Seal arrangement for a turbomachine, method for manufacturing a seal arrangement and turbomachine

Patent metadata

Field	Value
Publication number	US-10808561-B2
Application number	US-201815990652-A
Country	US
Kind code	B2
Filing date	May 27, 2018
Priority date	May 29, 2017
Publication date	Oct 20, 2020
Grant date	Oct 20, 2020

Abstract

The invention relates to a seal arrangement for a turbomachine, especially for an aircraft engine, for sealing a radial gap between a rotor and a stator, comprising at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of extension and an axial crosspiece, formed as a single piece with the latter and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece, and a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, each with a radially running crosspiece.

First claim

What is claimed is:

1. A seal arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, comprising:
at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of an extension and an axial crosspiece, formed as a single piece with the former and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece; and
a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, wherein the front ring or the front ring segment and/or the rear ring or the rear ring segment include a respective radially running crosspiece,
wherein the radially running crosspiece of the front ring or the front ring segment or of the rear ring or the rear ring segment forms, with the radial crosspiece, a mount for uptake of an element of the stator, while an axially extending inner flange is formed at a radially inner end of the respective radially running crosspiece, and at least the inner flange of the respective radially running crosspiece, which forms the mount with the axial crosspiece of the seal carrier, is joined by integral bonding and/or form fitting to a radially outer-lying surface of the axial crosspiece.

2. The seal arrangement as claimed in claim 1 , wherein the inner flange is welded or soldered to the radially outer-lying surface of the axial crosspiece.

3. The seal arrangement as claimed in claim 1 , further comprising:
an axially extending outer flange located at a radially outer end of the respective radially running crosspiece.

4. The seal arrangement as claimed in claim 1 , wherein the front ring or the front ring segment and/or the rear ring or the rear ring segment are made of sheet metal.

5. The seal arrangement as claimed in claim 1 , wherein the seal carrier is T-shaped with the axial crosspiece extending in the axial direction at both ends beyond a connection region between the radial crosspiece and the axial crosspiece.

6. The seal arrangement as claimed in claim 1 , wherein the element of the stator is a vane root or a vane root segment of a guide vane ring, a guide vane ring segment or a guide vane of the turbomachine.

7. The seal arrangement as claimed in claim 1 , wherein a sliding block is connected by at least one axial bolt to the respective radially running crosspiece and to the radial crosspiece.

8. The seal arrangement as claimed in claim 1 , wherein the seal carrier of the seal arrangement is produced by forging, casting, lathe turning, or an additive manufacturing method.

9. The seal arrangement as claimed in claim 1 , wherein the seal element is a honeycomb seal.

10. The seal arrangement as claimed in claim 1 , wherein the seal arrangement is a Static Inner Air Seal (SIAS) ring or a ring segment thereof.

11. The seal arrangement as claimed in claim 1 ,
wherein the seal carrier of the seal arrangement is formed by forging, casting, lathe turning, or an additive manufacturing method; and
wherein the front ring or the front ring segment and/or the rear ring or the rear ring segment in the region of the radial crosspiece of the seal carrier is configured and arranged as the mount for the stator element.

12. The seal arrangement as claimed in claim 11 , wherein the inner flange is welded or soldered to the radially outer-lying surface of the axial crosspiece.

13. The seal arrangement of claim 1 , wherein at least one the seal arrangement is configured and arranged in a turbomachine.

Assignees

• MTU Aero Engines AG

Inventors

• Schlemmer Markus
• Pirker Klaus
• Sosnowka Lukasz
• Kislinger Bernd
• Stanka Rudolf
• Regulski Marcin

Classifications

• F16J15/444

  with facing materials having honeycomb-like structure · CPC title

• F05D2230/25

  by forging · CPC title

• F05D2240/55

  Seals · CPC title

• F05D2230/232

  by welding · CPC title

• F05D2230/237

  Brazing · CPC title