# US 10,767,490 B2 · Hot section engine components having segment gap discharge holes > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,767,490 B2 - Document ID: US10767490B2 - Status: Granted - Kind: B2 - Application number: 15/699,303 - Filed: 2017-09-08 - Published: 2019-03-14 - Granted: 2020-09-08 - Earliest claimed: 2017-09-08 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Carey Clum; Dominic J. Mongillo, Jr. - Web page: https://patentgrep.com/patent/US10767490B2 ## CPC - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - B23P 15/02: turbine or like blades from one piece - F01D 5/187: {Convection cooling} - F05D 2230/00: Manufacture - F05D 2240/122: related to the trailing edge of a stator vane - F05D 2240/304: related to the trailing edge of a rotor blade - F05D 2260/202: by film cooling - F05D 2260/2214: by increasing the heat transfer surface - F05D 2260/22141: using fins or ribs - 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) - B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract Components for gas turbine engines and methods of making the same, the components including a component body having an external side wall and an internal side wall and defining at least a first cooling cavity and a second cooling cavity between the external side wall and the internal side wall, at least one segmented rib extending within the component body and separating the first cooling cavity from the second cooling cavity, wherein the first and second cooling cavities, the at least one segmented rib comprising at least two rib segments separated by a segment gap, and a discharge hole formed in the external side wall fluidly connected the segment gap to an exterior surface of the component body. ## Claims ### Claim 1 An airfoil for a gas turbine engine, the airfoil comprising: an airfoil body having an external side wall and an internal side wall and defining a first cooling cavity and a second cooling cavity between the external side wall and the internal side wall; at least one segmented rib extending within the airfoil body and separating the first cooling cavity from the second cooling cavity, wherein the first and second cooling cavities are defined between the external side wall and the internal side wall, the at least one segmented rib comprising at least two rib segments separated by a segment gap; and a discharge hole formed in the external side wall fluidly connecting the segment gap to an exterior surface of the airfoil body, wherein a center of the discharge hole is aligned with a radially oriented axis of the at least two rib segments that define the segment gap. ### Claim 2 (depends on 1) The airfoil of claim 1, wherein the at least one segmented rib comprises at least three rib segments and at least two segments gaps between the rib segments, the airfoil comprising at least one discharge hole located at each of the segment gaps. ### Claim 3 (depends on 1) The airfoil of claim 1, wherein: the at least one segmented rib comprises a plurality of segmented ribs, and the airfoil body comprises at least one additional cooling cavity. ### Claim 4 (depends on 1) The airfoil of claim 1, wherein the discharge hole is angled relative to the exterior surface of the airfoil body. ### Claim 5 (depends on 1) The airfoil of claim 1, wherein the airfoil body is a body of hot section engine airfoil. ### Claim 6 (depends on 1) The airfoil of claim 1, wherein a portion of cooling air within the first cooling cavity and a portion of cooling air within the second cooling cavity are ejected from a respective cooling cavity through the discharge hole. ### Claim 7 (depends on 1) The airfoil of claim 1, wherein the external side wall is at least one of a pressure sidewall and a suction side wall of the airfoil body. ### Claim 8 (depends on 1) The airfoil of claim 1, wherein at least one of the first cooling cavity and the second cooling cavity fluidly discharges out of a tip of the airfoil body. ### Claim 9 (depends on 1) The airfoil of claim 1, wherein the segment gap has a radial gap size h, the rib segments have a local thickness t, and the discharge hole has a hydraulic diameter Dh, and the radial gap size h is defined as 2t≤h≤4t or 2Dh≤h≤4Dh. ### Claim 10 A method of manufacturing an airfoil for a gas turbine engine, the method comprising: forming an airfoil body having an external side wall and an internal side wall; forming at least one segmented rib within the airfoil body, the at least one segmented rib separating a first cooling cavity from a second cooling cavity within the airfoil body, wherein the first cooling cavity and the second cooling cavity are defined between the external side wall and the internal side wall, the segmented rib comprising at least two rib segments separated by a segment gap; and forming a discharge hole in the external side wall to fluidly connect the segment gap to an exterior surface of the airfoil body, wherein a center of the discharge hole is aligned with a radially oriented axis of the at least two rib segments that define the segment gap. ### Claim 11 (depends on 10) The method of claim 10, wherein the at least one segmented rib comprises at least three rib segments and at least two segments gaps between the rib segments, the method comprising forming at least one discharge hole at each of the segment gaps. ### Claim 12 (depends on 10) The method of claim 10, wherein: the at least one segmented rib comprises a plurality of segmented ribs, and the airfoil body is formed with at least one additional cooling cavity. ### Claim 13 (depends on 10) The method of claim 10, wherein the discharge hole is angled relative to the exterior surface of the airfoil body. ### Claim 14 (depends on 10) The method of claim 10, wherein the airfoil body is a body of a hot section engine airfoil. ### Claim 15 (depends on 10) The method of claim 10, wherein a portion of cooling air within the first cooling cavity and a portion of cooling air within the second cooling cavity are ejected from a respective cooling cavity through the discharge hole. ### Claim 16 (depends on 10) The method of claim 10, wherein the external side wall is at least one of a pressure sidewall and a suction sidewall of the airfoil body. ### Claim 17 (depends on 10) The method of claim 10, wherein at least one of the first cooling cavity and the second cooling cavity fluidly discharges out of a tip of the airfoil body. ### Claim 18 (depends on 10) The method of claim 10, wherein the airfoil body is formed using at least one of fugitive core technologies and additive manufacturing processes. ### Claim 19 (depends on 10) The method of claim 10, wherein the segment gap has a radial gap size h, the rib segments have a local thickness t, and the discharge hole has a hydraulic diameter Dh, and the radial gap size h is defined as 2t≤h≤4t or 2Dh≤h≤4Dh.