# US 10,119,400 B2 · High pressure rotor disk

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- Number: US 10,119,400 B2
- Document ID: US10119400B2
- Status: Granted
- Kind: B2
- Application number: 13/713,257
- Filed: 2012-12-13
- Published: 2014-04-24
- Granted: 2018-11-06
- Earliest claimed: 2012-09-28
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Scott D. Virkler
- Web page: https://patentgrep.com/patent/US10119400B2

## 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 5/3007: {of axial insertion type}
- F05D 2200/00: Mathematical features
- F05D 2240/20: Rotors
- F05D 2240/24: for turbines
- Y10T 29/49321: Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
- 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 rotor disk for a gas turbine engine is disclosed and formed to enable operation at high rotational speeds in a high temperature environment. The rotor disk is formed to include a bore, a live rim diameter and an outer diameter related to each other according to defined relationships.

## Claims

### Claim 1

A gas turbine engine comprising:
a compressor section including a high pressure compressor and a low pressure compressor;
a combustor in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor, wherein the turbine section includes a high pressure turbine driving the high pressure compressor and a low pressure turbine driving the low pressure compressor, wherein at least one of the high pressure turbine and the high pressure compressor includes a disk having a bore diameter (D) related to a bore width (W) according to a ratio (D/W) between 1.25 and 1.65.

### Claim 2 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the ratio (DAY) is between 1.35 and 1.55.

### Claim 3 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the ratio (D/W) is 1.45.

### Claim 4 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the disk includes an outer diameter (OD) related to the bore diameter (D) according to a ratio (OD/D) that is between 2.95 and 3.25.

### Claim 5 (depends on 4)

The gas turbine engine as recited in claim 4, wherein the ratio (OD/D) is between 3.04 and 3.20.

### Claim 6 (depends on 4)

The gas turbine engine as recited in claim 4, wherein the ratio (OD/D) is 3.15.

### Claim 7 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the disk includes a live rim diameter (d) related to the bore diameter (D) according to a ratio (d/D) that is between 2.25 and 3.00.

### Claim 8 (depends on 7)

The gas turbine engine as recited in claim 7, wherein the ratio (d/D) is between 2.50 and 2.75.

### Claim 9 (depends on 7)

The gas turbine engine as recited in claim 7, wherein the ratio (d/D) is 2.69.

### Claim 10

A rotor disk for a gas turbine engine comprising:
an outer diameter (OD) related to a bore diameter (D) according to a ratio (OD/D) that is between 2.95 and 3.25.

### Claim 11 (depends on 10)

The rotor disk as recited in claim 10, wherein the ratio (OD/D) is between 3.04 and 3.20.

### Claim 12 (depends on 10)

The rotor disk as recited in claim 10, wherein the ratio (OD/D) is 3.15.

### Claim 13 (depends on 10)

The rotor disk as recited in claim 10, wherein the bore diameter (D) is related to a bore width (W) according to a ratio (D/W) between 1.25 and 1.65.

### Claim 14 (depends on 13)

The rotor disk as recited in claim 13, wherein the ratio (D/W) is between 1.53 and 1.55.

### Claim 15 (depends on 13)

The rotor disk as recited in claim 13, wherein the ratio (DAY) is 1.45.

### Claim 16 (depends on 10)

The rotor disk as recited in claim 10, wherein the disk includes a live rim diameter (d) related to the bore diameter (D) according to a ratio (d/D) that is between 2.25 and 3.00.

### Claim 17 (depends on 16)

The rotor disk as recited in claim 16, wherein the ratio (d/D) is between 2.50 and 2.75.

### Claim 18 (depends on 16)

The rotor disk as recited in claim 16, wherein the ratio (d/D) is 2.69.

### Claim 19

A method of fabricating a rotor disk for a gas turbine engine comprising;
forming a bore including a bore diameter (D) and a live rim diameter (d) with a ratio (d/D) of the live rim diameter (d) to the bore diameter (D) being between 2.25 and 3.00
forming at least one lug for mounting a blade at the live rim diameter (d); and
forming an outer diameter (OD).

### Claim 20 (depends on 19)

The method as recited in claim 19, including forming the disk to include a ratio (OD/D) of the outer diameter (OD) to the bore diameter (D) between 2.95 and 3.25.

### Claim 21 (depends on 19)

The method as recited in claim 19, including forming a bore including a bore diameter (D) and a bore width (W) in a direction parallel to an axis of intended rotation, wherein the bore diameter (D) is related to the bore width (W) according to a ratio (D/W) that is between 1.25 and 1.65.