Blade or vane arrangement for a turbomachine

Patent metadata

Field	Value
Publication number	US-2016138401-A1
Application number	US-201514934970-A
Country	US
Kind code	A1
Filing date	Nov 6, 2015
Priority date	Nov 13, 2014
Publication date	May 19, 2016
Grant date	—

Abstract

The present invention relates to a blade or vane arrangement for a turbomachine having a turbomachine blade or vane ( 10 ) and at least one tuning element guide housing ( 21, 22 ) with at least one cavity ( 11 ), in which at least one tuning element ( 3 ), which is provided for impact contact with the tuning element guide housing is taken up, the tuning element guide housing being arranged in a recess ( 12 ) of the turbomachine blade or vane, wherein the cavity ( 11 ) of the tuning element guide housing ( 21, 22 ) in which the tuning element ( 3 ) is taken up, is closed in a gas-tight manner.

First claim

What is claimed is:

1 . A blade or vane arrangement for a turbomachine having a turbomachine blade or vane ( 10 ) and at least one tuning element guide housing ( 21 , 22 ) with at least one cavity ( 11 ), in which at least one tuning element ( 3 ) that is provided for impact contact with the tuning element guide housing is taken up, wherein the tuning element guide housing is arranged in a recess ( 12 ) of the turbomachine blade or vane, wherein
the cavity ( 11 ) of the tuning element guide housing ( 21 , 22 ) in which the tuning element ( 3 ) is taken up, is closed in a gas-tight manner.

2 . The blade or vane arrangement for a turbomachine according to the claim 1 , wherein the tuning element guide housing has at least two parts ( 21 , 22 ) that are welded together and define the cavity ( 11 ), which is closed in a gas-tight manner.

3 . The blade or vane arrangement for a turbomachine according to claim 1 , further comprising:
a locking plate ( 40 ), by means of which the tuning element guide housing ( 21 , 22 ) is fastened in the recess ( 12 ), in a form-fitting and/or friction-fitting manner.

4 . The blade or vane arrangement for a turbomachine according to claim 3 , wherein the locking plate ( 40 ) is joined to the tuning element guide housing ( 21 , 22 ) in form-fitting manner by at least one bent tab ( 41 ), and/or in a friction-fitting manner.

5 . The blade or vane arrangement for a turbomachine according to claim 3 , wherein the locking plate ( 40 ) is joined cohesively to the tuning element guide housing ( 21 , 22 ).

6 . The blade or vane arrangement for a turbomachine according to claim 3 , wherein the recess ( 12 ) has an introduction opening ( 13 ), which permits a sequential introduction of the tuning element guide housing ( 21 , 22 ) and the locking plate ( 40 ) and prevents a withdrawal of the locking plate together with the tuning element guide housing that is joined to it in form-fitting manner.

7 . The blade or vane arrangement for a turbomachine according to claim 3 , wherein the locking plate ( 40 ) is fastened in the recess ( 12 ) in a friction-fitting and/or form-fitting manner by at least one bent tab ( 42 ).

8 . The blade or vane arrangement for a turbomachine according to claim 3 , wherein the locking plate ( 40 ) is elastically deformed by the tuning element guide housing ( 21 , 22 ) that is joined thereto, and/or is clamped against the recess ( 12 ) in a friction-fitting manner.

9 . The blade or vane arrangement for a turbomachine according to claim 1 , wherein the tuning element guide housing ( 21 , 22 ) is joined cohesively to the turbomachine blade or vane ( 10 ).

10 . The blade or vane arrangement for a turbomachine according to claim 1 , wherein at least one blade or vane arrangement is configured and arranged in a turbomachine.

11 . The blade or vane arrangement for a turbomachine according to claim 1 , wherein the at least one tuning element ( 3 ) is arranged in the cavity ( 11 ) of the at least one tuning element guide housing ( 21 , 22 ), the housing being closed in a gas-tight manner by welding of at least two parts ( 21 , 22 ) of the tuning element guide housing, and the tuning element guide housing is arranged in the recess ( 12 ) of the turbomachine blade or vane ( 10 ).

12 . The blade or vane arrangement for a turbomachine according to claim 11 , wherein a locking plate ( 40 ) is be arranged in the recess ( 12 ) and is fastened in the latter in a form-fitting and/or friction-fitting manner by bending a tab ( 42 ).

13 . The blade or vane arrangement for a turbomachine according to claim 11 , wherein a locking plate ( 40 ) is introduced through an introduction opening ( 13 ) of the recess ( 12 ) and is fastened in the recess by joining to the tuning element guide housing ( 21 , 22 ) in a friction-fitting or form-fitting manner, or cohesively.

Assignees

• MTU Aero Engines AG

Inventors

• Hartung Andreas
• Schill Manfred
• Roesele Gerhard-Heinz

Classifications

• F05D2260/961

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

• F01D5/14 Primary

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2250/241

  spherical · CPC title

• F01D5/26

  Antivibration means not restricted to blade form or construction or to blade-to-blade connections {or to the use of particular materials} · CPC title