Disk lug cooling flow trenches

Patent metadata

Field	Value
Publication number	US-2016348510-A1
Application number	US-201514727194-A
Country	US
Kind code	A1
Filing date	Jun 1, 2015
Priority date	Jun 1, 2015
Publication date	Dec 1, 2016
Grant date	—

Abstract

A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.

First claim

What is claimed is:

1 . A rotor disk, comprising:
a disk lug fixed to a distal surface of the rotor disk; and a trench disposed on a surface of the disk lug and extending radially inward from a distal surface of the disk lug, wherein the trench is configured to at least partially define a flow path by which air may reach a distal surface of the disk lug.

2 . The rotor disk of claim 1 , wherein the trench is located on a forward side of the rotor disk.

3 . The rotor disk of claim 1 , wherein the disk lug is configured to couple the rotor disk to a blade platform.

4 . The rotor disk of claim 1 , wherein the rotor disk is a high pressure turbine rotor disk.

5 . The rotor disk of claim 1 , wherein a width of the trench is less than a maximum width of the disk lug.

6 . The rotor disk of claim 1 , wherein a length of the trench is less than a length of the disk lug.

7 . The rotor disk of claim 1 , wherein the trench is manufactured via at least one of an additive process, a subtractive process, or an electrical discharge machining process.

8 . The rotor disk of claim 1 , wherein the rotor disk comprises a nickel based alloy.

9 . A rotor disk assembly, comprising:
a rotor disk, comprising:
a disk lug fixed to a distal surface of the rotor disk; and
a trench disposed on a surface of the disk lug and extending radially inwards from a distal surface of the disk lug, wherein the trench is configured to at least partially define a flow path by which air may reach a distal surface of the disk lug;
a retainer plate, wherein the flow path is partially defined by at least a portion of an aft surface of the retainer plate; a cover plate coupled to the rotor disk, wherein the flow path is partially defined by at least a portion of an aft surface of the cover plate; a blade platform coupled to the cover plate via the retainer plate; and a shield plate coupled between the distal surface of the disk lug and a proximal surface of the blade platform, wherein the flow path is partially defined by the distal surface of the disk lug and the proximal surface of the blade platform.

10 . The rotor disk assembly of claim 9 , wherein the trench is located on a forward side of the rotor disk.

11 . The rotor disk assembly of claim 9 , wherein the disk lug is configured to couple the rotor disk to the blade platform.

12 . The rotor disk assembly of claim 9 , wherein the rotor disk assembly is a high pressure turbine rotor disk assembly.

13 . The rotor disk assembly of claim 9 , wherein the air is cooling air, wherein the flow path is configured to provide cooling to the disk lug.

14 . The rotor disk assembly of claim 9 , wherein the cover plate comprises an aperture through which air may enter the rotor disk assembly.

15 . The rotor disk assembly of claim 9 , wherein a length of the trench is less than a length of the disk lug.

16 . The rotor disk assembly of claim 9 , wherein a width of the trench is less than a maximum width of the disk lug.

17 . The rotor disk assembly of claim 9 , wherein the rotor disk comprises a nickel based alloy.

18 . The rotor disk assembly of claim 9 , wherein the trench is manufactured via at least one of an additive process, a subtractive process, or an electrical discharge machining process.

19 . A gas turbine engine, comprising:
a rotor disk assembly, comprising:
a rotor disk, comprising:
a disk lug fixed to a distal surface of the rotor disk; and
a trench disposed on a surface of the disk lug and extending radially inwards from a distal surface of the disk lug, wherein the trench is configured to at least partially define a flow path by which air may reach a distal surface of the disk lug.

20 . The gas turbine engine of claim 19 , wherein the trench is located on a forward side of the rotor disk.

Assignees

• United Technologies Corp

Inventors

• Griffin David Richard
• Mott Zachary
• Corcoran Christopher
• Wilson Ross
• Himes Jason D

Classifications

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D5/082 Primary

  on the side of the rotor disc · CPC title

• F05D2300/177

  Ni - Si alloys · CPC title

• F05D2230/12

  by spark erosion methods · CPC title

• F05D2220/32

  in gas turbines · CPC title