Blade or vane for a turbomachine and axial turbomachine

Patent metadata

Field	Value
Publication number	US-9982559-B2
Application number	US-201514943686-A
Country	US
Kind code	B2
Filing date	Nov 17, 2015
Priority date	Nov 24, 2014
Publication date	May 29, 2018
Grant date	May 29, 2018

Abstract

The present invention relates to a blade or vane for a turbomachine, having at least one impulse element housing with a first impact cavity, in which an impulse element is arranged with play of movement, wherein the impulse element housing has at least one second impact cavity, which is in alignment with the first impact cavity in a first matrix direction and in which an impulse element is arranged with play of movement, and has at least one third impact cavity, which is in alignment with the first impact cavity in a second matrix direction crosswise to the first matrix direction and in which an impulse element is arranged with play of movement.

First claim

What is claimed is:

1. A blade or vane for a turbomachine, comprising:
at least one impulse element housing including
a first impact cavity, in which an impulse element is arranged with play of movement,
at least one second impact cavity, which is in alignment with the first impact cavity in a first matrix direction and in which an impulse element is arranged with play of movement,
at least one third impact cavity, which is in alignment with the first impact cavity in a second matrix direction crosswise to the first matrix direction and in which an impulse element is arranged with play of movement, and
at least one fourth impact cavity, which is in alignment with the at least one third impact cavity in a first matrix direction and in which an impulse element is arranged with play of movement and is, respectively, in alignment with the respective at least one second impact cavity in the second matrix direction, and

at least one of the impact cavities in at least one first and one second matrix direction, which enclose between them an angle of at least 30° and at most 150° and each of which encloses an angle of at least 75° and at most 105° with a longitudinal axis of the blade or vane that is perpendicular to an axis of rotation of the turbomachine, in each case, has cavity walls lying opposite each other, wherein a distance between the cavity walls lying opposite each other in the first matrix direction differs by at most 10% in comparison to a distance between the cavity walls lying opposite each other in the second matrix direction;
whereby the first impact cavity, the at least one second impact cavity, the at least one third cavity and the at least one fourth cavity are arranged in a substantially equidistant matrix-like manner.

2. The blade or vane according to claim 1 , wherein at least one wall of at least one of the impact cavities encloses an angle of at most 15° with the longitudinal axis of the blade or vane.

3. The blade or vane according to claim 1 , wherein at least one wall of at least one of the impact cavities is flat.

4. The blade or vane according to claim 1 , wherein at least one of the impact cavities has a circular or polygonal cross section.

5. The blade or vane according to claim 1 , wherein a weight of at least one of the impulse elements is at least 0.01 g and/or at most 0.075 g.

6. The blade or vane according to claim 1 , wherein a density of at least one of the impulse elements is at most 80% of a density of a body of the blade.

7. The blade or vane according to claim 1 , wherein the impulse element housing is manufactured separately in multiple parts, and joined detachably or permanently to a main body root, a shroud, or a body of the blade.

8. The blade or vane according to claim 1 , wherein at least one of the impulse element housings is arranged in a half of the blade closer to a front edge and/or at least one of the impulse element housings is arranged in a half of the blade closer to a back edge.

9. An axial turbomachine, comprising:
a frontmost blade cascade assembly in a through flow direction,
a rearmost blade cascade assembly in the through flow direction, and
at least one further blade cascade assembly, which is arranged between the frontmost and the rearmost blade cascade assemblies in the through flow direction,
wherein at least one rotating blade of the frontmost blade cascade assembly and at least one rotating blade of the rearmost blade assembly has at least one impulse element housing with at least one impact cavity, in which an impulse element is arranged with play of movement, and
wherein at least one guide vane and/or one rotating blade of the further blade cascade assembly does not have an impact cavity, in which an impulse element is arranged with play of movement.

10. The axial turbomachine according to claim 9 , wherein at least one wall of at least one of the impact cavities encloses an angle of at most 15° with a longitudinal axis of the blade perpendicular to an axis of rotation of the axial turbomachine, and/or is flat.

11. The axial turbomachine according to claim 9 , wherein at least one of the impact cavities has a circular or polygonal cross section.

12. The axial turbomachine according to claim 9 , wherein a weight of at least one impulse element is at least 0.01 g and/or at most 0.075 g.

13. The axial turbomachine according to claim 9 , wherein a density of at least one of the impulse elements is at most 80% of a density of a body of the blade in which the impulse element is arranged.

14. The axial turbomachine according to claim 9 , wherein the impulse element housing is manufactured separately in multiple parts, and joined detachably or permanently to a main body root, a shroud, or a body of the blade, in which the impulse element is arranged.

15. The axial turbomachine according to claim 9 , wherein at least one of the impulse element housings is arranged in a half of the blade closer to a front edge and/or at least one of the impulse element housings is arranged in a half of the blade closer to a back edge, in which blade the impulse element housing is arranged.

Assignees

• MTU Aero Engines AG

Inventors

• Hartung Andreas
• Klingels Hermann
• Wackers Patrick
• Feldmann Manfred
• Stiehler Frank
• Schlemmer Markus

Classifications

• F05D2250/241

  spherical · CPC title

• F05D2230/51

  in a modular way, e.g. using several identical or complementary parts or features · CPC title

• F01D25/06 Primary

  for preventing blade vibration (means on blade-carrying members or blades F01D5/00) · CPC title

• F05D2250/131

  polygonal · CPC title

• F04D29/324

  Blades · CPC title