TURBOMACHINE BLADE ASSEMBLY

Abstract

A turbomachine blade assembly including a turbomachine blade (1), in particular for a gas turbine, and at least one tuning element container including a housing (10) attached to the turbomachine blade and an insert (20) disposed in a recess (11) of this housing. A wall (20; 21) of the insert spaces apart two first cavities (31), which each accommodate at least one tuning element (40) provided for impacting contact with the housing (10) and the insert (20).

Claims

1 to 11. (canceled)

12. A turbomachine blade assembly comprising: a turbomachine blade; at least one tuning element container including a housing attached to the turbomachine blade and an insert disposed in a recess of the housing, a wall of the insert spacing apart two first cavities; and tuning elements provided for impacting contact with the housing and the insert, the two first cavities each accommodating at least one of the tuning elements.

13. The turbomachine blade assembly as recited in claim 12 wherein the wall spaces apart two second cavities each accommodating at least one of the tuning elements.

14. The turbomachine blade assembly as recited in claim 13 wherein the wall or a further wall of the housing spaces apart at least one of the first cavities and one of the second cavities.

15. The turbomachine blade assembly as recited in claim 12 wherein the housing is formed as a single part or the insert is formed as a single part.

15. The turbomachine blade assembly as recited in claim 12 wherein the housing is formed of two identical parts.

16. The turbomachine blade assembly as recited in claim 12 wherein the housing or the insert is symmetrical about an axial plane.

17. The turbomachine blade assembly as recited in claim 12 wherein at least two parts of the housing, or the housing and the insert are joined together by a material-to-material bond.

18. The turbomachine blade assembly as recited in claim 17 wherein the material-to material bond includes a weld.

19. The turbomachine blade assembly as recited in claim 12 wherein end faces of two parts of the housing are joined together, at least one of the end faces having a depression, the insert being at least partially received in the depression.

20. The turbomachine blade assembly as recited in claim 12 wherein the housing has a recess open at one or both ends, the insert being inserted in the recess.

21. The turbomachine blade assembly as recited in claim 12 wherein the housing or the insert have at least one recess open at one or both ends and bounding one of the two first cavities.

22. The turbomachine blade assembly as recited in claim 12 wherein the housing is cuboid-shaped.

23. A turbomachine comprising: at least one turbomachine blade assembly as recited in claim 12.

24. A gas turbine comprising the turbomachine blade assembly as recited in claim 23.

25. A method for manufacturing the turbomachine blade assembly as recited in claim 12, comprising placing the tuning elements into the first cavities and placing the insert into a recess of the housing.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Further advantageous embodiments of the present invention will become apparent from the dependent claims and the following description of preferred embodiments. To this end, the drawings show, partly in schematic form, in:

[0029] FIG. 1: a perspective view of a portion of a turbomachine blade assembly in accordance with an embodiment of the present invention showing a generally axial direction c-c and a generally radial direction beta-beta;

[0030] FIG. 2: a cross section through a tuning element container of the turbomachine blade assembly, taken parallel to the plane of the drawing of FIG. 1 and along line II-II in FIG. 3;

[0031] FIG. 3: a cross section through the tuning element container, taken along line III-III in FIG. 2;

[0032] FIG. 4: a cross section, corresponding to FIG. 2, through a tuning element container of a turbomachine blade assembly in accordance with another embodiment of the present invention;

[0033] FIG. 5: a cross section, corresponding to FIG. 3, through the tuning element container of FIG. 4;

[0034] FIG. 6: a cross section, corresponding to FIGS. 2, 4, through a tuning element container of a turbomachine blade assembly in accordance with another embodiment of the present invention; and

[0035] FIG. 7: a cross section, corresponding to FIGS. 3, 5, through the tuning element container of FIG. 6.

DETAILED DESCRIPTION

[0036] FIG. 1 shows, in perspective view, a root-end portion of a turbomachine blade assembly according to an embodiment of the present invention. The turbomachine blade assembly includes a turbomachine blade 1 (only partially shown in FIG. 1) and a tuning element container, which is shown in FIG. 2 in a cross section taken parallel to the plane of the drawing of FIG. 1 and, in FIG. 3, in a cross section perpendicular thereto, taken along line III-III in FIG. 2.

[0037] The tuning element container includes a housing 10 which is attached to the turbomachine blade 1 and composed of two identical parts 10A, 10B, as well as an insert 20 disposed in a recess 11 of this housing. Two first cavities 31, which each accommodate a tuning element 40 provided for impacting contact with housing 10 and insert 20, are spaced apart by the insert, which, in the exemplary embodiment of FIGS. 2, 3, is formed by a flat wall 20.

[0038] The tuning element container has two second cavities 32, as well as further cavities 33, which also each accommodate a tuning element 40 provided for impacting contact with housing 10 and insert 20. The two second cavities 32, and each two of the further cavities 33, are respectively spaced apart by the insert; i.e., wall 20.

[0039] As can be seen in FIG. 2, a wall 12 of housing 10 spaces apart each one of the first cavities 31 from a respective one of the second cavities 32, each one of the second cavities 32 from a respective one of the further cavities 33, and each two of the further cavities 33 from respective ones of the further cavities 33.

[0040] End faces 13 of the two parts 10A, 10B of housing 10 are joined together gas-tight by a circumferential weld 12. Each of the end faces 13 has a depression 11, in which insert 20 is partially received, and which thus together form recess 11.

[0041] Housing 10 has blind holes which are open at one end. Each of the blind holes bounds one of the cavities 31-33 and, together with the insert or wall 20, defines one of the cavities 31-33.

[0042] Housing 10 is cuboid-shaped.

[0043] In order to manufacture the turbomachine blade assembly, initially, tuning elements 40 are placed into the blind holes in parts 10A, 10B of the housing, and then insert 20 is placed into recess 11. Subsequently, the two parts 10A, 10B are welded together.

[0044] FIGS. 4, 5 show cross sections, corresponding to FIGS. 2, 3, through a tuning element container of a turbomachine blade assembly in accordance with another embodiment of the present invention. Corresponding features are identified by identical reference numerals, so that reference is made to the above description and only the differences will be discussed below.

[0045] In the embodiment of FIGS. 4, 5, insert 20 is inserted in a recess 11 of one-piece housing 10, which recess is open at both ends. Insert 20 is welded gas-tight to housing 10 at both end faces (at the top and bottom in FIG. 4) by a respective circumferential weld 12.

[0046] In this embodiment, as can be seen in FIG. 4, a wall 22 of insert 20 spaces apart each one of the first cavities 31 from a respective one of the second cavities 32, each one of the second cavities 32 from a respective one of the further cavities 33, and each two of the further cavities 33 from respective ones of the further cavities 33, and a wall 21 of insert 20, which is perpendicular to wall 22, spaces apart the two first cavities 21, the two second cavities 32, and each two of the further cavities 33 from respective ones of the further cavities 33.

[0047] Insert 20 has through-holes which are open at both ends (at the top and bottom in FIG. 5). Each of the through-holes bounds one of the cavities 31-33 and, together with housing 10, defines one of the cavities 31-33.

[0048] In order to manufacture the turbomachine blade assembly of the embodiment of FIGS. 4, 5, tuning elements 40 are placed into the through-holes of insert 20, and then insert 20 is placed into recess 11 of housing 10 and welded thereto.

[0049] FIGS. 6, 7 show cross sections, corresponding to FIGS. 4, 5, through a tuning element container of a turbomachine blade assembly in accordance with another embodiment of the present invention. Corresponding features are identified by identical reference numerals, so that reference is made to the above description and only the differences will be discussed below.

[0050] Unlike the embodiment of FIGS. 4, 5, in the embodiment of FIGS. 6, 7, the through-holes of insert 20 do not have a closed periphery (i.e., cross section), but each have slot (at the right and left in FIGS. 6, 7) which, like the opposite openings at the end faces (at the top and bottom in FIG. 5 and FIG. 7), is covered or closed by housing 10. This makes it possible to reduce weight and/or to achieve a different impact behavior of tuning elements 40 in cavities 31-33.

[0051] Although exemplary embodiments have been described in the foregoing, it should be noted that many modifications are possible. It should also be appreciated that the exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration in any way. Rather, the foregoing detailed description provides those skilled in the art with a convenient road map for implementing at least one exemplary embodiment, it being understood that various changes may be made in the function and arrangement of elements described without departing from the scope of protection set forth in the appended claims and the legal equivalents thereof.

LIST OF REFERENCE NUMERALS

[0052] 1 turbomachine blade

[0053] 10 housing

[0054] 10A,

[0055] 10B housing part

[0056] 11 recess/depression

[0057] 12 weld

[0058] 13 end face

[0059] 20 insert

[0060] 21 wall

[0061] 22 wall

[0062] 31 first cavity

[0063] 32 second cavity

[0064] 33 further cavity

[0065] 40 tuning element