Guide vane segment for a turbomachine

Patent metadata

Field	Value
Publication number	US-10895162-B2
Application number	US-201715428386-A
Country	US
Kind code	B2
Filing date	Feb 9, 2017
Priority date	Feb 18, 2016
Publication date	Jan 19, 2021
Grant date	Jan 19, 2021

Abstract

The invention relates to a guide vane segment for an aircraft engine, having at least one guide vane element, having at least one flange formed in a radial extension direction (R) of the guide vane element and at least one positioning member projecting from the flange in the radial extension direction (R), and at least one seal carrier, which is arranged at the flange and is aligned relative to the guide vane element by way of the positioning member, wherein the flange has a supporting surface on which the seal carrier is supported, wherein a partial surface of the positioning member is adjacent to the flange at a transition from the flange to the positioning member, and respective surface normal lines of the supporting surface and of the partial surface enclose between them an angle (α) that is different from a zero angle.

First claim

What is claimed is:

1. A guide vane segment for a turbomachine, comprising:
at least one guide vane element, which includes at least one flange formed in a radial extension direction of the guide vane element and at least one positioning member projecting from the flange in the radial extension direction, and
at least one seal carrier, which is positioned at the flange and is aligned relative to the guide vane element by way of the positioning member, wherein the flange has a supporting surface on which the seal carrier is supported;
wherein a partial surface of the positioning member is adjacent to the flange at a transition from the flange to the positioning member, and respective surface normal lines of the supporting surface and of the partial surface enclose between them an angle that is different from a zero angle,
wherein the at least one seal carrier has at least one encircling radial groove, with which the positioning member is engaged in the arrangement of the seal carrier at the flange,
wherein the positioning member has at least two positioning mandrels arranged fork-like to one another extending directly downward from the supporting surface, the partial surface of the position member defines at least a portion of a face of the respective mandrels, and these mandrels engaging in the encircling radial groove in the arrangement of the seal carrier at the flange,
wherein a gap is defined between the seal carrier and the face of the respective mandrels along an entire length of the mandrel, and
wherein the partial surface is at least a partially curved surface.

2. The guide vane segment according to claim 1 , wherein the supporting surface is at least substantially formed as an annular surface segment.

3. The guide vane segment according to claim 1 , wherein the positioning member is joined as one part with the flange.

4. A guide vane element for the guide vane segment according to claim 1 , wherein, with the at least one flange formed in the radial extension direction of the guide vane element, the at least one positioning member projecting from the flange in the radial extension direction for the alignment of the seal carrier relative to the guide vane element, and
wherein the partial surface of the positioning member is adjacent to the flange at a transition from the flange to the positioning member, and respective surface normal lines of the supporting surface and of the partial surface enclose between them an angle that is different from a zero angle.

5. A guide vane element according to claim 1 , wherein at least one guide vane segment is arranged into a guide vane ring.

6. A guide vane element according to claim 5 , wherein at least one guide vane segment and/or at least one guide vane element is arranged into an aircraft engine.

7. A guide vane element according to claim 6 , wherein the turbomachine is a turbine and the supporting surface of the flange is facing a main flow direction of a working medium flowing through the turbomachine during the operation thereof.

8. A guide vane element according to claim 6 , wherein the turbomachine is a compressor, and the supporting surface of the flange is facing away from a main flow direction of a working medium flowing through the turbomachine during the operation thereof.

9. The guide vane segment according to claim 1 , wherein the partially curved surface extends directly from a planar surface which extends directly from the supporting surface.

Assignees

• MTU Aero Engines AG

Inventors

• Schlemmer Markus
• Feldmann Manfred
• Stanka Rudolf
• Thiele Oliver

Classifications

• F01D9/04 Primary

  forming ring or sector · CPC title

• F01D9/042

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title