# US 12,215,604 B1 · Cooling nozzle vanes of a turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,215,604 B1 - Document ID: US12215604B1 - Status: Granted - Kind: B1 - Application number: 18/394,810 - Filed: 2023-12-22 - Granted: 2025-02-04 - Earliest claimed: 2023-12-22 - Assignees: Rtx Corporation - Applicants: RTX Corporation - Inventors: Lawrence A. Binek; Paul M. Lutjen; Jose R. Paulino - Web page: https://patentgrep.com/patent/US12215604B1 ## CPC - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F01D 9/023: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings} - F23R 3/50: Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) - F23R 3/54: Reverse-flow combustion chambers - F01D 5/187: {Convection cooling} - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F23R 2900/03044: Impingement cooled combustion chamber walls or subassemblies - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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) ## Abstract An assembly is provided for a turbine engine. This assembly includes a nozzle structure and a combustor wall. The nozzle structure includes a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis. The nozzle vanes extends radially between and are connected to the first platform and the second platform. The combustor wall includes a plurality of apertures. An upstream portion of the combustor wall is radially between and borders a plenum and a combustion chamber. A downstream portion of the combustor wall is radially between and borders the plenum and a gap. The downstream portion of the combustor wall axially overlaps the nozzle structure with the gap formed by and extending between the combustor wall and the first platform. The apertures extends through the downstream portion of the combustor wall and are aligned with the nozzle vanes. ## Claims ### Claim 1 An assembly for a turbine engine, comprising: a nozzle structure including a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis, the plurality of nozzle vanes extending radially between and connected to the first platform and the second platform; and a combustor wall comprising a plurality of apertures, an upstream portion of the combustor wall radially between and bordering a plenum and a combustion chamber, a downstream portion of the combustor wall radially between and bordering the plenum and a gap, the downstream portion of the combustor wall axially overlapping the nozzle structure with the gap formed by and extending between the combustor wall and the first platform, and the plurality of apertures extending through the downstream portion of the combustor wall and aligned with the plurality of nozzle vanes. ### Claim 2 (depends on 1) The assembly of claim 1, wherein each of the plurality of apertures is configured to direct air, received from the plenum, across the gap onto the first platform. ### Claim 3 (depends on 1) The assembly of claim 1, wherein the plurality of nozzle vanes comprise a first nozzle vane; and the plurality of apertures comprise a first aperture, and the first aperture is axially and circumferentially aligned with the first nozzle vane. ### Claim 4 (depends on 3) The assembly of claim 3, wherein the plurality of nozzle vanes further comprise a second nozzle vane circumferentially neighboring the first nozzle vane; and the plurality of apertures further comprise a second aperture, and the second aperture is circumferentially aligned with a channel between the first nozzle vane and the second nozzle vane. ### Claim 5 (depends on 1) The assembly of claim 1, wherein each of the plurality of apertures is circumferentially aligned with a respective one of the plurality of nozzle vanes. ### Claim 6 (depends on 1) The assembly of claim 1, wherein the plurality of apertures comprise a first aperture; the first aperture extends along a centerline through the downstream portion of the combustor wall from the plenum to the gap; the centerline is coincident with a point on a surface of the first platform; and the centerline is angularly offset from a normal line projecting out from the point on the surface of the first platform by an acute angle. ### Claim 7 (depends on 1) The assembly of claim 1, wherein the plurality of apertures comprise a first aperture; the first aperture extends along a centerline through the downstream portion of the combustor wall from the plenum to the gap; and at least a portion of the first aperture along the centerline has a round cross-sectional geometry. ### Claim 8 (depends on 1) The assembly of claim 1, wherein the plurality of apertures comprise a first aperture; the first aperture extends along a centerline through the downstream portion of the combustor wall from the plenum to the gap; and at least a portion of the first aperture along the centerline has a polygonal cross-sectional geometry. ### Claim 9 (depends on 1) The assembly of claim 1, wherein the plurality of apertures comprise a first aperture; and at least a portion of the first aperture laterally converges as the first aperture extends through the downstream portion of the combustor wall towards the gap. ### Claim 10 (depends on 1) The assembly of claim 1, wherein the plurality of apertures comprise a first aperture; and at least a portion of the first aperture laterally diverges as the first aperture extends through the downstream portion of the combustor wall towards the gap. ### Claim 11 (depends on 1) The assembly of claim 1, wherein the plurality of apertures include a first set of apertures and a second set of apertures; the first set of apertures are arranged in a first circumferential array about the axis; and the second set of apertures are arranged in a second circumferential array about the axis, and each aperture in the second set of apertures is circumferentially aligned with a respective aperture in the first set of apertures. ### Claim 12 (depends on 1) The assembly of claim 1, wherein the plurality of apertures include a first set of apertures and a second set of apertures; the first set of apertures are arranged in a first circumferential array about the axis; and the second set of apertures are arranged in a second circumferential array about the axis, and each aperture in the second set of apertures is circumferentially aligned with a respective circumferentially neighboring pair of apertures in the first set of apertures. ### Claim 13 (depends on 1) The assembly of claim 1, further comprising: a turbine wall axially overlapping the downstream portion of the combustor wall and bordering the plenum; and an intermediate structure extending between a downstream end of the first platform and an upstream end of the turbine wall; the downstream portion of the combustor wall extending axially to the intermediate structure. ### Claim 14 (depends on 1) The assembly of claim 1, wherein the gap is fluidly coupled to the combustion chamber at an upstream end of the first platform. ### Claim 15 (depends on 1) The assembly of claim 1, wherein the first platform is an inner platform radially outboard of and circumscribing the downstream portion of the combustor wall; and the second platform is an outer platform radially outboard of and circumscribing the inner platform. ### Claim 16 (depends on 1) The assembly of claim 1, further comprising: a second combustor wall projecting axially to and connected to the second platform; the combustion chamber extending radially between the combustor wall and the second combustor wall. ### Claim 17 An assembly for a turbine engine, comprising: a nozzle structure including a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis, each of the plurality of nozzle vanes extending radially from the first platform to the second platform; and a combustor wall comprising a plurality of apertures, an upstream portion of the combustor wall radially between and lining a plenum and a combustion chamber, a downstream portion of the combustor wall radially between and lining the plenum and a channel, the downstream portion of the combustor wall axially overlapping the nozzle structure with the channel formed by and extending between the combustor wall and the first platform, and the plurality of apertures configured to direct air, received from the plenum, across the channel and onto a surface of the first platform located opposite the plurality of nozzle vanes. ### Claim 18 (depends on 17) The assembly of claim 17, wherein the plurality of apertures comprise a first aperture; the first aperture is configured to direct a portion of the air along a trajectory across the channel to a point on the surface of the first platform, and the trajectory is angularly offset from a normal line projecting out from the point on the surface of the first platform by an angle greater than twenty degrees. ### Claim 19 (depends on 17) The assembly of claim 17, further comprising: a turbine wall axially overlapping the downstream portion of the combustor wall and bordering the plenum; and an intermediate structure extending between and formed integral with a downstream end of the first platform and an upstream end of the turbine wall; the downstream portion of the combustor wall extending axially to and formed integral with the intermediate structure, wherein the plurality of apertures extend through the downstream portion of the combustor wall. ### Claim 20 An assembly for a turbine engine, comprising: a monolithic body extending axially along and circumferentially about an axis, the monolithic body including an outer wall, an inner wall, an intermediate structure, a combustor wall, a plenum and a channel; the inner wall radially inboard of and axially overlapping the outer wall; the intermediate structure extending between and connected to an axial forward end of the outer wall and an axial forward end of the inner wall; a downstream portion of the combustor wall projecting axially to and connected to the intermediate structure, the plenum radially between and formed by the combustor wall and the inner wall, and the channel radially between and formed by the downstream portion of the combustor wall and the outer wall; and a plurality of apertures extending radially across the downstream portion of the combustor wall and fluidly coupling the plenum to the channel.