# US 10,371,381 B2 · Combustor wall for a gas turbine engine and method of acoustic dampening > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,371,381 B2 - Document ID: US10371381B2 - Status: Granted - Kind: B2 - Application number: 14/805,963 - Filed: 2015-07-22 - Published: 2016-06-02 - Granted: 2019-08-06 - Earliest claimed: 2014-07-22 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: JinQuan Xu - Web page: https://patentgrep.com/patent/US10371381B2 ## CPC - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F02C 7/24: Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) - F23M 20/005: {Noise absorbing means} - F23R 3/04: Air inlet arrangements - F23R 2900/00014: Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators - F23R 2900/03042: Film cooled combustion chamber walls or domes - F23R 2900/03043: Convection cooled combustion chamber walls with means for guiding the cooling air flow - 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) - 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) - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A vascular wall of a combustor that may be for a gas turbine engine includes a first face defining at least in-part a combustion chamber, a second face defining at least in-part a cooling air plenum, and a vascular lattice structure located between the first and second faces for distributing cooling air from the plenum and to the chamber. The vascular lattice structure may be configured to enhance cooling air flow where needed whiling providing structural support. The orientation of the vascular lattice structure may further contribute toward acoustic dampening. ## Claims ### Claim 1 A combustor wall comprising: a hot side panel comprising a first face, the first face defining at least in-part a combustion chamber; a cold side panel comprising a second face, the second face defining at least in-part a cooling air plenum; and a vascular lattice structure located between the first and second faces for distributing cooling air from the cooling air plenum and to the combustion chamber; the cold side panel spaced from the vascular lattice structure so as to define an annular cooling cavity therebetween. ### Claim 2 (depends on 1) The combustor wall set forth in claim 1, wherein the hot side panel and the vascular lattice structure are one unitary piece. ### Claim 3 (depends on 1) The combustor wall set forth in claim 1, wherein at least a portion of the combustor wall is additive manufactured. ### Claim 4 (depends on 1) The combustor wall set forth in claim 1, wherein a plurality of inlet holes are configured in the second face and a plurality of outlet holes are configured in the first face for flowing cooling air from the cooling air plenum, through the vascular lattice structure and into the combustion chamber. ### Claim 5 (depends on 4) The combustor wall set forth in claim 4, wherein the plurality of outlet holes are film cooling holes. ### Claim 6 (depends on 5) The combustor wall set forth in claim 5, wherein the plurality of film cooling holes are multi-lobed cooling holes. ### Claim 7 (depends on 4) The combustor wall set forth in claim 4, wherein the vascular lattice structure has a plurality of hubs and a plurality of branches projecting between the plurality of hubs in fluid communication between the plurality of inlet holes in the second face and the plurality of outlet holes in the first face. ### Claim 8 A combustor of a gas turbine engine comprising: a hot side panel defining at least in-part a combustion chamber; a cold side panel spaced from the hot side panel and defining a cooling air plenum; and a vascular lattice structure located in an annular cooling cavity defined between the hot and cold side panels; wherein a gap extends between and separates the cold side panel and the vascular lattice structure to define a portion of the annular cooling cavity that accepts air from the cooling air plenum. ### Claim 9 (depends on 8) The combustor set forth in claim 8, wherein a plurality of outlet holes are in the hot side panel and are in fluid communication between the combustion chamber and the annular cooling cavity, and a plurality of inlet holes are in the cold side panel and are in fluid communication between the cooling air plenum and the cooling annular cavity. ### Claim 10 (depends on 9) The combustor set forth in claim 9, wherein the vascular lattice structure is formed as one unitary piece to the hot side panel. ### Claim 11 (depends on 10) The combustor set forth in claim 10, wherein the plurality of inlet holes are impingement holes. ### Claim 12 (depends on 10) The combustor set forth in claim 10, wherein a combination of the combined hot side panel and the vascular lattice structure is divided circumferentially into a plurality of portions and about an axis. ### Claim 13 (depends on 8) The combustor set forth in claim 8, wherein the vascular lattice structure has a plurality of hubs and a plurality of branches interconnected to the plurality of hubs for cooling air flow distribution. ### Claim 14 (depends on 8) The combustor set forth in claim 8, wherein the vascular lattice structure has a plurality of hubs and a plurality of branches interconnected to the plurality of hubs for structural support.