# US 10,309,228 B2 · Impingement insert 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 10,309,228 B2 - Document ID: US10309228B2 - Status: Granted - Kind: B2 - Application number: 15/177,370 - Filed: 2016-06-09 - Published: 2017-12-14 - Granted: 2019-06-04 - Earliest claimed: 2016-06-09 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Sandip Dutta; Kassy Moy Hart - Web page: https://patentgrep.com/patent/US10309228B2 ## CPC - F01D 5/189: {the insert having a tubular cross-section, e.g. airfoil shape} - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F01D 11/24: by selectively cooling-heating stator or rotor components - F05D 2240/11: Shroud seal segments - F05D 2250/232: conical - F05D 2250/323: convergent - F05D 2250/324: divergent - F05D 2260/201: by impingement of a fluid - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract The present disclosure is directed to an impingement insert for a gas turbine engine. The impingement insert includes an insert wall having an inner surface and an outer surface spaced apart from the inner surface. A nozzle extends outwardly from the outer surface of the insert wall. The nozzle includes an outer surface and a circumferential surface. The insert wall and the nozzle collectively define a cooling passage extending from the inner surface of the insert wall to the outer surface of the nozzle. The cooling passage includes an inlet portion, a throat portion, a converging portion extending from the inlet portion to the throat portion, an outlet portion, and a diverging portion extending from the throat portion to the outlet portion. The cooling passage further includes a cross-sectional shape having a semicircular portion and a non-circular portion. ## Claims ### Claim 1 An impingement insert for a gas turbine engine, comprising: an insert wall comprising an inner surface and an outer surface spaced apart from the inner surface; a nozzle extending at least one of outwardly from the outer surface of the insert wall and inwardly from the inner surface of the insert wall, the nozzle comprising an outer surface and a circumferential surface; wherein the insert wall and the nozzle collectively define a cooling passage extending therethrough; wherein the cooling passage comprises an inlet portion, a throat portion, a converging portion extending from the inlet portion to the throat portion, an outlet portion, and a diverging portion extending from the throat portion to the outlet portion; and wherein the cooling passage further comprises a cross-sectional shape, the cross-sectional shape comprising a semicircular portion and a non-circular portion, the non-circular portion of the cross-sectional shape comprising a first linear side and a second linear side, the first linear side and the second linear side coupled by a fillet portion. ### Claim 2 (depends on 1) The impingement insert of claim 1, further comprising: a pedestal comprising a pedestal surface that extends outwardly from the outer surface of the insert wall and couples to a portion of the circumferential surface of the nozzle. ### Claim 3 (depends on 2) The impingement insert of claim 2, wherein the pedestal surface and a circumferential line extending circumferentially outwardly from the outer surface of the insert wall define a pedestal angle therebetween, and wherein the pedestal angle is between thirty degrees and ninety degrees. ### Claim 4 (depends on 2) The impingement insert of claim 2, wherein the insert wall, the nozzle, and the pedestal are integrally formed. ### Claim 5 (depends on 1) The impingement insert of claim 1, wherein the first linear side comprises a first linear side length and the second linear side comprises a second linear side length, and wherein the first linear side length is the same as the second linear side length. ### Claim 6 (depends on 1) The impingement insert of claim 1, wherein the first linear side and the second linear side define an angle therebetween, and wherein the angle is between 60 degrees and 120 degrees. ### Claim 7 (depends on 6) The impingement insert of claim 6, wherein the angle is 90 degrees. ### Claim 8 (depends on 1) The impingement insert of claim 1, wherein the semicircular portion of the cross-sectional shape couples directly to the non-circular portion of the cross-sectional shape. ### Claim 9 (depends on 1) The impingement insert of claim 1, wherein the semicircular portion of the cross-sectional shape is positioned radially inwardly from the non-circular portion of the cross-sectional shape. ### Claim 10 (depends on 1) The impingement insert of claim 1, wherein the converging portion comprises a converging portion length and the diverging portion comprises a diverging portion length, and wherein the converging portion length is the same as the diverging portion length. ### Claim 11 (depends on 1) The impingement insert of claim 1, wherein the converging portion comprises a converging portion angle and the diverging portion comprises a diverging portion angle, and wherein the converging portion angle and the diverging portion angle are different. ### Claim 12 A gas turbine engine, comprising: a compressor section; a combustion section; a turbine section; a gas turbine engine component; an impingement insert positioned within the gas turbine engine component, the impingement insert comprising: an insert wall comprising an inner surface and an outer surface spaced apart from the inner surface; a nozzle extending at least one of outwardly from the outer surface of the insert wall and inwardly from the inner surface of the insert wall, the nozzle comprising an outer surface and a circumferential surface; wherein the insert wall and the nozzle collectively define a cooling passage extending therethrough; wherein the cooling passage comprises an inlet portion, a throat portion, a converging portion extending from the inlet portion to the throat portion, an outlet portion, and a diverging portion extending from the throat portion to the outlet portion; and wherein the cooling passage further comprises a cross-sectional shape, the cross-sectional shape comprising a semicircular portion and a non-circular portion, the non-circular portion of the cross-sectional shape comprising a first linear side and a second linear side, the first linear side and the second linear side coupled by a fillet portion. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, further comprising: a pedestal comprising a pedestal surface extending outwardly from the outer surface of the insert wall and couples to a portion of the circumferential surface of the nozzle. ### Claim 14 (depends on 13) The gas turbine engine of claim 13, wherein the pedestal surface and a circumferential line extending circumferentially outwardly from the outer surface of the insert wall define a pedestal angle therebetween, and wherein the pedestal angle is between thirty degrees and sixty degrees. ### Claim 15 (depends on 12) The gas turbine engine of claim 12, wherein the first linear side and the second linear side define an angle therebetween, and wherein the angle is between 60 degrees and 120 degrees. ### Claim 16 (depends on 12) The gas turbine engine of claim 12, wherein the gas turbine component is a turbine nozzle or a turbine shroud.