# US 10,370,981 B2 · Gas turbine engine component cooling circuit with respirating pedestal > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,370,981 B2 - Document ID: US10370981B2 - Status: Granted - Kind: B2 - Application number: 15/112,497 - Filed: 2015-01-26 - Published: 2016-11-17 - Granted: 2019-08-06 - Earliest claimed: 2014-02-13 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Thomas N. Slavens; Brooks E. Snyder - Web page: https://patentgrep.com/patent/US10370981B2 ## CPC - F01D 5/187: {Convection cooling} - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 25/12: Cooling - F01D 25/30: Exhaust heads, chambers, or the like - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F05D 2220/32: in gas turbines - F05D 2230/211: by precision casting, e.g. microfusing or investment casting - F05D 2230/31: Layer deposition - F05D 2240/35: Combustors or associated equipment - F05D 2260/204: by the use of microcircuits - F05D 2260/205: Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes - F05D 2260/2214: by increasing the heat transfer surface - F23R 2900/03045: Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling - 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) - 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) - 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 A component according to an exemplary aspect of the present disclosure includes, among other things, a pedestal that traverses a flow channel disposed between a first wall and a second wall. The pedestal includes at least one interior bore configured to communicate a cooling fluid inside of the pedestal. ## Claims ### Claim 1 A component, comprising: an airfoil section having an outer wall and an inner wall; and a pedestal that traverses across a flow channel from said outer wall to said inner wall, said flow channel disposed between said outer wall and said inner wall, said pedestal including a body and a head that extends transversely from said body, said head including at least one interior bore in fluid communication with said flow channel, and said body including a second bore extending from said head to said inner wall, wherein said at least one interior bore is configured to receive a cooling fluid from said flow channel and communicate said cooling fluid inside of said pedestal through said second bore and into a cavity formed inside of said inner wall. ### Claim 2 (depends on 1) The component as recited in claim 1, wherein said at least one interior bore feeds said cooling fluid from a cavity inside of said inner wall. ### Claim 3 (depends on 1) The component as recited in claim 1, wherein a head of said pedestal is received in a trough formed in said outer wall. ### Claim 4 (depends on 1) The component as recited in claim 1, wherein said pedestal is disposed at a leading edge region or a trailing edge region of said component. ### Claim 5 (depends on 1) The component as recited in claim 1, wherein said head includes a curved outer surface received within a trough formed on an interior surface of said outer wall. ### Claim 6 (depends on 1) The component as recited in claim 1, comprising a plurality of pedestals arranged in rows inside of said component, each of said plurality of pedestals traversing said flow channel. ### Claim 7 A gas turbine engine, comprising: an airfoil including a cooling circuit configured to cool said airfoil with a cooling fluid, said cooling circuit including: a flow channel disposed between an outer wall and an inner wall of said airfoil and a pedestal that extends from said outer wall to said inner wall across said flow channel between said outer wall and said inner wall, wherein said pedestal includes a hollow portion in fluid communication with said flow channel, wherein said pedestal includes a body and a head that extends transversely from said body, said head including at least one interior bore fluidly connecting said flow passage with said hollow portion, wherein said flow channel connects between a first cavity and a second cavity formed inside of said airfoil, and said at least one interior bore is configured to receive a cooling fluid from the flow channel and communicate said cooling fluid inside said pedestal through said hollow portion and into a third cavity opposite said flow channel from said inner wall. ### Claim 8 (depends on 7) The gas turbine engine as recited in claim 7, wherein said flow channel is a microcircuit. ### Claim 9 (depends on 7) The gas turbine engine as recited in claim 7, wherein said cooling circuit excludes film cooling holes. ### Claim 10 A method of cooling a gas turbine engine component, comprising: communicating a first cooling fluid in a first direction through a flow channel of a cooling circuit disposed within an airfoil of the gas turbine engine component, wherein the flow channel is disposed between an outer wall and an inner wall of said airfoil; cooling the first cooling fluid with a second cooling fluid that is communicated in a second direction generally perpendicular to the first direction inside a pedestal that traverses across the flow channel from the outer wall to the inner wall, wherein the pedestal includes a head and a body that extends transversely from the head; extracting the second cooling fluid from the first cooling fluid inside of the flow channel through the head; communicating the second cooling fluid through the body in the second direction; and expelling in said second direction the second cooling fluid into an inner cavity formed within the inner wall of said airfoil. ### Claim 11 (depends on 10) The method as recited in claim 10, comprising: communicating the first cooling fluid within a first cavity of the cooling circuit; communicating the first cooling fluid across the pedestal within the flow channel; and expelling the first cooling fluid into a second cavity of the cooling circuit. ### Claim 12 (depends on 10) The method as recited in claim 10, wherein the gas turbine engine component is cast using a casting article that is manufactured layer-by-layer using an additive manufacturing process.