# US 11,898,465 B2 · Forming lined cooling aperture(s) in a turbine engine component > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,898,465 B2 - Document ID: US11898465B2 - Status: Granted - Kind: B2 - Application number: 17/401,914 - Filed: 2021-08-13 - Published: 2023-02-16 - Granted: 2024-02-13 - Earliest claimed: 2021-08-13 - Assignees: Rtx Corporation - Applicants: Raytheon Technologies Corporation - Inventors: Brian Craig; James M. Koonankeil; Brian T. Hazel; Paul E. Denney; Dominic J. Mongillo - Web page: https://patentgrep.com/patent/US11898465B2 ## CPC - F01D 5/288: {Protective coatings for blades} - F01D 5/005: {Repairing methods or devices} - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F01D 5/284: {Selection of ceramic materials} - F01D 9/023: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings} - 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)} - F02K 1/822: {Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors} - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F23R 3/005: {Combined with pressure or heat exchangers} - F23R 3/06: Arrangement of apertures along the flame tube - B23H 9/10: Working turbine blades or nozzles - B23H 9/14: Making holes - B23K 26/389: {of fluid openings, e.g. nozzles, jets} - B23K 2101/001: {Turbines} - B23P 9/00: Treating or finishing surfaces mechanically, with or without calibrating, primarily to resist wear or impact, e.g. smoothing or roughening turbine blades or bearings (treatment covered by a single other subclass, see the relevant subclass, e.g. B24C, C21D7/00, C22F1/00); Features of such surfaces not otherwise provided for, their treatment being unspecified - B23P 15/02: turbine or like blades from one piece - B23P 2700/06: Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components - C23C 4/06: Metallic material - C23C 4/073: containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements - C23C 4/11: Oxides - C23C 4/12: characterised by the method of spraying - C23C 4/16: Wires; Tubes - F05D 2230/11: by electrochemical methods - F05D 2230/12: by spark erosion methods - F05D 2230/13: using lasers - F05D 2230/313: by physical vapour deposition - F05D 2230/314: by chemical vapour deposition - F05D 2230/90: Coating; Surface treatment - F05D 2240/11: Shroud seal segments - F05D 2240/81: Cooled platforms - F05D 2250/324: divergent - F05D 2260/202: by film cooling - F05D 2300/2112: Aluminium oxides - F23R 2900/00018: Manufacturing combustion chamber liners or subparts - F23R 2900/03042: Film cooled combustion chamber walls or domes - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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) - B23H: WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL (processes for the electrolytic or electrophoretic production of coatings, electroforming, or apparatus therefor C25D; processes for the electrolytic removal of material from objects C25F; manufacturing printed circuits using precipitation techniques to apply the conductive material to form the desired conductive pattern H05K3/18) - B23K: SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM - B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q) - C23C: COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL (making metal-coated products by extrusion B21C23/22; covering with metal by connecting pre-existing layers to articles, see the relevant places, e.g. B21D39/00, B23K; metallising of glass C03C; metallising mortars, concrete, artificial stone, ceramics or natural stone C04B41/00; enamelling of, or applying a vitreous layer to, metals C23D; treating metal surfaces or coating of metals by electrolysis or electrophoresis C25D; single-crystal film growth C30B; by metallising textiles D06M11/83; decorating textiles by locally metallising D06Q1/04) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A preform meter section and a preform diffuser section are formed in the substrate. An internal coating is applied to at least the preform meter section to provide a meter section of a cooling aperture. External coating material is applied over the substrate. The applying of the external coating material forms an external coating over the substrate. The applying of the external coating also builds up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture. ## Claims ### Claim 1 A manufacturing method, comprising: providing a preform component for a turbine engine, the preform component comprising a substrate; forming a preform meter section and a preform diffuser section in the substrate; applying an internal coating to at least the preform meter section to provide a meter section of a cooling aperture; and applying external coating material over the substrate, the applying of the external coating material forming an external coating over the substrate, and the applying of the external coating building up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture. ### Claim 2 (depends on 1) The manufacturing method of claim 1, wherein the diffuser section, provided following the applying of the external coating material, satisfies a design specification. ### Claim 3 (depends on 1) The manufacturing method of claim 1, wherein the cooling aperture is completely formed following the applying of the external coating material without further machining. ### Claim 4 (depends on 1) The manufacturing method of claim 1, wherein the internal coating comprises an aluminide coating. ### Claim 5 (depends on 1) The manufacturing method of claim 1, wherein the internal coating comprises PtAl. ### Claim 6 (depends on 1) The manufacturing method of claim 1, wherein the internal coating comprises NiCoCrAlY. ### Claim 7 (depends on 1) The manufacturing method of claim 1, wherein the substrate comprises metal; and the external coating material comprises ceramic. ### Claim 8 (depends on 1) The manufacturing method of claim 1, further comprising: applying a bond coating onto the substrate; wherein the external coating material is applied onto the bond coating. ### Claim 9 (depends on 1) The manufacturing method of claim 1, wherein the preform meter section and the preform diffuser section are formed using a common machining process. ### Claim 10 (depends on 1) The manufacturing method of claim 1, wherein the forming of the preform meter section and the preform diffuser section comprises forming the preform meter section using a first machining process; and forming at least a portion of the preform diffuser section using a second machining process that is different than the first machining process. ### Claim 11 (depends on 10) The manufacturing method of claim 10, wherein the first machining process comprises an electrical discharge machining process; and the second machining process comprises a laser machining process. ### Claim 12 (depends on 1) The manufacturing method of claim 1, wherein the preform component comprises a preform of an airfoil for the turbine engine. ### Claim 13 (depends on 1) The manufacturing method of claim 1, wherein the preform component comprises a preform of a flowpath wall for the turbine engine. ### Claim 14 (depends on 1) The manufacturing method of claim 1, wherein the diffuser section comprises a single lobed diffuser section. ### Claim 15 (depends on 1) The manufacturing method of claim 1, wherein the diffuser section comprises a multi-lobed diffuser section. ### Claim 16 A manufacturing method, comprising: providing a preform component for a turbine engine, the preform component comprising a substrate; forming a preform aperture extending through the substrate; applying an internal coating to the preform aperture to provide a meter section of a cooling aperture; forming a preform diffuser section in the substrate; and applying external coating material over the substrate, the applying of the external coating material forming an external coating over the substrate, and the applying of the external coating material building up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture. ### Claim 17 (depends on 16) The manufacturing method of claim 16, wherein the internal coating comprises an aluminide coating. ### Claim 18 (depends on 16) The manufacturing method of claim 16, wherein the preform aperture is formed using a first machining process; and the preform diffuser section is formed using a second machining process that is different than the first machining process. ### Claim 19 A manufacturing method, comprising: providing a preform component for a turbine engine, the preform component comprising a substrate configured with a meter section of a cooling aperture and a preform diffuser section, and the meter section lined with an internal coating; and applying external coating material over the substrate to form an external coating over the substrate; and build up the preform diffuser section to provide a final form diffuser section of the cooling aperture. ### Claim 20 (depends on 19) The manufacturing method of claim 19, wherein the internal coating comprises aluminide.