Cross key anti-rotation spacer

Patent metadata

Field	Value
Publication number	US-10669875-B2
Application number	US-201815939070-A
Country	US
Kind code	B2
Filing date	Mar 28, 2018
Priority date	Mar 28, 2018
Publication date	Jun 2, 2020
Grant date	Jun 2, 2020

Abstract

This disclosure provides a cross key anti rotation spacer for use in a gas turbine engine. A compressor disk assembly can have a cross key ring having a plurality of keys, teeth, or castellations, alternating with a plurality of gaps to form a cross key surface. The keys or teeth of the cross key surface can mesh with corresponding teeth formed on a spacer of a compressor rotor assembly. The spacer teeth, in connection with the teeth or keys of the cross key ring can prevent rotation between the spacer and compressor disk. This is particularly beneficial during transient operations, such as startup and shutdown of the gas turbine engine.

First claim

What is claimed is:

1. A compressor disk assembly comprising:
a cross key ring having,
an annular body having a circumference defined by an outer surface, and a ring aft face orthogonal to the outer surface, and
a plurality of keys alternating with a plurality of gaps forming a cross key surface opposite the ring aft face, each key of the plurality of keys spanning an annular sector of the cross key surface; and

a compressor disk configured to receive a plurality of compressor blades about an outer circumference, the compressor disk having,
a rim extending from an outer portion of the compressor disk defining the outer circumference of the compressor disk,
a forward disk face disposed radially inward from the rim' and
a forward extension extending axially forward from the rim and defining an extension depth, the extension depth extending from the forward disk face to a forward extension face along a forward extension inner surface, the forward extension being configured to receive the cross key ring in an interference fit with the forward extension inner surface, such that the ring aft face is disposed adjacent to the forward disk face, and the outer surface adjacent to the forward extension inner surface.

2. The compressor disk assembly of claim 1 , wherein one or more of the plurality of keys comprises a key aperture extending from a key face of the one or more keys of the plurality of keys to a ring aft face, each key aperture corresponding with a disk aperture formed in the compressor disk, wherein each key aperture and corresponding disk aperture are configured to coaxially receive a corresponding pin.

3. The compressor disk assembly of claim 1 , wherein the plurality of keys and alternating plurality of gaps are equally distributed about the cross key surface.

4. The compressor disk assembly of claim 1 , wherein the cross key ring comprises a ring depth defining a distance from the aft ring surface to a key face of each key of the plurality of keys.

5. The compressor disk assembly of claim 4 , wherein the ring depth is less than the extension depth of the forward extension.

6. A method for retrofitting a gas turbine engine, the method comprising:
forming a forward disk face on a compressor disk radially inward from a rim, the rim having an outer surface defining a disk outer surface of the compressor disk, the rim configured to receive a plurality of rotor blades about the disk outer surface;
forming a forward extension inner surface extending an extension depth from the forward disk face of the compressor disk to a forward extension face of a forward extension, the forward extension extending axially forward from the rim; and
fitting a cross key ring to the compressor disk, the cross key ring having a plurality of keys alternating with a plurality of gaps forming a cross key surface opposite a ring aft face, each key of the plurality of keys spanning an annular sector of the cross key surface, the fitting further disposing the ring aft face adjacent the forward disk face.

7. The method of claim 6 further comprising fitting an outer surface of a circumference of the cross key ring adjacent to the forward extension inner surface.

8. The method of claim 7 wherein the spacer further comprises a spacer body having a substantially annular shape and a spacer outer surface disposed flush with the disk outer surface.

9. The method of claim 6 further comprising fitting a spacer to the compressor disk, the spacer having a plurality of spacer teeth formed on an aft face of the spacer body, each spacer tooth of the plurality of spacer teeth spanning an annular sector of the ring aft face, the plurality spacer teeth engaging with the plurality of keys.

10. The method of claim 6 wherein the cross key ring comprises a ring depth extending a distance from the aft ring surface to a key face of the plurality of keys, the ring depth being less than the extension depth.

Assignees

• Solar Turbines Inc

Inventors

• Hernandez Jorge
• Jeorling David
• Sovani Makarand

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F05D2230/80

  Repairing, retrofitting or upgrading methods · CPC title

• F04D29/321

  for axial flow compressors · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title