Blade or vane arrangement for a turbomachine

Patent metadata

Field	Value
Publication number	US-10247005-B2
Application number	US-201514934970-A
Country	US
Kind code	B2
Filing date	Nov 6, 2015
Priority date	Nov 13, 2014
Publication date	Apr 2, 2019
Grant date	Apr 2, 2019

Abstract

A blade or vane arrangement for a turbomachine includes a turbomachine blade or vane and at least one tuning element guide housing with at least one cavity, in which at least one tuning element, 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 of the turbomachine blade or vane, wherein the cavity of the tuning element guide housing in which the tuning element 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, comprising:
a turbomachine blade or vane including a recess defined by at least one recess wall; and
at least one tuner guide housing with at least one cavity, in which at least one tuner that is provided for impact contact with the tuner guide housing is taken up, and a locking plate joined to the tuner guide housing,
wherein the tuner guide housing is fastened in the recess of the turbomachine blade or vane by the locking plate in a form-fitting or friction-fitting manner,
wherein the cavity of the tuner guide housing in which the tuner is taken up, is closed in a gas-tight manner, and
wherein the locking plate is in direct contact with the tuner guide housing and the at least one recess wall.

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

3. The blade or vane arrangement for a turbomachine according to claim 1 , wherein the locking plate is joined cohesively to the tuner guide housing.

4. The blade or vane arrangement for a turbomachine according to claim 1 , wherein the recess has an introduction opening, which permits a sequential introduction of the tuner guide housing and the locking plate and prevents a withdrawal of the locking plate together with the tuner guide housing that is joined to it in form-fitting manner.

5. The blade or vane arrangement for a turbomachine according to claim 1 , wherein the locking plate is fastened in the recess in a friction-fitting or form-fitting manner by at least one bent tab.

6. The blade or vane arrangement for a turbomachine according to claim 1 , wherein the locking plate is elastically deformed by the tuner guide housing that is joined thereto, and/or is clamped against the recess in a friction-fitting manner.

7. The blade or vane arrangement for a turbomachine according to claim 1 , wherein the tuner guide housing is joined cohesively to the turbomachine blade or vane.

8. 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.

9. The blade or vane arrangement for a turbomachine according to claim 1 , wherein the at least one tuner is arranged in the cavity of the at least one tuner guide housing, the housing being closed in a gas-tight manner by welding of at least two parts of the tuner guide housing, and the tuner guide housing is arranged in the recess of the turbomachine blade or vane.

10. The blade or vane arrangement for a turbomachine according to claim 9 , wherein a locking plate is arranged in the recess and is fastened in the recess in a form-fitting or friction-fitting manner by bending a tab.

11. The blade or vane arrangement for a turbomachine according to claim 9 , wherein a locking plate is introduced through an introduction opening of the recess and is fastened in the recess by joining to the tuner guide housing in a friction-fitting or form-fitting manner, or cohesively.

Assignees

• MTU Aero Engines AG

Inventors

• Hartung Andreas
• Schill Manfred
• Roesele Gerhard-Heinz

Classifications

• F04D29/666

  by means of rotor construction or layout, e.g. unequal distribution of blades or vanes · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F01D5/16 Primary

  for counteracting blade vibration · CPC title

• F05D2260/961

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