# US 10,309,314 B2 · Finned ignitor grommet for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,309,314 B2 - Document ID: US10309314B2 - Status: Granted - Kind: B2 - Application number: 14/770,341 - Filed: 2014-02-25 - Published: 2016-01-14 - Granted: 2019-06-04 - Earliest claimed: 2013-02-25 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: James B. Hoke; James P. Bangerter - Web page: https://patentgrep.com/patent/US10309314B2 ## CPC - F02C 7/25: Fire protection or prevention (in general A62) - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F05D 2220/32: in gas turbines - F05D 2240/35: Combustors or associated equipment - F05D 2260/231: Preventing heat transfer - F23R 2900/00004: Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits - F23R 2900/00012: Details of sealing devices - F23R 2900/03042: Film cooled combustion chamber walls or domes - F23R 2900/03044: Impingement cooled combustion chamber walls or subassemblies - F23R 2900/03045: Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A heat shield for a combustor of a gas turbine engine includes a cold side opposite a hot side, the cold side defines a grommet that surrounds an igniter aperture, the grommet includes a multiple of fins. ## Claims ### Claim 1 A combustor of a gas turbine engine comprising: a support shell; and a heat shield mounted to the support shell, the heat shield comprising: a hot side; and a cold side opposite said hot side, wherein said cold side defines a grommet that surrounds an igniter aperture in the heat shield, said grommet contacts said support shell to provide a seal therewith, and said grommet includes a multiple of fins and a rail; wherein the multiple of fins are between the heat shield and the support shell; wherein the rail extends circumferentially around an axis of the igniter aperture along a first portion of a circular trajectory between opposing circumferential rail ends; wherein the multiple of fins are arranged circumferentially around the axis along a second portion of the circular trajectory such that the multiple of fins are circumferentially inline with the rail along the circular trajectory; wherein the multiple of fins are in a gap define between the opposing circumferential rail ends; and wherein each of the multiple of fins has a circular cross-sectional geometry. ### Claim 2 (depends on 1) The combustor as recited in claim 1, wherein said rail extends only partially around a circumference of said igniter aperture. ### Claim 3 (depends on 1) The combustor as recited in claim 1, wherein said multiple of fins extend only partially around a circumference of said igniter aperture. ### Claim 4 (depends on 1) The combustor as recited in claim 1, wherein said rail extends only partially around a circumference of said igniter aperture and said multiple of fins extend only for a remainder of said circumference of said igniter aperture. ### Claim 5 (depends on 1) The combustor as recited in claim 1, wherein said rail extends substantially 240 degrees around said igniter aperture and said multiple of fins extend substantially 120 degrees around said igniter aperture. ### Claim 6 (depends on 1) The combustor as recited in claim 1, wherein said multiple of fins are pegs. ### Claim 7 (depends on 1) The combustor of claim 1, wherein the multiple of fins partially define an outer periphery of the igniter aperture. ### Claim 8 (depends on 1) The combustor of claim 1, wherein the multiple of fins are formed integral with the heat shield. ### Claim 9 (depends on 1) The combustor of claim 1, wherein a first of the multiple of fins is configured as a pin or a peg. ### Claim 10 (depends on 1) The combustor of claim 1, wherein a first of the multiple of fins is a protrusion that is contiguous with and projects out from the cold side. ### Claim 11 A combustor of a gas turbine engine comprising: a support shell; and a heat shield with a grommet that surrounds an igniter aperture, wherein the heat shield is mounted to the support shell, said grommet includes a rail and a multiple of fins disposed between a cold side of the heat shield and the support shell, and the grommet contacts the support shell to provide a seal therewith; wherein the rail extends circumferentially about an axis of the igniter aperture along a first portion of an annular trajectory, and the multiple of fins are arranged circumferentially about the axis of the igniter aperture along a second portion of the annular trajectory such that the multiple of fins are circumferentially inline with the rail along the annular trajectory; and wherein a first of the multiple of fins has a circular cross-sectional geometry. ### Claim 12 (depends on 11) The combustor as recited in claim 11, wherein said rail extends only partially around a circumference of said igniter aperture. ### Claim 13 (depends on 11) The combustor as recited in claim 11, wherein said multiple of fins extend only partially around a circumference of said igniter aperture. ### Claim 14 (depends on 11) The combustor as recited in claim 11, wherein said rail extends only partially around a circumference of said igniter aperture and said multiple of fins extend only for a remainder of said circumference of said igniter aperture. ### Claim 15 (depends on 11) The combustor as recited in claim 11, wherein said rail extends substantially 240 degrees around said igniter aperture and said multiple of fins extend substantially 120 degrees around said igniter aperture. ### Claim 16 (depends on 11) The combustor as recited in claim 11, wherein said multiple of fins are pegs. ### Claim 17 (depends on 11) The combustor as recited in claim 11, further comprising an igniter that extends at least partially through said igniter aperture.