# US 8,784,062 B2 · Asymmetrically slotted rotor for a gas turbine engine

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- Number: US 8,784,062 B2
- Document ID: US8784062B2
- Status: Granted
- Kind: B2
- Application number: 13/283,710
- Filed: 2011-10-28
- Published: 2013-05-02
- Granted: 2014-07-22
- Earliest claimed: 2011-10-28
- Assignees: United Technologies Corporation
- Applicants: Gabriel L. Suciu; Stephen P. Muron; Christopher M. Dye; Ioannis Alvanos; Brian D. Merry
- Inventors: Gabriel L. Suciu; Stephen P. Muron; Christopher M. Dye; Ioannis Alvanos; Brian D. Merry
- Web page: https://patentgrep.com/patent/US8784062B2

## CPC

- F01D 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28})
- F01D 5/027: {Arrangements for balancing (for balancing rotating bodies in general F16F15/32; for compensating imbalance G01M1/36)}
- F01D 5/022: {with concentric rows of axial blades}
- F01D 5/025: {Fixing blade carrying members on shafts (attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00)}
- F01D 5/066: {Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps}
- F01D 5/14: Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28)
- F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)}
- F01D 11/006: {Sealing the gap between rotor blades or blades and rotor}
- F05D 2240/20: Rotors
- F05D 2260/15: Load balancing
- Y10T 29/49316: Impeller making
- Y10T 29/4932: Turbomachine making
- 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
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## 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.

## Claims

### Claim 1

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.

### Claim 2 (depends on 1)

The spacer as recited in claim 1, wherein said interface includes a heat treat transition.

### Claim 3 (depends on 1)

The spacer as recited in claim 1, wherein said interface includes a bond.

### Claim 4 (depends on 1)

The spacer as recited in claim 1, wherein said rotor ring is manufactured of a first material and said plurality of core gas path seals are manufactured of a second material, said first material different than said second material.

### Claim 5 (depends on 1)

The spacer as recited in claim 1, wherein each spoke is parallel to said axis of rotation.

### Claim 6 (depends on 1)

The spacer as recited in claim 1, wherein each spoke is angled with respect to said axis of rotation.

### Claim 7 (depends on 1)

The spacer as recited in claim 1, wherein at least one of said plurality of core gas path seals includes an inlet.

### Claim 8 (depends on 7)

The spacer as recited in claim 7, wherein said inlet is to a passage adjacent to said spoke.

### Claim 9 (depends on 1)

The spacer as recited in claim 1, wherein said interface is a ramped interface between said forward circumferential flange and said aft circumferential flange.