Turbomachine blade

Patent metadata

Field	Value
Publication number	US-9765625-B2
Application number	US-201414283985-A
Country	US
Kind code	B2
Filing date	May 21, 2014
Priority date	May 23, 2013
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

A blade ( 1 ) for a turbomachine, including an impact chamber ( 2 ), a single impulse body ( 3 ) being situated in the impact chamber, a clearance (S 1 +S 2 ) between the impulse body and the impact chamber being at least 10 μm and/or at most 1.5 mm in at least one direction.

First claim

What is claimed is:

1. A blade for a turbomachine, comprising:
an impact chamber; and
a single impulse body movably situated in the impact chamber, a clearance between the impulse body and the impact chamber in all directions being at least 0.1 mm and at most 1.5 mm and wherein a mass of the impulse body is at least 10 mg and at most 1.5 g.

2. The blade as recited in claim 1 wherein the impulse body is provided with a spherical or disk shaped design.

3. The blade as recited in claim 1 wherein the impulse body is made from a nickel or cobalt alloy or a ceramic.

4. The blade as recited in claim 1 wherein the impact chamber has at least one pair of opposite, inner walls, each wall defining a preferred impact direction.

5. The blade as recited in claim 4 wherein the opposing inner walls are parallel.

6. The blade as recited in claim 1 wherein the impact chamber is situated in an outer shroud or a blade root of the blade.

7. The blade as recited in claim 1 wherein the impact chamber is situated in an outer shroud, the outer shroud vane extending radially.

8. The blade as recited in claim 1 wherein the impact chamber is closed by a cover.

9. The blade as recited in claim 8 wherein the cover is flush with an outer contour of the blade.

10. The blade as recited in claim 1 wherein the impact chamber, together with the blade, is formed in the blade surface using a material removing method or defined by a calotte situated in a recess in the blade.

11. The blade as recited in claim 1 wherein the blade is a moving blade.

12. The blade as recited in claim 1 wherein the blade is a guide blade.

13. A turbomachine comprising at least one compressor stage and/or turbine stage having at least one blade, the blade comprising:
an impact chamber; and
a single impulse body movably situated in the impact chamber, a clearance between the impulse body and the impact chamber in ail directions being at least 0.1 mm and at most 1.5 mm and wherein a mass of the impulse body is at least 10 mg and at most 1.5 g.

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

15. An aircraft engine gas turbine comprising the gas turbine as recited in claim 14 .

16. A method for manufacturing a blade as recited in claim 1 , the method comprising: providing the impact chamber in the blade; inserting the impulse body into the impact chamber; and subsequently closing the impact chamber.

Assignees

• MTU Aero Engines AG

Inventors

• Stiehler Frank
• Hartung Andreas

Classifications

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01D5/225

  by shrouding · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title