# US 10,502,060 B2 · Rotor and gas turbine engine including same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,502,060 B2 - Document ID: US10502060B2 - Status: Granted - Kind: B2 - Application number: 14/742,162 - Filed: 2015-06-17 - Published: 2015-12-24 - Granted: 2019-12-10 - Earliest claimed: 2014-06-18 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Michael G. McCaffrey - Web page: https://patentgrep.com/patent/US10502060B2 ## CPC - F01D 5/082: {on the side of the rotor disc} - F01D 5/12: Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) - F04D 29/321: {for axial flow compressors} - F04D 29/584: {cooling or heating the machine (F04D29/5846, F04D29/5853 take precedence)} - F05D 2220/32: in gas turbines - F05D 2250/12: rectangular - F05D 2250/13: trapezoidal - F05D 2250/71: curved - F05D 2260/20: Heat transfer, e.g. cooling - F05D 2260/2212: by creating turbulence - 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) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - 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 rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk. One or more cooling features may be incorporated radially inboard from the rotor disk rim that operate to induce vortices adjacent to the disk rim and/or disk web. The vortices increase the local velocity in the secondary cooling air flow path and therefore increase the heat transfer rate from the rotor to the secondary cooling air flow path. ## Claims ### Claim 1 A rotor for a gas turbine engine, the rotor comprising: a disk including a rim having a radially outer rim surface and a radially inner rim surface, and a radially extending web connected to the rim at a junction; first and second cooling features configured to cool the disk and disposed on opposite sides of the web and the first and second cooling features directly extend from at least one of the rim, the web, and the junction in opposite directions, wherein each of the cooling features comprises a circumferentially extending ring and at least one of the cooling features extends from the radially inner rim surface or the junction and includes a feature longitudinal axis that includes curvature; and a seal support member that is a circumferentially extending ring that abuts the rim, the seal support member having a seal assembly that includes a cooling fin. ### Claim 2 (depends on 1) The rotor of claim 1, further comprising: a plurality of blades which extend from the radially outer rim surface. ### Claim 3 (depends on 1) The rotor of claim 1, wherein at least one of the cooling features is configured to increase a velocity of air adjacent the rotor when the rotor is rotating. ### Claim 4 (depends on 1) The rotor of claim 1, wherein the circumferentially extending ring comprises a plurality of sections combined to form a ring. ### Claim 5 (depends on 1) The rotor of claim 1, wherein: the rotor includes an axis of rotation; and wherein the feature longitudinal axis is perpendicular to the axis of rotation. ### Claim 6 (depends on 1) The rotor of claim 1, wherein: the rotor includes an axis of rotation; and wherein the feature longitudinal axis is disposed at an angle to the axis of rotation. ### Claim 7 (depends on 1) The rotor of claim 1, wherein: at least one of the cooling features comprises an axially upstream feature side and an axially downstream feature side; and the axially upstream feature side and the axially downstream feature side of at least one of the cooling features are parallel. ### Claim 8 (depends on 1) The rotor of claim 1, wherein: wherein at least one of the cooling features comprises an axially upstream feature side and an axially downstream feature side; and the axially upstream feature side and the axially downstream feature side of at least one of the cooling features taper. ### Claim 9 (depends on 8) The rotor of claim 8, wherein said at least one of the cooling features tapers with multiple radii of curvature. ### Claim 10 (depends on 1) The rotor of claim 1, wherein at least one of the cooling features includes a radius of curvature that is constant along an axis of at least one of the cooling features. ### Claim 11 (depends on 1) The rotor of claim 1, wherein at least one of the cooling features comprises a thickness that is constant. ### Claim 12 (depends on 1) The rotor of claim 1, wherein at least one of the cooling features comprises a thickness that varies in steps. ### Claim 13 A spool for a gas turbine engine comprising: a compressor rotor disk including a rim having a radially outer rim surface and a radially inner rim surface, and a radially extending web connected to the rim at a junction; a first cooling feature configured to cool the compressor rotor disk, the first cooling feature directly extending from at least one of the rim, the web, and the junction in a first direction and disposed proximate a first side of the web; and a second cooling feature configured to cool the compressor rotor disk, the first cooling feature directly extending from at least one of the rim, the web, and the junction in a second direction that is disposed opposite the first direction and is disposed proximate a second side of the web; wherein at least one of the first and second cooling features is configured to increase a velocity of air adjacent the rotor when the rotor is rotating, and wherein each of the cooling features comprises a circumferentially extending ring and at least one of the cooling features extends from the radially inner rim surface or the junction and includes a feature longitudinal axis that includes curvature. ### Claim 14 (depends on 13) The spool of claim 13, wherein: the rotor includes an axis of rotation; and the feature longitudinal axis that is perpendicular to the axis of rotation. ### Claim 15 (depends on 13) The spool of claim 13, wherein: the rotor includes an axis of rotation; and the feature longitudinal axis that is disposed at an angle to the axis of rotation. ### Claim 16 (depends on 13) The spool of claim 13, wherein: wherein at least one of the first and second cooling features comprises an axially upstream feature side and an axially downstream feature side; and the axially upstream feature side and the axially downstream feature side of at least one of the first and second cooling features taper. ### Claim 17 (depends on 13) The spool of claim 13, wherein at least one of the first and second cooling features includes a radius of curvature that increases along an axis of the at least one of the first and second cooling feature. ### Claim 18 (depends on 13) The spool of claim 13, wherein at least one of the first and second cooling features comprises a thickness that is constant.