# US 2020/0400313 A1 · Combustor panel configuration with skewed side walls > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2020/0400313 A1 - Document ID: US20200400313A1 - Status: Published application - Kind: A1 - Application number: 16/448,414 - Filed: 2019-06-21 - Published: 2020-12-24 - Earliest claimed: 2019-06-21 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: San Quach; Jeremy Styborski; Caroline Karanian - Web page: https://patentgrep.com/patent/US20200400313A1 ## CPC - F23R 3/06: Arrangement of apertures along the flame tube - F23M 5/02: characterised by the shape of the bricks or blocks used - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F23R 3/50: Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) - F23R 2900/03042: Film cooled combustion chamber walls or domes - 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) - 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 combustor of a gas turbine engine including a first forward liner panel. The forward liner panel including a liner panel forward edge, a liner panel aft edge opposite of the liner panel forward edge, and a first liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor. ## Claims ### Claim 1 A combustor of a gas turbine engine, the combustor comprising: a first forward liner panel comprising: a liner panel forward edge; a liner panel aft edge opposite of the liner panel forward edge; and a first liner panel side edge between the liner panel aft edge and the liner panel forward edge, wherein the first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor. ### Claim 2 (depends on 1) The combustor of claim 1, where the first forward liner panel further comprising: a second liner panel side edge between the liner panel aft edge and the liner panel forward edge, the second liner panel side edge being about parallel to the first liner panel side edge, wherein the second liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to the swirl flow in the combustor. ### Claim 3 (depends on 1) The combustor of claim 1, wherein the liner panel forward edge and the liner panel aft edge are parallel. ### Claim 4 (depends on 1) The combustor of claim 1, further comprising: a second forward liner panel circumferentially adjacent to the first forward liner panel, the first forward liner panel and the second forward liner panel being in a spaced relationship forming a gap therebetween. ### Claim 5 (depends on 4) The combustor of claim 4, wherein the first forward liner panel is offset from the second forward liner panel to direct cooling airflow from a cavity of the first forward liner panel to a hot side of the second forward liner panel. ### Claim 6 (depends on 2) The combustor of claim 2, further comprising: a second forward liner panel circumferentially adjacent to the first forward liner panel, the first forward liner panel and the second forward liner panel being in a spaced relationship forming a gap therebetween ### Claim 7 (depends on 6) The combustor of claim 6, wherein the second forward liner panel further comprises: a liner panel forward edge; a liner panel aft edge opposite of the liner panel forward edge of the second forward liner panel; a first liner panel side edge between the liner panel aft edge of the second forward liner panel and the liner panel forward edge of the second forward liner panel, wherein the first liner panel side edge of the second forward liner panel is non-perpendicular to the liner panel forward edge of the second forward liner panel and oriented at an angle about perpendicular to the swirl flow in the combustor; and a second liner panel side edge between the liner panel aft edge of the second forward liner panel and the liner panel forward edge of the second forward liner panel, the second liner panel side edge of the second forward liner panel being about parallel to the first liner panel side edge of the second forward liner panel, wherein the second liner panel side edge of the second forward liner panel is non-perpendicular to the liner panel forward edge of the second forward liner panel and oriented at an angle about perpendicular to the swirl flow in the combustor. ### Claim 8 (depends on 7) The combustor of claim 7, wherein the first liner panel side edge of the first forward liner panel is offset from the second liner panel side edge of the second forward liner panel to direct cooling airflow from the cavity of the first forward liner panel to a hot side of the second forward liner panel. ### Claim 9 (depends on 8) The combustor of claim 8, wherein the first liner panel side edge of the first forward liner panel is in a facing spaced relationship with the second liner panel side edge of the second forward liner panel defining the gap therebetween. ### Claim 10 (depends on 7) The combustor of claim 7, wherein at least one of the first liner panel side edge of the first forward liner panel and the second liner panel side edge of the second forward liner panel is operably shaped to direct cooling airflow from a cavity of the first forward liner panel to a hot side of the second forward liner panel. ### Claim 11 (depends on 7) The combustor of claim 7, wherein the first liner panel side edge of the first forward liner panel is operably shaped to direct cooling airflow from a cavity of the first forward liner panel to a hot side of the second forward liner panel. ### Claim 12 (depends on 7) The combustor of claim 7, wherein the second liner panel side edge of the second forward liner panel is operably shaped to direct cooling airflow from a cavity of the first forward liner panel to a hot side of the second forward liner panel. ### Claim 13 (depends on 1) The combustor of claim 1, wherein the first forward liner panel further comprises a side wall at the first liner panel side edge of the first forward liner panel, wherein the side wall further comprises cooling film orifices. ### Claim 14 (depends on 7) The combustor of claim 7, wherein the second forward liner panel further comprises a side wall at the first liner panel side edge of the second forward liner panel, wherein the side wall does not include cooling film orifices. ### Claim 15 (depends on 1) The combustor of claim 1, further comprising: an aft liner panel located aft of the first forward liner panel, wherein the aft liner panel is in a spaced relationship with the first forward liner panel forming a circumferential gap therebetween. ### Claim 16 (depends on 1) The combustor of claim 1, further comprising: an aft liner panel located aft of the first forward liner panel, wherein the aft liner panel is integrally attached to the first forward liner panel to form a combined liner panel. ### Claim 17 (depends on 2) The combustor of claim 2, wherein the first liner panel side edge and the second liner panel side edge are linear in shape. ### Claim 18 (depends on 2) The combustor of claim 2, wherein the first liner panel side edge and the second liner panel side edge are curvilinear in shape. ### Claim 19 A gas turbine engine, comprising: a combustor comprising; a forward liner panel comprising: a liner panel forward edge; a liner panel aft edge opposite of the liner panel forward edge; and a first liner panel side edge between the liner panel aft edge and the liner panel forward edge, wherein the first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor. ### Claim 20 A forward liner panel for use in a combustor of a gas turbine engine, the forward liner panel comprising: a liner panel forward edge; a liner panel aft edge opposite of the liner panel forward edge; and a first liner panel side edge between the liner panel aft edge and the liner panel forward edge, wherein the first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor.