Stabilized sealing ring for a turbomachine

Patent metadata

Field	Value
Publication number	US-10544696-B2
Application number	US-201615367697-A
Country	US
Kind code	B2
Filing date	Dec 2, 2016
Priority date	Dec 4, 2015
Publication date	Jan 28, 2020
Grant date	Jan 28, 2020

Abstract

Disclosed is a sealing ring for a turbomachine, which is constructed so as to be fastened at a radially inner region of a plurality of guide vanes and rotate around a rotor shaft. The sealing ring comprises a ring part that extends in the axial direction and has a plurality of stiffened portions in succession in the peripheral direction. Further disclosed is a seal for a turbomachine that comprises such a sealing ring as well as a brush and/or run-in coating sealing ring that is to face a rotor shaft, and a method for the manufacture of a sealing ring.

First claim

What is claimed is:

1. A sealing ring for a turbomachine, is configured and arranged to be fastened to each radially inner region of a plurality of guide vanes and rotate around a rotor shaft, the rotor shaft extending in an axial direction, wherein the sealing ring comprises an axially extending ring part that extends substantially in the axial direction and a fastening portion that extends substantially in a radial direction from the ring part,
wherein the ring part has a radial facing surface that has a plurality of stiffened portions disposed in succession along a peripheral direction,
wherein the turbomachine further comprises a rotating blade cascade with a plurality of rotating blades that is axially adjacent to the plurality of guide vanes, wherein each of the plurality of guide vanes each comprise a radially inner cover plate and the rotating blades each comprise an axial projection at a radially inner region, the axial projection of the rotating blades being directed toward the plurality of guide vanes, wherein the ring part of the sealing ring that extends in the axial direction forms a labyrinth seal together with the radially inner cover plates of the plurality of guide vanes and the axial projections of the rotating blades,
wherein at least a portion of the plurality of stiffened portions or all of the plurality of stiffened portions are each essentially conical shaped and/or rotational paraboloid shaped,
wherein the plurality of the stiffened portions extend in the axial direction from a fastening means edge towards an opposing edge, wherein the plurality of stiffened portions does not extend to the opposing edge, and
wherein the stiffened portions are formed conically proceeding from the fastening edge in the axial direction and/or are formed so as to taper parabolically.

2. The sealing ring according to claim 1 , wherein the stiffened portions are distributed uniformly on the ring part extending in the axial direction.

3. The sealing ring according to claim 1 , wherein the stiffened portions comprise radial wells and/or radial elevations.

4. The sealing ring according to claim 1 , wherein the stiffened portions are tapered in the axial direction starting from a fastening means of the sealing ring.

5. The sealing ring according to claim 1 , including a seal for the turbomachine, which is configured and arranged to be fastened to a radially inner region of the plurality of guide vanes and to rotate around the rotor shaft, wherein the seal comprises at least one sealing ring and a brush and/or run-in coating sealing ring that faces the rotor shaft.

6. The sealing ring according to claim 5 , wherein turbomachine with the rotor shaft, the plurality of guide vanes, which together form a guide vane cascade of a turbine stage or a compressor stage, and the seal,
wherein the seal, together with the at least one sealing ring, is fastened to the radially inner region of the plurality of guide vanes.

7. The sealing ring according to claim 6 , wherein the axial projections of the rotating blades are arranged in the radial direction between the radially inner cover plates of the guide vanes and the ring part of the sealing ring.

8. The sealing ring according to claim 6 , wherein the guide vane cascade comprises two sealing rings, wherein one of the two sealing rings forms a labyrinth seal with an upstream rotating blade cascade and the other one of the two sealing rings forms a labyrinth seal with a downstream rotating blade cascade.

9. The sealing ring according to claim 1 , wherein at least a part of the stiffened portions or all stiffened portions is or are impressed as radial wells and/or molded as radial elevations in the outer surface.

Assignees

• MTU Aero Engines AG

Inventors

• Schlemmer Markus
• Liebscher Otto
• Thiele Oliver

Classifications

• F01D11/02

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F16J15/447

  Labyrinth packings · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title