# US 9,038,395 B2 · Combustors with quench inserts > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,038,395 B2 - Document ID: US9038395B2 - Status: Granted - Kind: B2 - Application number: 13/434,618 - Filed: 2012-03-29 - Published: 2013-10-03 - Granted: 2015-05-26 - Earliest claimed: 2012-03-29 - Assignees: Honeywell International Inc. - Applicants: Nagaraja S. Rudrapatna; Philip Smalley; Lowell Frye; William Landram - Inventors: Nagaraja S. Rudrapatna; Philip Smalley; Lowell Frye; William Landram - Web page: https://patentgrep.com/patent/US9038395B2 ## CPC - F23R 3/06: Arrangement of apertures along the flame tube - F23R 3/16: with devices inside the flame tube or the combustion chamber to influence the air or gas flow - F23R 2900/00017: Assembling combustion chamber liners or subparts - F23R 2900/00018: Manufacturing combustion chamber liners or subparts - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - Y10T 29/49323: Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles - 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) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defining an air admission hole for directing a first jet of pressurized air into the combustion chamber, and the air admission hole may have a non-circular shape. The combustor further includes an insert positioned within the air admission hole to guide the first jet through the air admission hole and into the combustion chamber. ## Claims ### Claim 1 A combustor for a turbine engine, comprising: a first liner comprising a hot side and a cold side; a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein; the first liner defining an air admission hole for directing a first jet of pressurized air into the combustion chamber, the air admission hole having a non-circular shape; and an insert positioned within the air admission hole to guide the first jet through the air admission hole and into the combustion chamber, wherein the insert includes a shoulder abutting the hot side and a flared inlet portion abutting the cold side, wherein the insert has an outer circumference swaged into the air admission hole such that the outer circumference of the insert matches the non-circular shape of the air admission hole. ### Claim 2 (depends on 1) The combustor of claim 1, wherein the air admission hole has a tri-lobe shape. ### Claim 3 (depends on 1) The combustor of claim 1, wherein the air admission hole has a hexagonal shape. ### Claim 4 (depends on 1) The combustor of claim 1, wherein the air admission hole has a knurled shape. ### Claim 5 (depends on 1) The combustor of claim 1, wherein the air admission hole has a shape with at least one straight portion and at least one curved portion. ### Claim 6 A method for installing an insert in an air admission hole of a combustor liner, the insert including a body portion, a shoulder, and an inlet portion and the combustor liner having a liner wall with a first side and a second side, the method comprising the steps of: inserting the inlet portion through the air admission hole from the first side to the second side until the shoulder abuts the hot side, wherein the air admission hole has a generally non-circular shape; and deforming the inlet portion such that the inlet portion has an outer diameter greater than a diameter of the air admission hole such that the inlet portion and the shoulder capture the combustor liner to retain the insert relative to the air admission hole, wherein the deforming step includes swaging the body portion of the insert such that an outer circumference of the body portion matches the generally non-circular shape of the air admission hole. ### Claim 7 (depends on 6) The method of claim 6, wherein the air admission hole has a tri-lobe shape. ### Claim 8 (depends on 6) The method of claim 6, wherein the air admission hole has a hexagonal shape. ### Claim 9 (depends on 6) The method of claim 6, wherein the air admission hole has a knurled shape. ### Claim 10 (depends on 6) The method of claim 6, wherein the air admission hole has a shape with at least one straight portion. ### Claim 11 (depends on 6) The method of claim 6, wherein the first liner is a dual-walled liner with a hot wall and a cold wall, and wherein the air admission hole is defined in the hot wall. ### Claim 12 (depends on 1) The combustor of claim 1, wherein the first liner is a dual-walled liner with a hot wall and a cold wall, wherein the cold wall defines a plurality of impingement cooling holes to direct cooling air onto the surface of the hot wall, and wherein the air admission hole is defined in the hot wall. ### Claim 13 (depends on 12) The combustor of claim 12, wherein the air admission hole defined in the hot wall is a first air admission hole, and wherein the combustor further comprises a second air admission hole in the cold wall that is in fluid communication with the first air admission hole such that the first jet flows through the second air admission hole, then through the insert and the first air admission hole into the combustion chamber.