# US 2014/0196433 A1 · Gas turbine engine component platform cooling > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0196433 A1 - Document ID: US20140196433A1 - Status: Published application - Kind: A1 - Application number: 13/653,633 - Filed: 2012-10-17 - Published: 2014-07-17 - Earliest claimed: 2012-10-17 - Assignees: United Technologies Corporation - Inventors: Eleanor D. Kaufman; Matthew A. Devore - Web page: https://patentgrep.com/patent/US20140196433A1 ## CPC - F01D 5/145: {Means for influencing boundary layers or secondary circulations (for compressors F04D29/68)} - F01D 5/187: {Convection cooling} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 25/12: Cooling - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F05D 2220/32: in gas turbines - F05D 2240/81: Cooled platforms - F05D 2260/2212: by creating turbulence - F05D 2260/2214: by increasing the heat transfer surface - F05D 2260/22141: using fins or ribs - 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 ## Abstract A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least one of the leading edge portion and the trailing edge portion of the outer surface of the platform. ## Claims ### Claim 1 A component for a gas turbine engine, comprising: a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion; and at least one augmentation feature disposed on at least one of said leading edge portion and said trailing edge portion of said outer surface of said platform. ### Claim 2 (depends on 1) The component as recited in claim 1, wherein said platform is an inner diameter platform. ### Claim 3 (depends on 1) The component as recited in claim 1, wherein the component is a turbine vane. ### Claim 4 (depends on 1) The component as recited in claim 1, wherein said outer surface is a non-gas path side of said platform and said inner surface is a gas path side of said platform. ### Claim 5 (depends on 1) The component as recited in claim 1, comprising an airfoil that extends from said inner surface of said platform. ### Claim 6 (depends on 1) The component as recited in claim 1, wherein said at least one augmentation feature includes a plurality of trip strips. ### Claim 7 (depends on 6) The component as recited in claim 6, wherein said plurality of trip strips are disposed at said trailing edge portion of said platform. ### Claim 8 (depends on 6) The component as recited in claim 6, wherein each of said plurality of trip strips are angled relative to opposing mate faces of said platform. ### Claim 9 (depends on 6) The component as recited in claim 6, wherein each of said plurality of trip strips include a first portion and a second portion that is transverse to the first portion. ### Claim 10 (depends on 9) The component as recited in claim 9, wherein said first portions are angled at a first angle relative to a mate face of said platform and said second portions are angled at a second angle different from said first angle relative to said mate face. ### Claim 11 (depends on 1) The component as recited in claim 1, wherein said at least one augmentation feature is disposed at said leading edge portion of said platform. ### Claim 12 (depends on 1) The component as recited in claim 1, wherein said at least one augmentation feature is disposed on a portion of said outer surface of said platform that axially overlaps a neighboring component of the gas turbine engine. ### Claim 13 A gas turbine engine, comprising: a compressor section; a combustor section in fluid communication with said compressor section; a turbine section in fluid communication with said combustor section; and wherein at least one of said compressor section and said turbine section includes: a first component having a platform that includes an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion; a second component mounted adjacent to said first component and including a platform; wherein a portion of said platform of said first component axially overlaps a portion of said platform of said second component, and said portion of said first platform includes at least one augmentation feature disposed on said outer surface of said platform. ### Claim 14 (depends on 13) The gas turbine engine as recited in claim 13, wherein said first component is a vane and said second component is a blade. ### Claim 15 (depends on 13) The gas turbine engine as recited in claim 13, wherein said at least one augmentation feature includes a plurality of trip strips. ### Claim 16 (depends on 13) The gas turbine engine as recited in claim 13, wherein said at least one augmentation feature is disposed on at least one of said leading edge portion and said trailing edge portion of said platform of said first component. ### Claim 17 (depends on 13) The gas turbine engine as recited in claim 13, wherein said at least one augmentation feature is angled relative to a mate face of said platform. ### Claim 18 A method of cooling a component of a gas turbine engine, comprising the steps of: cooling a platform of the component with a leakage airflow that is communicated from a cavity positioned radially inwardly from the component by circulating the leakage airflow over at least one augmentation feature that is disposed on an outer surface of the platform. ### Claim 19 (depends on 18) The method as recited in claim 18, wherein the leakage airflow is not a dedicated cooling airflow that is communicated inside of the component. ### Claim 20 (depends on 18) The method as recited in claim 18, wherein the at least one augmentation feature is disposed on a trailing edge portion of the platform.