Turbomachine blade

Patent metadata

Field	Value
Publication number	US-10451089-B2
Application number	US-201615257434-A
Country	US
Kind code	B2
Filing date	Sep 6, 2016
Priority date	Sep 7, 2015
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber ( 10 ) in which at least one impulse element ( 11 ) is disposed with play, at least one second impact chamber ( 20 ) whose volumetric centroid is offset from a volumetric centroid of the first impact chamber ( 10 ) along a first matrix axis (A) and in which at least one impulse element ( 21 ) is disposed with play, and at least one third impact chamber ( 30 ) whose volumetric centroid is offset from the volumetric centroid of the first impact chamber ( 10 ) along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element ( 31 ) is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.

First claim

What is claimed is:

1. A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, comprising at least one matrix having:
a first impact chamber, at least one impulse element disposed with play in the first impact chamber;
at least one second impact chamber whose volumetric centroid is offset from a volumetric centroid of the first impact chamber along a first matrix axis, at least one second impulse element disposed with play in the second impact chamber, and
at least one third impact chamber whose volumetric centroid is offset from the volumetric centroid of the first impact chamber along a second matrix axis transversely to the first matrix axis, at least one third impulse element disposed with play in the third impact chamber,
the first matrix axis and an axis of rotation of the turbomachine forming an angle of at least 60° and no more than 120°;
the first, second and third impact chambers all being located either on a suction-side of the blade, or all being located on a pressure-side of the blade.

2. The blade as recited in claim 1 wherein the second matrix axis forms an angle of at least 0° and no more than 30° with the axis of rotation of the turbomachine.

3. The blade as recited in claim 1 further comprising at least one fourth impact chamber whose volumetric centroid is in a plane formed by the first and second matrix axes, at least one fourth impulse element disposed with play in the fourth impact chamber.

4. The blade as recited in claim 3 wherein a first connecting line between the volumetric centroid of the fourth impact chamber and the volumetric centroid of another one of the first impact chamber, the second impact chamber and the third impact chamber forms an angle of no more than 0° with the first matrix axis, and a second connecting line between the volumetric centroid of the fourth impact chamber and the volumetric centroid of the other one of the impact chamber, the second impact chamber and the third impact chamber forms an angle of no more than 10° with the second matrix axis.

5. The blade as recited in claim 1 wherein the volumetric centroids of at least one pair of the first impact chamber, the second impact chamber and the third impact chamber are spaced apart by at least 110% or no more than 400% of a maximum length dimension of the respective two of the impulse element, the second impulse element and the third impulse elements of the pair.

6. The blade as recited in claim 1 wherein the matrix is arranged on a side of a shroud of the blade facing away from the airfoil.

7. The blade as recited in claim 1 wherein at least one of the first impact chamber, the at least one second impact chamber and the at least one third impact chamber is formed in a base member formed with or connected to an airfoil.

8. The blade as recited in claim 1 wherein at least one of the first impact chamber, the at least one second impact chamber and the at least one third impact chamber is formed in a housing connected to a base member formed with or connected to an airfoil.

9. The blade as recited in claim 8 wherein the housing is connected by a material-to-material bond to the base member.

10. The blade as recited in claim 1 wherein at least one of the first impact chamber, the at least one second impact chamber and the at least one third impact chamber is closed by a cover.

11. The blade as recited in claim 10 wherein the cover is connected by a material-to-material bond.

12. A compressor or turbine stage for a gas turbine comprising at least one blade as recited in claim 1 .

13. A turbomachine comprising at least one blade as recited in claim 1 .

14. A gas turbine comprising the turbomachine as recited in claim 13 .

15. A method for manufacturing a blade as recited in claim 1 comprising the steps of: forming the first impact chamber, the second impact chamber and the third impact chamber; introducing the impulse element, the second impulse element and the third impulse element; and closing the first impact chamber, the second impact chamber and the third impact chamber.

16. The blade as recited in claim 1 wherein the first, second and third impact chambers all are located on the suction-side of the blade.

17. The blade as recited in claim 1 wherein the first, second and third impact chambers all are located on the pressure-side of the blade.

18. The blade as recited in claim 1 wherein at least one of the at least one impulse element, the at least one second impulse element and the at least one third impulse elements has a mass of at least 0.01 g and no more than 0.075 grams.

19. The blade as recited in claim 1 wherein play in at least one of the first, second and third impact chambers in at least one direction is at least 10 micrometers and no more than 1.5 mm.

20. The blade as recited in claim 1 wherein the second matrix axis forms an angle of at least 30° and no more than 90° with the first matrix axis.

Assignees

• MTU Aero Engines AG

Inventors

• Hartung Andreas
• Richter Karl-Hermann
• Hanrieder Herbert
• Schill Manfred

Classifications

• F05D2230/51

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

• F05D2250/241

  spherical · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F04D29/324

  Blades · 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