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US 9,790,792 B2Granted
Asymmetrically slotted rotor for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsGabriel L. Suciu, Stephen P. Muron, Christopher M. Dye, Ioannis Alvanos, Brian D. Merry
Life of this patent
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Abstract
A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path.
Claims14
A spool for a gas turbine engine comprising:
- at least one rotor disk defined along an axis of rotation;
- a plurality of blades which extend from said rotor disk, each blade of said plurality of blades extends from said rotor disk at an interface, said interface defined along a spoke;
- at least one rotor ring defined along said axis of rotation, said rotor ring in contact with said rotor disk, said rotor disk and said rotor ring contoured to be axially asymmetric to define a smooth rotor stack load path;
- a plurality of core gas path seals which extend from said rotor ring, each seal of said plurality of core gas path seals extends from said rotor ring at an interface, said interface defined along a ring spoke;
- and
- wherein said rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, said first thickness different than said second thickness.
3 more elements
A method of orienting a rotor stack load path for a spool comprising:
- stacking a rotor ring in contact with a rotor disk along an axis of rotation, the rotor disk and the rotor ring axially asymmetric to define a smooth rotor stack load path;
- providing a plurality of core gas path seals which extend from said rotor ring, each seal of said plurality of core gas path seals extends from said rotor ring at an interface, said interface defined along a ring spoke;
- and
- wherein asymmetry extends in an axial direction along the axis of rotation, and wherein the asymmetry is defined at least within the rotor ring which includes a forward circumferential flange having a first thickness and an aft circumferential flange having a second thickness different than the first thickness, and with a ramped interface extending between the forward circumferential flange and an aft circumferential flange.
1 more element
A rotor for a gas turbine engine comprising:
- a rotor disk defined along an axis of rotation, said rotor disk comprising a rotor hub, a rotor rim, and a web which extends between the rotor hub and the rotor rim, and wherein the rotor rim is axially asymmetric;
- at least one rotor ring defined along said axis of rotation, said rotor ring in contact with said rotor disk, said rotor disk and said rotor ring contoured to be axially asymmetric to define a smooth rotor stack load path;
- a plurality of core gas path seals which extend from said rotor ring, each seal of said plurality of core gas path seals extends from said rotor ring at an interface, said interface defined along a ring spoke;
- a plurality of blades which extend from said rotor disk, wherein each blade includes an attachment section, a platform section, and an airfoil section extending from said platform section, and wherein each blade of said plurality of blades extends from said rotor disk at an interface, said interface defined along a spoke, wherein the spoke is defined between the rotor rim and the attachment section;
- and
- wherein said rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, said first thickness different than said second thickness, and with a ramped interface extending between the forward circumferential flange and the aft circumferential flange.
3 more elements
Dependencies are inferred from the claim text.