# US 10,502,092 B2 · Internally cooled turbine platform > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,502,092 B2 - Document ID: US10502092B2 - Status: Granted - Kind: B2 - Application number: 14/945,556 - Filed: 2015-11-19 - Published: 2016-05-26 - Granted: 2019-12-10 - Earliest claimed: 2014-11-20 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Russell J. Bergman - Web page: https://patentgrep.com/patent/US10502092B2 ## CPC - F01D 25/12: Cooling - F01D 9/04: forming ring or sector - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 25/246: {Fastening of diaphragms or stator-rings} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F05D 2220/32: in gas turbines - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/24: for turbines - F05D 2240/35: Combustors or associated equipment - F05D 2240/55: Seals - F05D 2260/201: by impingement of a fluid - 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 A turbine flowpath component for a gas turbine engine includes a platform defining at least one internal cooling cavity and a turbine flowpath component cover disposed radially outward of the platform. The turbine flowpath component cover defines a radially outward edge of the at least one internal cooling cavity. The turbine flowpath component cover further defines a transition region in which a radial depth of the at least one internal cooling cavity varies from a first depth to a second depth. ## Claims ### Claim 1 A turbine flowpath component for a gas turbine engine comprising: a platform defining at least one internal cooling cavity; a turbine flowpath component cover disposed radially outward of said platform, wherein the turbine flowpath component cover defines a radially outward edge of said at least one internal cooling cavity; wherein the turbine flowpath component cover defines a transition region in which a radial depth of the at least one internal cooling cavity varies from a first depth to a second depth, and a first region having a first radial depth on a first side of the transition region and a second region having a second radial depth on a second side of the transition region, and wherein the transition region transitions from the first depth to the second depth, said first region being an upstream edge of said at least one internal cooling cavity relative to a fluid flow through a gas turbine engine, and said second region is a downstream edge of said at least one internal cooling cavity relative to the fluid flow through the gas turbine engine; and wherein the first depth is a radial distance between the platform and the turbine flowpath component cover at an upstream edge of the at least one internal cooling cavity and wherein the second depth is a radial distance between the platform and the turbine flowpath component cover at a downstream edge of the at least one internal cooling cavity, and wherein the first radial depth is greater than the second radial depth; and wherein the turbine flowpath component cover maintains a constant angle relative to the platform through the transition region. ### Claim 2 (depends on 1) The turbine flowpath component of claim 1, where the at least one internal cooling cavity includes at least one serpentine cooling passage, and wherein the turbine flowpath component cover further includes at least one inlet for receiving cooling air into said at least one serpentine cooling passage. ### Claim 3 (depends on 1) The turbine flowpath component of claim 1, wherein the at least one internal cooling cavity includes at least one impingement cavity. ### Claim 4 (depends on 3) The turbine flowpath component of claim 3, wherein said turbine flowpath component cover includes a plurality of impingement holes disposed radially outward of the at least one impingement cavity, and wherein each of said impingement holes allows cooling fluid to pass through said flowpath component cover. ### Claim 5 (depends on 1) The turbine flowpath component of claim 1, wherein the at least one internal cooling cavity includes at least one serpentine cooling passage and at least one impingement cavity. ### Claim 6 (depends on 1) The turbine flowpath component of claim 1, wherein the first radial depth is a first uniform radial depth, and the second radial depth is a second uniform radial depth. ### Claim 7 (depends on 6) The turbine flowpath component of claim 6, wherein the first uniform radial depth is approximately 0.100 inches (0.254 centimeters) and wherein the second uniform radial depth is approximately 0.080 inches (0.203 centimeters). ### Claim 8 (depends on 6) The turbine flowpath component of claim 6, wherein an angle of said transition region is at least partially aligned with a direction of fluid flow through the gas turbine engine including the turbine flowpath component. ### Claim 9 (depends on 6) The turbine flowpath component of claim 6, wherein an angle of said transition region is at least partially aligned with a direction of fluid flow through a serpentine passage. ### Claim 10 (depends on 1) The turbine flowpath component of claim 1, further comprising a plurality of said platforms arranged in a hoop configuration, each of said platforms including at least one connection feature operable to connect the corresponding platform to an engine static structure. ### Claim 11 (depends on 1) The turbine flowpath component of claim 1, wherein the turbine flowpath component is a vane. ### Claim 12 A gas turbine engine comprising: a primary flowpath defined within, and fluidly connecting, a compressor section, a combustor section, and a turbine section; said turbine section including a plurality of stages; at least one of said stages including at least one turbine flowpath component further comprising: a platform defining at least one internal cooling cavity; a turbine flowpath component cover disposed radially outward of said platform, wherein the turbine flowpath component cover defines a radially outward edge of said at least one internal cooling cavity; and wherein the turbine flowpath component cover further defines a transition region in which a radial depth of the at least one internal cooling cavity varies from a first depth to a second depth, and a first region having a first radial depth on a first side of the transition region and a second region having a second radial depth on a second side of the transition region, and wherein the transition region transitions from the first radial depth to the second radial depth, said first region being an upstream edge of said at least one internal cooling cavity relative to a fluid flow through a gas turbine engine, and said second region is a downstream edge of said at least one internal cooling cavity relative to the fluid flow through the gas turbine engine; and wherein the first radial depth is a radial distance between the platform and the turbine flowpath component cover at an upstream edge of the at least one internal cooling cavity and wherein the second radial depth is a radial distance between the platform and the turbine flowpath component cover at a downstream edge of the at least one internal cooling cavity, and wherein the first radial depth is greater than the second radial depth; and wherein the turbine flowpath component cover maintains a constant angle relative to the platform through the transition region. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, wherein the at least one internal cooling cavity includes at least one serpentine cooling passage and at least one impingement cavity. ### Claim 14 (depends on 13) The gas turbine engine of claim 13, wherein said turbine flowpath component cover includes a plurality of impingement holes disposed radially outward of the at least one impingement cavity, and wherein each of said impingement holes allows cooling fluid to pass through said turbine flowpath component cover. ### Claim 15 (depends on 12) The gas turbine engine of claim 12, wherein the first radial depth is a first uniform radial depth and the second radial depth is a second uniform radial depth. ### Claim 16 (depends on 15) The gas turbine engine of claim 15, wherein the first uniform radial depth is approximately 0.100 inches (0.254 centimeters) and wherein the second uniform radial depth is approximately 0.080 inches (0.203 centimeters).