Turbomachine blade having a main body including a plane first attachment surface

Patent metadata

Field	Value
Publication number	US-10001016-B2
Application number	US-201514795017-A
Country	US
Kind code	B2
Filing date	Jul 9, 2015
Priority date	Jul 11, 2014
Publication date	Jun 19, 2018
Grant date	Jun 19, 2018

Abstract

A turbomachine blade having a main body ( 10 ) that includes a plane, first attachment surface ( 100 ) having a first rim contour ( 110 ), a cover ( 20; 21, 22 ) that has a plane, second attachment surface ( 200 ) having a second rim contour ( 210 ) that is welded to the first attachment surface, and a tuning body configuration having at least one tuning body ( 30; 31 - 33 ) for contacting an inner wall ( 220 ) of the cover by impact therewith, a gap (s) being formed between the first and the second rim contour.

First claim

What is claimed is:

1. A turbomachine blade comprising:
a main body including a plane, first attachment surface having a first rim contour; and
a cover including a plane, second attachment surface having a second rim contour and welded to the first attachment surface; and
a tuning body configuration having at least one tuning body for contacting an inner wall of the cover by impact therewith, a gap being formed between the first and second rim contour;
wherein the first attachment surface is configured radially inwardly or outwardly from an airfoil for flow deflection on a surface of an inner or outer shroud facing away from the airfoil.

2. The turbomachine blade as recited in claim 1 wherein the cover is disposed on the main body in a way that allows the cover to extend freely therefrom.

3. The turbomachine blade as recited in claim 1 wherein at least one tuning body of the tuning body configuration is accommodated in a cavity completely formed in the cover.

4. The turbomachine blade as recited in claim 1 wherein the cover is a multipart cover.

5. The turbomachine blade as recited in claim 1 wherein at least one tuning body of the tuning body configuration is accommodated in a cavity formed at least in sections thereof in the main body.

6. The turbomachine blade as recited in claim 1 further comprising at least two cavities having a different shape or different volume; at least one tuning body of the tuning body configuration being accommodated in at least one of these cavities.

7. The turbomachine blade as recited in claim 1 wherein at least one tuning body of the tuning body configuration is accommodated in a cavity; a circumferentially extending groove being formed in the first or second attachment surface between the cavity and the second rim contour.

8. The turbomachine blade as recited in claim 1 wherein at least one tuning body of the tuning body configuration is accommodated in a cavity and has a clearance of motion in a direction of degree of freedom of impact that is at least twice a guide clearance in a guide direction orthogonally to the direction of degree of freedom of impact or is between 0.5 mm and 1.5 mm.

9. The turbomachine blade as recited in claim 1 wherein at least one tuning body of the tuning body configuration is accommodated in a cavity and has a clearance of motion in a direction of degree of freedom of impact that is at least four times a guide clearance in a guide direction orthogonally to the direction of degree of freedom of impact or is between 0.5 mm and 1.5 mm.

10. The turbomachine blade as recited in claim 1 wherein at least one tuning body of the tuning body configuration is accommodated in a cavity, the cavity being airtight.

11. The turbomachine blade according to claim 10 , wherein the first and the second attachment surface are welded together without filler material.

12. The turbomachine blade as recited in claim 1 wherein the first or second attachment surface is produced by primary shaping or by casting.

13. The turbomachine blade as recited in claim 1 wherein the first and the second attachment surface are welded together without filler material.

14. A turbomachine comprising:
at least one compressor stage or turbine stage having at least one guide vane cascade or rotor blade cascade having at least one turbomachine blade as recited in claim 1 .

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

16. A method for manufacturing a turbomachine blade as recited in claim 1 , the method comprising:
disposing the tuning bodies of the tuning body configuration in at least one cavity formed at least in sections thereof in the cover or the main body.

17. The method as recited in claim 16 further comprising, subsequently to the disposing step, welding the plane, second attachment surface of the cover to the plane, first attachment surface of the main body in a way that allows the gap to be formed between the first and second rim contour.

18. The method as recited in claim 17 wherein the first and the second attachment surface are welded together without filler material.

19. The method as recited in claim 16 wherein the first or second attachment surface is produced by primary shaping or by casting.

20. The turbomachine blade according to claim 1 , wherein the first attachment surface is disposed solely radially inwardly from the airfoil.

21. A turbomachine blade comprising:
a main body including a plane, first attachment surface having a first rim contour; and
a cover including a plane, second attachment surface having a second rim contour and welded to the first attachment surface; and
a tuning body configuration having at least one tuning body for contacting an inner wall of the cover by impact therewith, a gap being formed between the first and second rim contour, wherein at least one tuning body of the tuning body configuration is accommodated in a cavity completely formed in the cover.

22. A turbomachine blade comprising:
a main body including a plane, first attachment surface having a first rim contour; and
a cover including a plane, second attachment surface having a second rim contour and welded to the first attachment surface, wherein the cover is a multipart cover; and
a tuning body configuration having at least one tuning body for contacting an inner wall of the cover by impact therewith, a gap being formed between the first and second rim contour.

23. A turbomachine blade comprising:
a main body including a plane, first attachment surface having a first rim contour; and
a cover including a plane, second attachment surface having a second rim contour and welded to the first attachment surface;
a tuning body configuration having at least one tuning body for contacting an inner wall of the cover by impact therewith, a gap being formed between the first and second rim contour;
at least two cavities having a different shape or different volume, at least one tuning body of the tuning body configuration being accommodated in at least one of these cavities.

24. A turbomachine blade comprising:
a main body including a plane, first attachment surface having a first rim contour; and
a cover including a plane, second attachment surface having a second rim contour and welded to the first attachment surface; and
a tuning body configuration having at least one tuning body for contacting an inner wall of the cover by impact therewith, a gap being formed between the first and second rim contour, wherein at least one tuning body of the tuning body configuration is accommodated in a cavity, a circumferentially extending groove being formed in the first or second attachment surface between the cavity and the second rim contour.

Assignees

• MTU Aero Engines AG

Inventors

• Stiehler Frank
• Hartung Andreas

Classifications

• F01D5/16 Primary

  for counteracting blade vibration · CPC title

• F05D2230/232

  by welding · CPC title

• B23P15/04

  turbine or like blades from several pieces · 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

• F05D2250/241

  spherical · CPC title