# US 11,078,844 B2 · Thermal gradient reducing device for gas 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 11,078,844 B2 - Document ID: US11078844B2 - Status: Granted - Kind: B2 - Application number: 16/197,835 - Filed: 2018-11-21 - Published: 2020-05-21 - Granted: 2021-08-03 - Earliest claimed: 2018-11-21 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Adam P. Generale; Bryan P. Dube - Web page: https://patentgrep.com/patent/US11078844B2 ## CPC - 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)} - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F01D 5/188: {with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall} - F01D 11/005: {Sealing means between non relatively rotating elements} - F01D 25/005: {Selecting particular materials} - F01D 5/189: {the insert having a tubular cross-section, e.g. airfoil shape} - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/55: Seals - F05D 2260/203: by transpiration cooling - F05D 2300/6033: Ceramic matrix composites [CMC] - 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) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - 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 An internally cooled component for a gas turbine engine includes a component having one or more exterior walls defining an internal component cavity configured for a cooling airflow to flow therethrough. An internal component rib extends into the internal component cavity from the one or more exterior walls. An insert is positioned in the internal component cavity, and a flow discourager is positioned at the insert and is configured to prevent the cooling airflow from flowing past the internal component rib. ## Claims ### Claim 1 An internally cooled component for a gas turbine engine, comprising: a component having two or more exterior walls defining an internal component cavity configured for a cooling airflow to flow therethrough; an internal component rib extending into the internal component cavity from the two or more exterior walls; an insert positioned in the internal component cavity, the cooling airflow directed to flow between the insert and the two or more exterior walls; and two or more flow discouragers positioned at the insert configured to prevent the cooling airflow from flowing out of the component cavity between the insert and the two or more exterior walls, and past the internal component rib, wherein a flow discourager of the two or more flow discouragers is retained between an exterior wall of the two or more exterior walls and the insert such that the flow discourager is maintained in contact with the exterior wall and does not contact the internal component rib. ### Claim 2 (depends on 1) The internally cooled component of claim 1, wherein a flow discourager of the two or more flow discouragers is retained in an insert pocket of the insert. ### Claim 3 (depends on 2) The internally cooled component of claim 2, wherein the insert pocket includes one or more tabs to retain the flow discourager of the two or more flow discouragers at the insert pocket. ### Claim 4 (depends on 1) The internally cooled component of claim 1, wherein a flow discourager of the two or more flow discouragers is formed integral to the insert. ### Claim 5 (depends on 1) The internally cooled component of claim 1, wherein a flow discourager of the two or more flow discouragers is one of a rope seal or a fabric seal. ### Claim 6 (depends on 1) The internally cooled component of claim 1, wherein the insert urges the flow discourager of the two or more flow discouragers into contact with the exterior wall. ### Claim 7 (depends on 1) The internally cooled component of claim 1, wherein the insert is hollow. ### Claim 8 A turbine vane assembly, comprising: a stator vane, including: a pressure side extending from the leading edge to the trailing edge; and a suction side extending from the leading edge to the trailing edge, the pressure side and the suction side together defining an internal vane cavity therebetween, the internal vane cavity configured for a cooling airflow to flow therethrough; an internal vane rib extending into the internal vane cavity from one or more of the pressure side or the suction side; an insert positioned in the internal component cavity, the cooling airflow directed to flow between the insert and the one or more exterior walls; and two or more flow discouragers positioned at the insert configured to prevent the cooling airflow from flowing out of the component cavity between the insert and the one or more of the pressure side or the suction side, and past the internal component rib, wherein a flow discourager of the two or more flow discouragers is retained between one of the pressure side or the suction side and the insert such that the flow discourager is maintained in contact with the one of the pressure side or the suction side and does not contact the internal component rib. ### Claim 9 (depends on 8) The turbine vane assembly of claim 8, wherein a flow discourager of the two or more flow discouragers is retained in an insert pocket of the insert. ### Claim 10 (depends on 9) The turbine vane assembly of claim 9, wherein the insert pocket includes one or more tabs to retain the flow discourager of the two or more flow discouragers at the insert pocket. ### Claim 11 (depends on 8) The turbine vane assembly of claim 8, wherein the vane insert urges the flow discourager of the two or more flow discouragers into contact with the one of the pressure side or the suction side. ### Claim 12 (depends on 8) The turbine vane assembly of claim 8, wherein the insert is hollow. ### Claim 13 (depends on 8) The turbine vane assembly of claim 8, wherein a flow discourager of the two or more flow discouragers is one of a rope seal or a fabric seal. ### Claim 14 (depends on 8) The turbine vane assembly of claim 8, wherein a flow discourager of the two or more flow discouragers is formed from a metallic material or a ceramic material. ### Claim 15 (depends on 8) The turbine vane assembly of claim 8, wherein the a flow discourager of the two or more flow discouragers is formed integral to the insert. ### Claim 16 (depends on 8) The turbine vane assembly of claim 8, further comprising a cover plate disposed at the turbine vane to redirect the cooling airflow through the turbine vane. ### Claim 17 A gas turbine engine, comprising: a combustor; and one or more internally cooled components in flow communication with the combustor including: a component having two or more exterior walls defining an internal component cavity configured for a cooling airflow to flow therethrough; an internal component rib extending into the internal component cavity from the two or more exterior walls; an insert positioned in the internal component cavity, the cooling airflow directed to flow between the insert and the one two or more exterior walls; and two or more flow discouragers positioned at the insert configured to prevent the cooling airflow from flowing out of the component cavity between the insert and the two or more exterior walls, and past the internal component rib, wherein a flow discourager of the two or more flow discouragers is retained between an exterior wall of the two or more exterior walls and the insert such that the flow discourager is maintained in contact with the exterior wall and does not contact the internal component rib. ### Claim 18 (depends on 17) The gas turbine engine of claim 17, wherein a flow discourager of the two or more flow discouragers is retained in an insert pocket of the insert and the insert pocket includes one or more tabs to retain a flow discourager of the two or more flow discouragers at the insert pocket.