# US 10,478,920 B2 · Dual wall components for gas turbine engines > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,478,920 B2 - Document ID: US10478920B2 - Status: Granted - Kind: B2 - Application number: 14/847,571 - Filed: 2015-09-08 - Published: 2016-03-31 - Granted: 2019-11-19 - Earliest claimed: 2014-09-29 - Assignees: ROLLS-ROYCE plc - Applicants: Rolls-Royce Corporation - Inventors: Quinlan Y. Shuck - Web page: https://patentgrep.com/patent/US10478920B2 ## CPC - B23K 26/34: Laser welding for purposes other than joining - B22F 3/105: by using electric current {other than for infrared radiant energy}, laser radiation or plasma (B22F3/11 takes precedence){; by ultrasonic bonding (B22F3/115 takes precedence)} - B22F 5/009: {of turbine components other than turbine blades (of turbine blades B22F5/04)} - B22F 5/04: of turbine blades - B22F 7/08: with one or more parts not made from powder {(B22F7/062 takes precedence)} - B23K 26/142: for the removal of by-products - B23K 26/144: the fluid stream containing particles, e.g. powder - B23K 26/244: Overlap seam welding - B23K 26/32: taking account of the properties of the material involved - B23K 26/324: involving non-metallic parts - B23K 26/342: Build-up welding - B23K 26/702: {Auxiliary equipment} - F01D 5/187: {Convection cooling} - F01D 5/189: {the insert having a tubular cross-section, e.g. airfoil shape} - B23K 2101/001: {Turbines} - B23K 2103/14: Titanium or alloys thereof - B23K 2103/18: Dissimilar materials - B23K 2103/26: {Alloys of Nickel and Cobalt and Chromium} - B23K 2103/52: {Ceramics} - F05D 2260/204: by the use of microcircuits - 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 - 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 ## Abstract A dual wall component for use in a gas turbine engine and a method for making the same are disclosed herein. The dual wall component includes an inner support wall and an outer shield wall that extends around the inner support wall to act as a heat shield for the inner support wall. ## Claims ### Claim 1 A method for producing a dual wall component for a gas turbine engine, the method comprising: depositing powder feedstock at predetermined positions on an inner wall, applying a first directed energy beam onto the powder feedstock to create pedestals and form inner weld joints between an outer surface of the inner wall and the pedestals, positioning an outer wall on the pedestals, and welding the pedestals to an inner surface of the outer wall by applying a second directed energy beam onto an outer surface of the outer wall at predetermined positions corresponding to the pedestals to form outer weld joints between the inner surface of the outer wall and the pedestals. ### Claim 2 (depends on 1) The method of claim 1, wherein the first directed energy beam and the second directed energy beam are supplied by a single energy source. ### Claim 3 (depends on 1) The method of claim 1, wherein the powder feedstock is deposited using blown powder directed energy deposition. ### Claim 4 (depends on 1) The method of claim 1, further comprising depositing powder fill onto the outer surface of the inner wall between the pedestals to support the outer wall when the outer wall is positioned on the pedestals and to assist with welding the inner surface of the outer wall to the pedestal. ### Claim 5 (depends on 4) The method of claim 4, wherein the powder feedstock is a nickel-based superalloy or a cobalt-based superalloy. ### Claim 6 (depends on 1) The method of claim 1, further comprising removing a leftover portion of the powder feedstock after formation of the inner weld joint between the pedestal and the outer surface of the inner wall and after formation of the outer weld joint between the pedestal and the inner surface of the outer wall. ### Claim 7 (depends on 6) The method of claim 6, wherein removing the leftover portion of the powder feedstock is performed by suspending the powder in a liquid. ### Claim 8 (depends on 6) The method of claim 6, wherein removing the powder feedstock comprises pumping fluid between the inner wall and the outer wall. ### Claim 9 (depends on 1) The method of claim 1, wherein a concave feature is formed along the outer surface of the outer wall. ### Claim 10 (depends on 9) The method of claim 9, further comprising filling in the concave features along the outer surface of the outer wall with a powder fill and applying a third directed energy beam with a single energy source to the powder fill to create a fill cap weld joint to form a smooth surface along the outer surface of the outer wall. ### Claim 11 An airfoil for use in a gas turbine engine, the airfoil comprising: an inner wall; an outer wall that extends around the inner wall to act as a heat shield for the inner wall; a plurality of spaced apart pedestals welded to an outer surface of the inner wall to form an inner weld joint and welded to an inner surface of the outer wall to form an outer weld joint, wherein the pedestals transmit loads between the inner wall and the outer wall while maintaining a spaced apart relationship between the inner wall and the outer wall to define a cooling channel between the inner wall and the outer wall to conduct cooling air through the airfoil; and a plurality of fill caps welded to an outer surface of the outer wall to form a cap weld joint located opposite the outer weld joints along the outer wall to smooth concave features formed in the outer wall during welding of the pedestals to the outer wall. ### Claim 12 (depends on 11) The airfoil of claim 11, wherein the pedestal comprises a nickel-based superalloy or a cobalt-based superalloy. ### Claim 13 (depends on 11) The airfoil of claim 11, wherein the outer wall comprises a plurality of cooling holes spaced apart from the pedestals and extending between the cooling channel and an outer surface of the outer wall. ### Claim 14 (depends on 11) The airfoil of claim 11, wherein the inner wall is formed to include cooling holes spaced apart from the pedestals and opening into the cooling channel. ### Claim 15 A dual wall component for use in a gas turbine engine, the dual wall component comprising: an inner wall; an outer wall spaced apart from the inner wall to form a cooling channel between the inner wall and the outer wall; a plurality of spaced apart pedestals that extend from the inner wall to the outer wall through the cooling channel, each pedestal welded to the inner wall to form an inner weld joint and welded to the outer wall to form an outer weld joint; and a plurality of fill caps welded to the outer surface of the outer wall to form a cap weld joint located opposite the outer weld joints along the outer wall. ### Claim 16 (depends on 15) The component of claim 15, wherein the plurality of pedestals are spaced apart from one another. ### Claim 17 (depends on 15) The component of claim 15, wherein the pedestal comprises a nickel-based superalloy or a cobalt-based superalloy. ### Claim 18 (depends on 15) The component of claim 15, wherein the outer wall includes a plurality of cooling holes spaced apart from the pedestals and opening into the cooling channel.