# US 11,994,293 B2 · Impingement cooling apparatus support structure and method of manufacture > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,994,293 B2 - Document ID: US11994293B2 - Status: Granted - Kind: B2 - Application number: 17/007,089 - Filed: 2020-08-31 - Published: 2023-12-21 - Granted: 2024-05-28 - Earliest claimed: 2020-08-31 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Jonathan Dwight Berry; Clay Thomas Griffis; Keith Cletus Belsom; Charles Van Buchan - Web page: https://patentgrep.com/patent/US11994293B2 ## CPC - F23R 3/06: Arrangement of apertures along the flame tube - F01D 9/023: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings} - F02C 3/14: characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F23R 3/005: {Combined with pressure or heat exchangers} - F23R 3/10: for primary air (F23R3/06, F23R3/045 take precedence) - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23R 3/346: {for staged combustion} - F23R 3/50: Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) - F05D 2260/201: by impingement of a fluid - F23R 2900/03044: Impingement cooled combustion chamber walls or subassemblies - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The integrated combustor nozzle further includes an impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members that each extend from a respective opening defined in the flange to a respective closed end. Each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall. The impingement cooling apparatus further includes stand-offs extending from each impingement member of the plurality of impingement members. The stand-offs space apart each impingement member of the plurality of impingement members from surrounding surfaces. ## Claims ### Claim 1 An integrated combustor nozzle, comprising: a combustion liner extending radially between an inner liner segment and an outer liner segment, the combustion liner including a forward end portion, an aft end portion, a first side wall, and a second side wall, the aft end portion of the combustion liner defining a turbine nozzle, the combustion liner defining a cavity forward of the turbine nozzle, the cavity extending between the first side wall and the second side wall, wherein a first rib and a second rib extend from one of the first side wall or the second side wall and within the cavity, the first rib and the second rib axially spaced apart such that the cavity is partitioned into a forward cavity portion, a middle cavity portion, and an aft cavity portion, and wherein the first rib and the second rib define one or more openings such that the forward cavity portion, the middle cavity portion, and the aft cavity portion are in fluid communication; a fuel injector having an inlet disposed within the middle cavity portion, the fuel injector extending through one of the first side wall or the second side wall; and an impingement cooling apparatus positioned within the aft cavity portion, the impingement cooling apparatus comprising: a flange; a plurality of impingement members each extending from a respective opening defined in the flange to a respective closed end, each impingement member including an impingement wall and a solid wall spaced apart from the impingement wall, wherein each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall, wherein the inlet of the fuel injector receives post-impingement air from the aft cavity portion; and stand-offs extending from each impingement member of the plurality of impingement members, the stand-offs spacing apart each impingement member of the plurality of impingement members from surrounding surfaces. ### Claim 2 (depends on 1) The integrated combustor nozzle as in claim 1, wherein each impingement member of the plurality of impingement members includes a first solid side wall that extends between the impingement wall and the solid wall and a second solid side wall that extends between the impingement wall and the solid wall. ### Claim 3 (depends on 2) The integrated combustor nozzle as in claim 2, wherein the stand-offs comprise side wall stand-offs, and wherein the side wall stand-offs extend from and couple the first solid side wall of an impingement member to the second solid side wall of a neighboring impingement member. ### Claim 4 (depends on 2) The integrated combustor nozzle as in claim 2, wherein the stand-offs comprise impingement wall stand-offs, and wherein each impingement wall stand-off extends from the impingement wall of one of the plurality of impingement members and contacts one of the first side wall or the second side wall of the combustion liner. ### Claim 5 (depends on 2) The integrated combustor nozzle as in claim 2, wherein the stand-offs comprise side wall stand-offs and impingement wall stand-offs, and wherein at least one side wall stand-off and at least one impingement wall stand-off are disposed proximate the flange on each impingement member of the plurality of impingement members, and wherein at least one side wall stand-off and at least one impingement wall stand-off are disposed proximate the closed end of each impingement member of the plurality of impingement members. ### Claim 6 (depends on 1) The integrated combustor nozzle as in claim 1, wherein each impingement member of the plurality of impingement members defines an internal volume, wherein each impingement member of the plurality of impingement members includes a first protrusion and a second protrusion within the internal volume of the impingement member, the first protrusion extending from the impingement wall and the second protrusion extending from the solid wall, and wherein each of a plurality of cross-supports extends directly from the first protrusion through the internal volume to the second protrusion. ### Claim 7 A turbomachine comprising: a compressor; a compressor discharge casing disposed downstream from the compressor; a turbine disposed downstream from the compressor discharge casing; and an annular combustion system disposed within the compressor discharge casing, the annular combustion system including a plurality of integrated combustor nozzles disposed in an annular array about an axial centerline of the turbomachine, wherein each integrated combustor nozzle comprises: a fuel injection panel extending radially between an inner liner segment and an outer liner segment, the fuel injection panel including a forward end portion, an aft end portion, a first side wall, and a second side wall, the aft end portion of the fuel injection panel defining a turbine nozzle, the fuel injection panel defining a cavity forward of the turbine nozzle, the cavity extending between the first side wall and the second side wall, wherein a first rib and a second rib extend from one of the first side wall or the second side wall and within the cavity, the first rib and the second rib axially spaced apart such that the cavity is partitioned into a forward cavity portion, a middle cavity portion, and an aft cavity portion, and wherein the first rib and the second rib define one or more openings such that the forward cavity portion, the middle cavity portion, and the aft cavity portion are in fluid communication; a fuel injector having an inlet disposed within the middle cavity portion, the fuel injector extending through one of the first side wall or the second side wall; and an impingement cooling apparatus positioned within the aft cavity portion, the impingement cooling apparatus comprising: a flange; a plurality of impingement members each extending from a respective opening defined in the flange to a respective closed end, each impingement member including an impingement wall and a solid wall spaced apart from the impingement wall, wherein each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall, wherein the inlet of the fuel injector receives post-impingement air from the aft cavity portion; and stand-offs extending from each impingement member of the plurality of impingement members, wherein the stand-offs space apart each impingement member of the plurality of impingement members from surrounding surfaces. ### Claim 8 (depends on 7) The turbomachine as in claim 7, wherein each impingement member of the plurality of impingement members includes a first solid side wall that extends between the impingement wall and the solid wall and a second solid side wall that extends between the impingement wall and the solid wall. ### Claim 9 (depends on 8) The turbomachine as in claim 8, wherein the stand-offs comprise side wall stand-offs, and wherein the side wall stand-offs extend from and couple the first solid side wall of an impingement member to the second solid side wall of a neighboring impingement member. ### Claim 10 (depends on 8) The turbomachine as in claim 8, wherein the stand-offs comprise impingement wall stand-offs, and wherein each impingement wall stand-off extends from the impingement wall of one of the plurality of impingement members and contacts one of the first side wall or the second side wall of the fuel injection panel. ### Claim 11 (depends on 8) The turbomachine as in claim 8, wherein the stand-offs comprise side wall stand-offs and impingement wall stand-offs, and wherein at least one side wall stand-off and at least one impingement wall stand-off are disposed proximate the flange on each impingement member of the plurality of impingement members, and wherein at least one side wall stand-off and at least one impingement wall stand-off are disposed proximate the closed end of each impingement member of the plurality of impingement members. ### Claim 12 (depends on 8) The turbomachine as in claim 8, wherein each impingement member of the plurality of impingement members comprises cross-supports that extend between the impingement wall and the solid wall. ### Claim 13 (depends on 12) The turbomachine as in claim 12, wherein each impingement member of the plurality of impingement members includes a first protrusion extending from the impingement wall and a second protrusion extending from the solid wall, and wherein each of a plurality of cross-supports extends directly between the first protrusion and the second protrusion. ### Claim 14 (depends on 13) The turbomachine as in claim 13, wherein each of the plurality of cross-supports includes a first support bar and a second support bar that intersect with one another within the impingement member. ### Claim 15 (depends on 6) The integrated combustor nozzle as in claim 6, wherein the first protrusion and the second protrusion each define a T-shaped cross-section.