Twist prevention for turbomachinery

Patent metadata

Field	Value
Publication number	US-9790813-B2
Application number	US-201414201498-A
Country	US
Kind code	B2
Filing date	Mar 7, 2014
Priority date	Mar 7, 2013
Publication date	Oct 17, 2017
Grant date	Oct 17, 2017

Abstract

A twist prevention system for turbomachinery is disclosed. The twist prevention system has a first ring segment pair with a first radially inner ring segment and a first radially outer ring segment and a second ring segment pair having a second radially inner ring segment and a second radially outer ring segment. The ring segment pairs have mutually facing faces. A portion of the face of the first radially inner ring segment overlaps a portion of the face of the second radially outer ring segment in the radial direction.

First claim

What is claimed is:

1. A twist prevention system for a turbomachine, comprising:
a first ring segment pair with a first radially inner ring segment and a first radially outer ring segment; and
a second ring segment pair with a second radially inner ring segment and a second radially outer ring segment;
wherein the second ring segment pair is offset in a radial direction from the first ring segment pair such that the first radially inner ring segment of the first ring segment pair is at a same radial distance from a central axis of the turbomachine as the second radially outer ring segment of the second ring segment pair.

2. The twist prevention system according to claim 1 , wherein a distance of a surface of the first and the second radially inner ring segment and a surface of the first and the second radially outer ring segment from the central axis of the turbomachine in a circumferential and an axial direction is substantially constant.

3. The twist prevention system according to claim 1 , further comprising a third ring segment pair with a third radially inner ring segment and a third radially outer ring segment, wherein a portion of a face of the third radially inner ring segment overlaps a portion of the face of the first or the second radially outer ring segment in the radial direction.

4. The twist prevention system according claim 1 , wherein the first and the second radially inner ring segments are each a seal carrier segment and wherein the first and the second radially outer ring segments are each an inner ring segment which are coupled with a respective guide vane.

5. The twist prevention system according to claim 4 , further comprising a first seal disposed between the first inner ring segment and the first seal carrier segment and a second seal disposed between the second inner ring segment and the second seal carrier segment.

6. The twist prevention system according to claim 5 , wherein the first and the second seals have a w-shaped profile.

7. A gas turbine, comprising:
a compressor and/or turbine stage with a twist prevention system according to claim 1 .

8. The gas turbine according to claim 7 , wherein the gas turbine is an aircraft engine.

Assignees

• MTU Aero Engines AG

Inventors

• Kraus Juergen
• Wintner Stephan

Classifications

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/122

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title