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US 8,784,062 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 spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.
Claims9
A spacer for a gas turbine engine comprising:
- a rotor ring defined along an axis of rotation, 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
- a plurality of core gas path seals which extend from said rotor ring opposite an interface, each of said plurality of core gas path seals extend from said rotor ring at said interface, said interface defined along a spoke.
Dependencies are inferred from the claim text.