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US 10,502,060 B2Granted
Rotor and gas turbine engine including same
AssigneeUnited Technologies Corporation
InventorMichael G. McCaffrey
Life of this patent
Estimating the term…
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.
Claims18
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.
1 more element
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.
3 more elements
Dependencies are inferred from the claim text.