High pressure rotor disk

Patent metadata

Field	Value
Publication number	US-10119400-B2
Application number	US-201213713257-A
Country	US
Kind code	B2
Filing date	Dec 13, 2012
Priority date	Sep 28, 2012
Publication date	Nov 6, 2018
Grant date	Nov 6, 2018

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.

First claim

What is claimed is:

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.

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

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

4. 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.

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

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

7. 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.

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

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

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.

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

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

13. 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.

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

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

16. 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.

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

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

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).

20. 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.

21. 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.

Assignees

• United Technologies Corp

Inventors

• Virkler Scott D

Classifications

• F05D2240/24

  for turbines · CPC title

• F01D5/02 Primary

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F01D5/3007 Primary

  of axial insertion type · CPC title

• Y10T29/49321

  Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member · CPC title

• F05D2200/00

  Mathematical features · CPC title