# US 10,502,062 B2 · Integrally bladed rotor having axial arm and pocket

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- Number: US 10,502,062 B2
- Document ID: US10502062B2
- Status: Granted
- Kind: B2
- Application number: 14/919,073
- Filed: 2015-10-21
- Published: 2016-07-14
- Granted: 2019-12-10
- Earliest claimed: 2014-10-23
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Matthew P. Forcier
- Web page: https://patentgrep.com/patent/US10502062B2

## CPC

- 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 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28})
- F01D 5/06: Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections {(F01D5/022, F01D5/023 take precedence)}
- F01D 5/063: {Welded rotors (welding per se B23K)}
- F01D 5/08: Heating, heat-insulating or cooling means {(specially adapted for radial flow machines or engines F01D5/04)}
- F01D 5/3061: {by welding, brazing}
- F01D 5/34: Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)}
- F01D 25/08: Cooling (of machines or engines in general F01P); Heating; Heat-insulation (of blade-carrying members, of blades F01D5/00)
- F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16)
- F04D 29/053: Shafts
- F04D 29/321: {for axial flow compressors}
- F04D 29/322: {Blade mountings}
- F04D 29/324: {Blades}
- F05D 2220/36: specially adapted for the fan of turbofan engines
- F05D 2230/53: by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
- F05D 2240/20: Rotors
- F05D 2240/24: for turbines
- F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- 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)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- 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

An integrally bladed rotor includes a monolithic rotor body that has a bore portion, a rim, and a web that joins the bore portion and the rim. A plurality of blades extends outwardly from the rim. An arm that extends axially off of the rim, and there is a pocket on a radially inner side of the arm.

## Claims

### Claim 1

An integrally bladed rotor comprising:
a monolithic rotor body that includes a bore portion, a rim, a web joining the bore portion and the rim, a plurality of blades that extend outwardly from the rim, an arm that extends axially off of the rim, the arm having a first portion and a second frustoconical portion, and a pocket on a radially inner side of the arm, wherein a radially most outward surface of the rim is configured to bound a fluid flowpath at one or more of the blades, and wherein a first end of the second frustoconical portion is directly connected to the first portion and a second end of the second frustoconical portion is directly connected to a forward edge of the most radially outward surface.

### Claim 2 (depends on 1)

The integrally bladed rotor as recited in claim 1, wherein the pocket is formed by the arm, the rim, and the web.

### Claim 3 (depends on 1)

The integrally bladed rotor as recited in claim 1, wherein the pocket has a flat side.

### Claim 4 (depends on 1)

The integrally bladed rotor as recited in claim 1, where the pocket has a curved side.

### Claim 5 (depends on 1)

The integrally bladed rotor as recited in claim 1, wherein the first portion is cylindrical.

### Claim 6

A gas turbine engine comprising:
a compressor section;
a combustor section in communication with the compressor section; and
a turbine section in communication with the combustor section,
wherein the compressor section has an integrally bladed rotor that includes:
a monolithic rotor body that includes a bore portion, a rim, a web joining the bore portion and the rim, a plurality of blades that extend outwardly from the rim, an arm that extends axially off of the rim, the arm having a first portion and a second frustoconical portion, and a pocket on a radially inner side of the arm, wherein a radially most outward surface of the rim bounds a flowpath of fluid through the compressor section at one or more of the blades, and wherein a first end of the second frustoconical portion is directly connected to the first portion and a second end of the second frustoconical portion is directly connected to a forward edge of the most radially outward surface.

### Claim 7 (depends on 6)

The gas turbine engine as recited in claim 6, wherein the pocket is formed by the arm, the rim, and the web.

### Claim 8 (depends on 6)

The gas turbine engine as recited in claim 6, wherein the pocket has a flat side.

### Claim 9 (depends on 6)

The gas turbine engine as recited in claim 6, wherein the pocket has a curved side.

### Claim 10 (depends on 6)

The gas turbine engine as recited in claim 6, wherein the first portion is cylindrical.

### Claim 11 (depends on 6)

The gas turbine engine as recited in claim 6, wherein the arm is generally parallel to a central axis of the gas turbine engine.

### Claim 12 (depends on 11)

The gas turbine engine as recited in claim 11, wherein the radial wall is generally perpendicular to the central axis of the gas turbine engine and to the arm.

### Claim 13 (depends on 6)

The gas turbine engine as recited in claim 6, wherein the at least one seal engages a shroud of a vane.

### Claim 14 (depends on 6)

The gas turbine engine as recited in claim 6, wherein the arm includes at least one seal.

### Claim 15 (depends on 14)

The gas turbine engine as recited in claim 14, wherein the at least one seal is a knife edge seal.

### Claim 16 (depends on 6)

The gas turbine engine as recited in claim 6, wherein a free end of the arm includes a radial wall.

### Claim 17

An integrally bladed rotor comprising:
a monolithic rotor body that includes a bore portion, a rim, a web joining the bore portion and the rim, a plurality of blades that extend outwardly from the rim, an arm that extends axially off of the rim, and a pocket on a radially inner side of the arm, wherein a radially most outward surface of the rim is configured to bound a fluid flow path at one or more blades, and wherein the arm includes a first portion and a second frustoconical portion joining the first portion to the rim, wherein the second frustoconical portion incudes a first end directly connected to the first portion of the arm and a second end directly connected to a forward edge of the most radially outward surface.

### Claim 18 (depends on 17)

The integrally bladed rotor of claim 17, wherein the first portion is cylindrical.

### Claim 19 (depends on 17)

The integrally bladed rotor of claim 17, wherein the first end of the first portion of the arm has a smaller radius than the second end of the first portion of the arm.