# US 8,784,037 B2 · Turbine shroud segment with integrated impingement plate > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,784,037 B2 - Document ID: US8784037B2 - Status: Granted - Kind: B2 - Application number: 13/221,997 - Filed: 2011-08-31 - Published: 2013-02-28 - Granted: 2014-07-22 - Earliest claimed: 2011-08-31 - Assignees: Pratt & Whitney Canada Corp. - Applicants: Eric Durocher; Guy Lefebvre - Inventors: Eric Durocher; Guy Lefebvre - Web page: https://patentgrep.com/patent/US8784037B2 ## CPC - B22F 3/225: {by injection molding} - B22F 5/009: {of turbine components other than turbine blades (of turbine blades B22F5/04)} - B22F 7/08: with one or more parts not made from powder {(B22F7/062 takes precedence)} - F01D 5/08: Heating, heat-insulating or cooling means {(specially adapted for radial flow machines or engines F01D5/04)} - F01D 9/04: forming ring or sector - F01D 25/246: {Fastening of diaphragms or stator-rings} - F05D 2240/11: Shroud seal segments - F05D 2240/15: Heat shield - F05D 2260/201: by impingement of a fluid - Y10T 29/4998: Combined manufacture including applying or shaping of fluent material - B22F: WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER (making alloys by powder metallurgy C22C); APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER - 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 - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract A turbine shroud segment is metal injection molded (MIM) about an insert having a cooling air cavity covered by an impingement plate. The insert is held in position in an injection mold and then the MIM material is injected in the mold to form the body of the shroud segment about the insert. ## Claims ### Claim 1 A method of manufacturing a shroud segment for a gas turbine engine, the method comprising: providing an insert defining a cooling air cavity covered by an impingement plate having a plurality of holes defined therethrough; holding the insert in position in an injection mold; and metal injection molding (MIM) a shroud segment body about the insert to form a composite component, including injecting a metal powder mixture into the injection mold to partially imbed the insert into the shroud segment body and subjecting the composite component to debinding and sintering operations. ### Claim 2 (depends on 1) The method of claim 1, wherein the impingement plate is provided in the form of a first sheet metal member, and wherein providing an insert comprises welding the first sheet metal member over a second sheet metal member. ### Claim 3 (depends on 2) The method defined in claim 2, wherein the second sheet metal member is formed into a vessel member having a peripheral rim, and wherein welding comprises welding the first sheet metal member to said peripheral rim. ### Claim 4 (depends on 3) The method defined in claim 3, wherein said first sheet metal member is spot welded to said peripheral rim of the vessel member. ### Claim 5 (depends on 1) The method defined in claim 1, comprising blocking the holes defined in the insert to prevent the metal powder mixture from flowing into the cooling air cavity during the metal injection process. ### Claim 6 (depends on 1) The method of claim 1, wherein the turbine shroud segment is metal injection molded with cooling air passages in flow communication with the cooling air cavity of the insert. ### Claim 7 (depends on 6) The method of claim 6, wherein additional holes are defined in the insert, and wherein pins are engaged in said holes to hold the insert in position in the injection mold, and wherein said pins are used to form said cooling air passages in the MIM shroud segment body. ### Claim 8 (depends on 7) The method of claim 7, wherein the insert comprises a vessel member on top of which is secured the impingement plate, the additional holes being defined in the vessel member, and wherein the pins block the metal injection mixture from entering into the cooling air cavity of the insert via the additional holes during the injection process. ### Claim 9 A method of creating a cooling air cavity in a shroud segment of a gas turbine engine, the method comprising: metal injection molding (MIM) a shroud segment body about a hollow insert having a cavity covered by an impingement plate, the impingement plate being provided at a radially outwardly facing surface of the MIM shroud segment body and having a plurality of holes defined therethrough for admitting air into the cavity of the hollow insert. ### Claim 10 (depends on 9) The method of claim 9, wherein metal injection molding the shroud segment body about the hollow insert comprises holding the hollow insert inside an injection mold in a position in which the impingement plate will form part of the radially outwardly facing surface. ### Claim 11 (depends on 9) The method of claim 9, wherein metal injection molding comprises placing the hollow insert at a predetermined position within a mold and filling the mold with a metal powder mixture. ### Claim 12 (depends on 9) The method of claim 9, comprising forming the hollow insert by welding a first sheet metal member over a second sheet metal member, the cavity of the hollow insert being defined between said first and second sheet metal members, and defining holes in said first sheet metal member to form said impingement plate. ### Claim 13 A shroud segment of a gas turbine engine comprising a metal injection molded (MIM) shroud body, an insert at least partly imbedded on a radially outer side of the MIM shroud body, the insert comprising first and second members defining therebetween a cooling air cavity, said first member having a plurality of impingement holes defined therethrough for directing cooling air into said cooling air cavity. ### Claim 14 (depends on 13) The shroud segment defined in claim 13, wherein the first member is a sheet metal impingement plate, and wherein the second member is a sheet metal pan-like container, the sheet metal impingement plate covering the sheet metal pan-like container. ### Claim 15 (depends on 14) The shroud segment defined in claim 14, wherein the sheet metal pan-like container has a flat bottom and a low peripheral rim, the sheet metal impingement plate resting on and being secured to said low peripheral rim. ### Claim 16 (depends on 13) The shroud segment defined in claim 13, wherein the MIM shroud body has forward and aft hooks projecting from the radially outer side of the body, and wherein said insert is disposed between said forward and aft hooks. ### Claim 17 (depends on 14) The shroud segment defined in claim 14, wherein holes are defined in the sheet metal pan-like container, said holes being in fluid flow communication with air channels defined in the MIM shroud body.