Guide vane segment for a turbomachine

Patent metadata

Field	Value
Publication number	US-10436044-B2
Application number	US-201615367657-A
Country	US
Kind code	B2
Filing date	Dec 2, 2016
Priority date	Dec 4, 2015
Publication date	Oct 8, 2019
Grant date	Oct 8, 2019

Abstract

The invention relates to a guide vane cluster for a turbomachine, in particular for a turbojet engine, having at least two vanes that are joined together by way of at least one common platform for the radial delimiting of a flow channel of the turbomachine, wherein each vane has a vane element with a suction side and a pressure side that are joined together by a leading edge and a trailing edge, wherein the at least two vanes have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.

First claim

What is claimed is:

1. A guide vane cluster for a turbomachine, having at least two vanes that are joined together by way of at least one common platform for the radial delimiting of a flow channel of the turbomachine, wherein each vane has a vane element with a suction side and a pressure side that are joined together by a leading edge and a trailing edge,
wherein the at least two vanes have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region,
wherein the at least two vanes have the same cross sectional geometry, at a given axial height, with the exception of the trailing edge wall thickness, and
wherein the at least two vanes are exposed to a common flow path at the same time.

2. The guide vane cluster according to claim 1 ,
wherein the at least two vanes are joined together by way of a common radially inner platform and a common radially outer platform.

3. The guide vane cluster according to claim 1 , wherein the at least two vanes have roundings with different rounding radii in corresponding connection regions to the at least one common platform.

4. The guide vane cluster according to claim 1 , wherein the guide vane cluster comprises at least three vanes, wherein at least two of the vanes have different trailing edge wall thicknesses in a corresponding radial lengthwise extension region.

5. The guide vane cluster according to claim 1 , wherein the at least two vanes have at least one region in a vicinity of the at least one common platform that extends away from the at least one common platform by at most 25% of the radial lengthwise extension of the trailing edge, and/or have at least one region remote from the at least one common platform that extends by at least 25% of the radial lengthwise extension of the trailing edge in a central region of the trailing edge.

6. The guide vane cluster according to claim 5 , wherein at least one of the at least two vanes has a maximum trailing edge wall thickness in a region in the vicinity of the at least one common platform and/or in a region remote from the at least one common platform.

7. The guide vane cluster according to claim 1 , wherein a maximum and/or a minimum trailing edge wall thickness of at least one vane of the at least two vanes is constant, along a predetermined radial lengthwise extension region.

8. The guide vane cluster according to claim 1 , wherein at least one vane of the at least two vanes has a radial transition region between a maximum and a minimum trailing edge wall thickness.

9. The guide vane cluster according to claim 8 ,
wherein the trailing edge wall thickness in the transition region of the at least one vane increases continually and/or monotonically from the minimum to the maximum trailing edge wall thickness, and/or that the transition region extends over at most 25% of the radial lengthwise extension of the trailing edge.

10. The guide vane cluster according to claim 1 , wherein the at least two vanes each have an axial length and a chord length, wherein the at least two vanes have the same axial length and/or the same chord length or that at least one vane, when compared to at least one other vane, has a cut-back profile in the region of its trailing edge.

11. The guide vane cluster according to claim 1 , wherein the guide vane cluster is configured and arranged into a guide vane ring for a turbomachine.

12. The guide vane cluster according to claim 11 , wherein the guide vane ring is configured and arranged into a turbojet engine.

Assignees

• MTU Aero Engines AG

Inventors

• Schlemmer Markus
• Pernleitner Martin
• Wolfrum Nina
• Brettschneider Markus
• Mahle Inga

Classifications

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F01D5/16

  for counteracting blade vibration · CPC title

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title