# US 11,029,027 B2 · Dilution/effusion hole pattern for thick combustor panels > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,029,027 B2 - Document ID: US11029027B2 - Status: Granted - Kind: B2 - Application number: 16/151,160 - Filed: 2018-10-03 - Published: 2020-04-09 - Granted: 2021-06-08 - Earliest claimed: 2018-10-03 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Scott D. Lewis; James B. Hoke; Jeffrey Jay Lienau - Web page: https://patentgrep.com/patent/US11029027B2 ## CPC - F23M 5/08: Cooling thereof; Tube walls - F02C 3/14: characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) - F02K 3/06: with front fan - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F23R 3/06: Arrangement of apertures along the flame tube - F05D 2240/35: Combustors or associated equipment - F05D 2260/202: by film cooling - F23R 2900/03041: Effusion cooled combustion chamber walls or domes - F23R 2900/03042: Film cooled combustion chamber walls or domes - 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 - 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) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A combustor panel may comprise a dilution hole, a plurality of film cooling holes each of the plurality comprising an inlet and an outlet, a first group of the plurality of film cooling holes arranged circumferentially about the dilution hole, wherein each of film cooling holes of the first group have a first outlet angle oriented radially toward the center of the dilution hole, and a second group of the plurality of film cooling holes arranged radially outward of the first group and relatively circumferentially between the first group. ## Claims ### Claim 1 A combustor panel, comprising: a dilution hole; a plurality of film cooling holes, wherein each of the film cooling holes in the plurality of film cooling holes comprise an inlet and an outlet, wherein the outlet is defined by a major axis and a minor axis, wherein the major axis is longer than the minor axis; a first group of the plurality of film cooling holes arranged circumferentially about the dilution hole, the first group of the plurality extending to encircle an upstream side and a downstream side of the dilution hole, wherein the major axis of each of the outlets of the film cooling holes of the first group are oriented radially toward a center of the dilution hole; and a second group of the plurality of film cooling holes arranged radially, with respect to the center of the dilution hole, outward of the first group and relatively circumferentially between the first group, wherein each of the first group of the plurality of film cooling holes and the second group of the plurality of film cooling holes comprise more than one film cooling hole, wherein each of the outlets of the film cooling holes of the first group have a first outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the first outlet angle is not more than 25° away from the radius extending from the centerline of the dilution hole, wherein each of the outlets of the second group of the plurality of film cooling holes are arranged in an arcuate segment extending about the center of the dilution hole and downstream thereof, wherein each of the outlets of the film cooling holes of the second group having a second outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a tangent, at the point of intersection of the major axis and the minor axis of the outlet, to the radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the second outlet angle is not more than 25° away from the tangent. ### Claim 2 (depends on 1) The combustor panel of claim 1, wherein the first group further comprises first set holes upstream of the dilution hole and second set holes downstream of the dilution hole characterized in that the first set holes have a greater surface concentration than the second set holes, wherein each of the first set holes and the second set holes comprise more than one film cooling hole. ### Claim 3 (depends on 1) The combustor panel of claim 1, wherein the first group further comprises first set holes on the upstream side of the dilution hole and second set holes on the downstream side of the dilution hole, wherein the second group of the plurality of film cooling holes are arranged relatively between the second set holes, each of the plurality of film cooling holes of the second group having a second outlet angle oriented in a circumferential direction relatively toward a tangent to a proximate point on a circumference of the dilution hole, wherein each of the first set holes and the second set holes comprise more than one film cooling hole. ### Claim 4 (depends on 3) The combustor panel of claim 3, wherein 80% of the outlets of the film cooling holes of the second group have the second outlet angle not more than 25° away from the tangent of the proximate point. ### Claim 5 (depends on 4) The combustor panel of claim 4, wherein the second group of the plurality of film cooling holes comprises third set holes and fourth set holes, wherein the third set holes are located radially outward of the first set holes and circumferentially between the second set holes and the fourth set holes, wherein the second set holes have a first surface angle between 20° and 75°, wherein the third set holes have a second surface angle between 20° and 65°, and wherein the fourth set holes have a third surface angle between 20° and 70°, wherein each of the third set holes and the fourth set holes comprise more than one film cooling hole. ### Claim 6 (depends on 3) The combustor panel of claim 3, further comprising a third group of the plurality of film cooling holes arranged downstream of the second group comprising fifth set holes arranged radially outward of the second group and oriented in a circumferential direction relatively toward the respective tangent of the respective proximate point on the circumference of the dilution hole, wherein the third group further comprises a plurality of downstream set holes each radially outward of the respectively upstream set holes, wherein each of the downstream set holes are characterized by a gradual turning of the respective outlet angle from the respective tangent toward a downstream direction, wherein each of the third group of the plurality of film cooling holes and the fifth set holes comprise more than one film cooling hole. ### Claim 7 A combustor assembly comprising: an inner annular wall; an outer annular wall about the inner annular wall; a dome joining the inner annular wall and the outer annular wall, wherein each of the inner annular wall and the outer annular wall comprise a hot surface defining a combustion chamber therebetween; and a dilution hole through the hot surface in fluid communication with a respective cold surface; a plurality of film cooling holes, wherein each of the film cooling holes in the plurality of film cooling holes comprise an inlet on the respective cold surface in fluid communication with an outlet on the respective hot surface, wherein the outlet is defined by a major axis and a minor axis, wherein the major axis is longer than the minor axis; a first group of the plurality of film cooling holes arranged circumferentially about the dilution hole, the first group of the plurality extending to encircle an upstream side and a downstream side of the dilution hole, wherein the major axis of each of the outlets of the film cooling holes of the first group are oriented radially toward a center of the dilution hole; and a second group of the plurality of film cooling holes arranged radially, with respect to the center of the dilution hole, outward of the first group and relatively circumferentially between the first group, wherein each of the first group of the plurality of film cooling holes and the second group of the plurality of film cooling holes comprise more than one film cooling hole, wherein each of the outlets of the film cooling holes of the first group have a first outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the first outlet angle is not more than 25° away from the radius extending from the centerline of the dilution hole, wherein each of the outlets of the second group of the plurality of film cooling holes are arranged in an arcuate segment extending about the center of the dilution hole and downstream thereof, wherein each of the outlets of the film cooling holes of the second group having a second outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a tangent, at the point of intersection of the major axis and the minor axis of the outlet, to the radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the second outlet angle is not more than 25° away from the tangent. ### Claim 8 (depends on 7) The combustor assembly of claim 7, wherein the first group further comprises first set holes upstream of the dilution hole and second set holes downstream of the dilution hole characterized in that the first set holes have a greater surface concentration than the second set holes, wherein each of the first set holes and the second set holes comprise more than one film cooling hole. ### Claim 9 (depends on 7) The combustor assembly of claim 7, wherein the first group further comprises first set holes upstream of the dilution hole and second set holes downstream of the dilution hole wherein the second group of the plurality of film cooling holes are arranged relatively between the second set holes, each of the plurality of film cooling holes of the second group having a second outlet angle oriented in a circumferential direction relatively toward a tangent to a proximate point on a circumference of the dilution hole, wherein each of the first set holes and the second set holes comprise more than one film cooling hole. ### Claim 10 (depends on 9) The combustor assembly of claim 9, wherein 80% of the outlets of the film cooling holes of the second group have the second outlet angle not more than 25° away from the tangent of the proximate point. ### Claim 11 (depends on 10) The combustor assembly of claim 10, wherein the second group of the plurality of film cooling holes comprises third set holes and fourth set holes, wherein the third set holes are located radially outward of the first set holes and circumferentially between the second set holes and the fourth set holes, wherein the second set holes have a first surface angle between 20° and 75°, wherein the third set holes have a second surface angle between 25° and 65°, and wherein the fourth set holes have a third surface angle between 20° and 70°, wherein each of the third set holes and the fourth set holes comprise more than one film cooling hole. ### Claim 12 (depends on 9) The combustor assembly of claim 9, further comprising a third group of the plurality of film cooling holes arranged downstream of the second group comprising fifth set holes arranged radially outward of the second group and oriented in a circumferential direction relatively toward the respective tangent of the respective proximate point on the circumference of the dilution hole, wherein the third group further comprises a plurality of downstream set holes each radially outward of the respectively upstream set holes, wherein each of the downstream set holes are characterized by a gradual turning of the respective outlet angle from the respective tangent toward a downstream direction, wherein each of the third group of the plurality of film cooling holes and the fifth set holes comprise more than one film cooling hole. ### Claim 13 A gas turbine engine comprising: a compressor section configured to compress a gas; a combustor section aft of the compressor section and configured to combust the gas, wherein the combustor section comprises a combustor panel comprising: a dilution hole; a plurality of film cooling holes, wherein each of the film cooling holes in the plurality of film cooling holes comprise an inlet and an outlet, wherein the outlet is defined by a major axis and a minor axis, wherein the major axis is longer than the minor axis; a first group of the plurality of film cooling holes arranged circumferentially about the dilution hole, the first group of the plurality extending to encircle an upstream side and a downstream side of the dilution hole, wherein the major axis of each of the outlets of the film cooling holes of the first group are oriented radially toward a center of the dilution hole; and a second group of the plurality of film cooling holes arranged radially, with respect to the center of the dilution hole, outward of the first group and relatively circumferentially between the first group, wherein each of the first group of the plurality of film cooling holes and the second group of the plurality of film cooling holes comprise more than one film cooling hole wherein each of the outlets of the film cooling holes of the first group have a first outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the first outlet angle is not more than 25° away from the radius extending from the centerline of the dilution hole, wherein each of the outlets of the second group of the plurality of film cooling holes are arranged in an arcuate segment extending about the center of the dilution hole and downstream thereof, wherein each of the outlets of the film cooling holes of the second group having a second outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a tangent, at the point of intersection of the major axis and the minor axis of the outlet, to the radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the second outlet angle is not more than 25° away from the tangent. ### Claim 14 (depends on 13) The gas turbine engine of claim 13, wherein the first group further comprises first set holes upstream of the dilution hole and second set holes downstream of the dilution hole characterized in that the first set holes have a greater surface concentration than the second set holes, wherein each of the first set holes and the second set holes comprise more than one film cooling hole. ### Claim 15 (depends on 13) The gas turbine engine of claim 13, wherein the first group further comprises first set holes upstream of the dilution hole and second set holes downstream of the dilution hole, wherein the second group of the plurality of film cooling holes are arranged relatively between the second set holes, wherein each of the first set holes and the second set holes comprise more than one film cooling hole. ### Claim 16 (depends on 15) The gas turbine engine of claim 15, wherein the second group of the plurality of film cooling holes comprises third set holes and fourth set holes, wherein the third set holes are located radially outward of the first set holes and circumferentially between the second set holes and the fourth set holes, wherein the second set holes have a first surface angle between 20° and 75°, wherein the third set holes have a second surface angle between 25° and 65°, and wherein the fourth set holes have a third surface angle between 20° and 70°, wherein each of the third set holes and the fourth set holes comprise more than one film cooling hole. ### Claim 17 (depends on 15) The gas turbine engine of claim 15, further comprising a third group of the plurality of film cooling holes arranged downstream of the second group comprising fifth set holes arranged radially outward of the second group and oriented in a circumferential direction relatively toward the respective tangent of the respective proximate point on the circumference of the dilution hole, wherein the third group further comprises a plurality of downstream set holes each radially outward of the respectively upstream set holes, wherein each of the downstream set holes are characterized by a gradual turning of the respective outlet angle from the respective tangent toward a downstream direction, wherein each of the third group of the plurality of film cooling holes and the fifth set holes comprise more than one film cooling hole.