# US 2019/0316475 A1 · Platform cooling core for a gas turbine engine rotor blade > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0316475 A1 - Document ID: US20190316475A1 - Status: Published application - Kind: A1 - Application number: 16/427,870 - Filed: 2019-05-31 - Published: 2019-10-17 - Earliest claimed: 2013-09-17 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Matthew Andrew Hough; Jeffrey S. Beattie - Web page: https://patentgrep.com/patent/US20190316475A1 ## CPC - F01D 5/187: {Convection cooling} - F05D 2240/81: Cooled platforms - F05D 2260/201: by impingement of a fluid - F05D 2260/202: by film cooling - F05D 2260/2212: by creating turbulence - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends radially from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform, a first cooling hole that extends circumferentially between a mate face of the platform and the second cooling core, a second cooling hole that extends between a gas path surface of the platform and the second cooling core, the second cooling core radially disposed between the gas path surface and a non-gas path surface, and the second cooling core circumferentially disposed between the first cooling core and the mate face. A method of cooling a blade is also disclosed. ## Claims ### Claim 1 A rotor blade, comprising: a platform; an airfoil that extends radially from said platform; a first cooling core that extends at least partially inside said airfoil; a second cooling core inside of said platform, wherein said second cooling core is fed with a cooling fluid from said first cooling core; a first cooling hole that extends circumferentially between a mate face of said platform and said second cooling core; a second cooling hole that extends between a gas path surface of said platform and said second cooling core; and wherein said second cooling core is radially disposed between said gas path surface and a non-gas path surface, and said second cooling core is circumferentially disposed between said first cooling core and said mate face. ### Claim 2 (depends on 1) The rotor blade as recited in claim 1, comprising a passage that fluidly connects said second cooling core with said first cooling core. ### Claim 3 (depends on 1) The rotor blade as recited in claim 1, comprising at least one augmentation feature formed inside said second cooling core. ### Claim 4 (depends on 3) The rotor blade as recited in claim 3, wherein said at least one augmentation feature includes a plurality of augmentation features circumferentially distributed along a wall of said second cooling core. ### Claim 5 (depends on 4) The rotor blade as recited in claim 4, wherein said plurality of augmentation features are arranged such that the cooling fluid circulates over said plurality of augmentation features prior to being expelled through said first and second cooling holes. ### Claim 6 (depends on 1) The rotor blade as recited in claim 1, wherein said first cooling core is a main body cooling core and said second cooling core is a platform cooling core. ### Claim 7 (depends on 1) The rotor blade as recited in claim 1, wherein said second cooling core is formed near a trailing edge of said platform on either a suction side or a pressure side of said airfoil. ### Claim 8 (depends on 1) The rotor blade as recited in claim 1, wherein said second cooling core is formed near a leading edge of said platform on either a suction side or a pressure side of said airfoil. ### Claim 9 (depends on 1) The rotor blade as recited in claim 1, wherein said first cooling hole is a plurality of cooling holes including respective outlets distributed along said mate face. ### Claim 10 (depends on 1) The rotor blade as recited in claim 1, comprising a root that extends radially inward from said platform, wherein said airfoil extends radially outward from said platform, and said first cooling core extends at least partially inside said root. ### Claim 11 A gas turbine engine, comprising: a compressor section; a turbine section downstream from said compressor section; a rotor blade positioned within at least one of said compressor section and said turbine section, said rotor blade including: a platform; an airfoil that extends radially from said platform; a main body cooling core that extends inside said airfoil; a platform cooling core inside of said platform; a first cooling hole that extends between a mate face of said platform and said platform cooling core; a second cooling hole that extends between a gas path surface of said platform and said platform cooling core; and wherein said platform cooling core is fed with a cooling fluid from said main body cooling core. ### Claim 12 (depends on 11) The gas turbine engine as recited in claim 11, wherein said first cooling hole is a plurality of cooling holes including respective outlets distributed along said mate face. ### Claim 13 (depends on 11) The gas turbine engine as recited in claim 11, comprising a plurality of augmentation features circumferentially distributed along a radially extending wall of said platform cooling core, each one of the plurality of augmentation features extending radially between opposed walls of said platform cooling core. ### Claim 14 (depends on 13) The gas turbine engine as recited in claim 13, comprising a passage that fluidly connects said platform cooling core with said main body cooling core. ### Claim 15 (depends on 13) The gas turbine engine as recited in claim 13, wherein said plurality of augmentation features are arranged such that the cooling fluid circulates over said plurality of augmentation features prior to being expelled through said first and second cooling holes. ### Claim 16 (depends on 11) The gas turbine engine as recited in claim 11, wherein said platform cooling core is formed on a suction side of said airfoil. ### Claim 17 (depends on 11) The gas turbine engine as recited in claim 11, wherein said platform cooling core is formed on a pressure side of said airfoil. ### Claim 18 A method of cooling a rotor blade of a gas turbine engine, comprising the steps of: communicating a cooling fluid into a platform cooling core of a platform of a rotor blade, including feeding the cooling fluid to the platform cooling core from a main body cooling core; expelling a first portion of the cooling fluid through a first cooling hole that extends through a mate face of the platform; and expelling a second portion of the cooling fluid through a second cooling hole that extends through a gas path surface of the platform. ### Claim 19 (depends on 18) The method as recited in claim 18, comprising depositing a film cooling layer at the mate face to discourage gas ingestion into a mate face gap, the mate face gap defined between the mate face and another mate face of an adjacent rotor blade. ### Claim 20 (depends on 18) The method as recited in claim 18, wherein the first cooling hole is a plurality of cooling holes including respective outlets distributed along the mate face.