# US 2019/0316474 A1 · Cupped contour for gas turbine engine blade assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0316474 A1 - Document ID: US20190316474A1 - Status: Published application - Kind: A1 - Application number: 16/426,036 - Filed: 2019-05-30 - Published: 2019-10-17 - Earliest claimed: 2015-08-17 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Dipanjan Saha; Brooks E. Snyder; Thomas N. Slavens - Web page: https://patentgrep.com/patent/US20190316474A1 ## CPC - F01D 5/187: {Convection cooling} - B23K 26/34: Laser welding for purposes other than joining - B33Y 10/00: Processes of additive manufacturing - B33Y 80/00: Products made by additive manufacturing - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 25/12: Cooling - B22F 5/04: of turbine blades - B22F 7/08: with one or more parts not made from powder {(B22F7/062 takes precedence)} - B22F 10/20: Direct sintering or melting - B22F 10/64: by thermal means (control of energy beam parameters for post heating B22F10/364) - B23K 2101/001: {Turbines} - F05D 2220/32: in gas turbines - F05D 2230/21: by casting - F05D 2230/30: with deposition of material - F05D 2240/81: Cooled platforms - F05D 2260/204: by the use of microcircuits - Y02P 10/25: Process efficiency - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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 - B33Y: ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - 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 - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02P: CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A gas turbine engine assembly according to an example of the present disclosure includes, among other things, an endwall having a first material composition, an airfoil extending in a radial direction from the endwall, and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. A method of forming an endwall is also disclosed. ## Claims ### Claim 1 A gas turbine engine assembly, comprising: an endwall having a first material composition, wherein an airfoil extends in a radial direction from the endwall; and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. ### Claim 2 (depends on 1) The gas turbine engine assembly of claim 1, wherein at least one cooling channel of the endwall opens to the cooling chamber. ### Claim 3 (depends on 2) The gas turbine engine assembly of claim 2, wherein the cooling chamber is defined between the cupped contour and a surface of the endwall. ### Claim 4 (depends on 3) The gas turbine engine assembly of claim 3, wherein the airfoil extends in the radial direction from the endwall to a tip. ### Claim 5 (depends on 4) The gas turbine engine assembly of claim 4, wherein the surface of the endwall is a radially facing surface of the endwall with respect to the radial direction. ### Claim 6 (depends on 5) The gas turbine engine assembly of claim 5, wherein the at least one cooling channel is defined by a groove formed in the radially facing surface of the endwall such that a length of the groove defines an opening along the radially facing surface. ### Claim 7 (depends on 6) The gas turbine engine assembly of claim 6, wherein the cupped contour slopes from a sidewall of the airfoil towards the radially facing surface of the endwall. ### Claim 8 (depends on 2) The gas turbine engine assembly of claim 2, wherein the endwall is entirely radially misaligned from the cooling chamber. ### Claim 9 (depends on 2) The gas turbine engine assembly of claim 2, wherein the cupped contour covers one or more cooling channel openings. ### Claim 10 (depends on 9) The gas turbine engine assembly of claim 9, wherein the cupped contour covers one or more cooling channel inlets. ### Claim 11 (depends on 1) The gas turbine engine assembly of claim 1, wherein the endwall is an endwall of a blade comprising the airfoil. ### Claim 12 (depends on 1) The gas turbine engine assembly of claim 1, wherein the endwall is a cast endwall, and the cupped contour is and additively manufactured cupped contour. ### Claim 13 A gas turbine engine blade assembly, comprising: an endwall with a plurality of cooling channels; an airfoil extending radially from the endwall to a tip; and a cupped contour formed on the endwall to provide a cooling chamber between the cupped contour and a radially facing surface of the endwall. ### Claim 14 (depends on 13) The gas turbine engine blade assembly of claim 13, wherein at least one opening of the plurality of cooling channels opens to the cooling chamber, and at least one inlet of the plurality of cooling channels opens to the cooling chamber, the cupped contour covering the at least one opening and the at least one inlet. ### Claim 15 (depends on 14) The gas turbine engine assembly of claim 14, wherein the cupped contour slopes from a sidewall of the airfoil towards the radially facing surface of the endwall. ### Claim 16 (depends on 14) The gas turbine engine assembly of claim 14, wherein the at least one opening of the plurality of cooling channels is defined along the radially facing surface. ### Claim 17 (depends on 16) The gas turbine engine assembly of claim 16, wherein the endwall defines a portion of a gas path surface. ### Claim 18 (depends on 17) The gas turbine engine blade assembly of claim 17, wherein the endwall has a first material composition, and the cupped contour has a second material composition different than the first material composition. ### Claim 19 (depends on 13) The gas turbine engine blade assembly of claim 13, wherein the endwall is a cast endwall, and the cupped contour is and additively manufactured cupped contour. ### Claim 20 (depends on 13) The gas turbine engine blade assembly of claim 13, wherein the endwall has a first material composition, and the cupped contour has a second material composition different than the first material composition.