claim 11 (depends on 2) The gas turbine part according to claim 2, wherein the feeding channel and the discharge channel each have a constant cross section in the second direction, and that the cross section of the cooling channels decreases in the second direction from the first end to the second end. ### Claim 12 (depends on 1) The gas turbine part according to claim 1, wherein the near wall cooling arrangement comprises a plurality of rows of near wall cooling channels, that the rows run parallel to each other in the second direction, and that each of said rows has a separate feeding channel and discharge channel with a common separation wall and respective outer channel walls, and that neighbouring rows share an outer channel wall.