TURBOMACHINE BLADE ASSEMBLY

Abstract

The present invention relates to a turbomachine blade or vane arrangement having a first turbomachine blade or vane (10), a second turbomachine blade or vane (20) adjacent to it, and at least one tuning element guide housing (30) with at least one cavity, in which at least one tuning element (5) is arranged with play of movement for impact contact with the tuning element guide housing, with the tuning element guide housing being arranged at least in part in a recess (11), in particular in a frame (12), of the first turbomachine blade or vane (10), where the second turbomachine blade or vane (20) has at least one first rib (21) for securing the tuning element guide housing (30) arranged in the recess (11).

Claims

1. A turbomachine blade or vane arrangement having a first turbomachine blade or vane (10), a second turbomachine blade or vane (20) adjacent to it, and at least one tuning element guide housing (30) with at least one cavity, in which at least one tuning element (5) is arranged with play of movement for impact contact with the tuning element guide housing, with the tuning element guide housing being arranged at least in part in a recess (11) in a frame (12) of the first turbomachine blade or vane (10), wherein the second turbomachine blade or vane (20) has at least one first rib (21) for securing the tuning element guide housing (30) arranged in the recess (11).

2. The turbomachine blade or vane arrangement according to claim 1, wherein the second turbomachine blade or vane (20) has at least one second rib (22) for securing the tuning element guide housing (30) arranged in the recess (11).

3. The turbomachine blade or vane arrangement according to claim 2, wherein the second rib (22) is inclined toward the first rib (21), wherein an angle between the first and second rib, in particular, is at least 45° and/or at most 135°.

4. The turbomachine blade or vane arrangement according to claim 1, wherein an angle between the first rib and a radial or axial direction is at most 30°.

5. The turbomachine blade or vane arrangement according to claim 1, wherein the first and/or second rib are or is joined to a front flange (23) of the second turbomachine blade or vane (20) and are integrally formed.

6. The turbomachine blade or vane arrangement according to claim 1, wherein the recess (11) is arranged in a platform on the side of the blade or vane root and/or on a pressure and/or outlet side of the first turbomachine blade or vane (10).

7. The turbomachine blade or vane arrangement according to claim 6, wherein the tuning element guide housing (30) has at least two parts (31, 32), which are joined to each other in an airtight and/or cohesive manner and define the cavity.

8. The turbomachine blade or vane arrangement according to claim 1, wherein the at least one tuning element (5) is conical in form.

9. The turbomachine blade or vane arrangement according to claim 1, wherein one tuning element (5) or at least two tuning elements are arranged in at least one cavity of the tuning element guide housing (30).

10. The turbomachine blade or vane arrangement according to claim 1, wherein at least one tuning element (5) is arranged in a cavity in a disengaged manner.

11. The turbomachine blade or vane arrangement according to claim 1, wherein at least one tuning element (5) has a weight that is at least 0.01 g and/or at most 0.05 g.

12. The turbomachine blade or vane arrangement according to claim 1, wherein at least one tuning element (5) has a diameter of at least 1 mm and/or at most 5 mm.

13. The turbomachine blade or vane arrangement according to claim 1, wherein the play of movement of at least one tuning element (5) is at least 0.01 mm and/or at least 1% of a minimum diameter of the tuning element and/or at most 10 mm and/or at most 100% of a maximum diameter of the tuning element.

14. The turbomachine blade or vane arrangement according to claim 1, wherein the turbomachine blade or vane arrangement is configured or arranged in a compressor or turbine stage.

15. The turbomachine blade or vane arrangement of claim 14, wherein the compressor or turbine stage is configured and arranged for use in an aircraft engine gas turbine.

Description

[0042] Other advantageous enhancements of the present invention ensue from the dependent claims and the following description of preferred embodiments. For this purpose and partially schematic:

[0043] FIG. 1 shows a turbomachine blade or vane arrangement of a turbomachine stage of a turbomachine in accordance with an embodiment of the present invention in perspective exploded view;

[0044] FIG. 2 shows a plan view onto a first turbomachine blade or vane of the turbomachine blade or vane arrangement in the peripheral direction;

[0045] FIG. 3 shows a section through the turbomachine blade or vane arrangement along the line C-C in FIG. 2;

[0046] FIG. 4 shows a section through the turbomachine blade or vane arrangement along the line L-L in FIGS. 3; and

[0047] FIG. 5 shows a section through the turbomachine blade or vane arrangement along the line M-M in FIG. 3.

[0048] FIG. 1 shows a turbomachine blade or vane arrangement of a turbomachine stage of a turbomachine in accordance with an embodiment of the present invention in perspective view.

[0049] The turbomachine blade or vane arrangement has a first turbomachine blade or vane 10 and a second turbomachine blade or vane 20, which is adjacent to it (in mounted position) in the peripheral direction, wherein the two turbomachine blade or vanes in FIG. 1 are exploded in the illustration in order to show their adjacent front sides (in mounted position).

[0050] The turbomachine blade or vane arrangement has a tuning element guide housing 30 with a plurality of cavities (eight in the exemplary embodiment), in each of which a conical tuning or impulse element 5 is arranged with play of movement for impact contact with the tuning element guide housing (see FIGS. 3-5).

[0051] The tuning element guide housing 30 is fully accommodated in a front-side recess 11 (see FIG. 5) in a frame 12 (see FIG. 2) of the first turbomachine blade or vane 10.

[0052] The tuning element guide housing 30 accommodated in the recess 11 in the frame 12 is accommodated therein with translational play of movement in a direction of insertion or direction of opening into or in, respectively, the recess 11 (perpendicular to the plane of the drawing of FIG. 2), so that it can be pulled out of it without the second blade or vane 20.

[0053] The recess 11 or the frame 12 has a slot 13 (see FIG. 2).

[0054] The second turbomachine blade or vane 20 has a first rib 21 and a second rib 22, which secure the tuning element guide housing 30 arranged in the recess 11 in a form-fitting manner, and, in particular prevent it, in a form-fitting manner, from being pulled out of the recess opposite to the direction of insertion, and, for this purpose, each lies opposite the recess 11 or the tuning element guide housing 30 arranged therein in the peripheral direction and partially overlap it.

[0055] The two ribs 21, 22 prevent, in a form-fitting manner, any twisting or rotation of the tuning element guide housing out of the recess 11.

[0056] An angle between the second rib 22, which is inclined toward the first rib, and the first rib is about 90°.

[0057] The first rib 21 extends essentially in the radial direction and the second rib 22 extends correspondingly essentially in the axial direction.

[0058] In this way, the first rib 21 limits, in particular, any twisting of the tuning element guide housing 30 in the plane of the drawing of FIG. 4 and the first and second ribs 21, 22 prevent, in particular, any twisting of the tuning element guide housing 30 in the plane of the drawing of FIG. 3.

[0059] The first and second ribs are essentially straight, spaced apart from each other, and formed integrally with a front flange 23 of the second turbomachine blade or vane.

[0060] The recess 11 is arranged in a platform on the side of the blade or vane root on a pressure side and on an outlet or outflow side of the first turbomachine blade or vane 10.

[0061] The tuning element guide housing 30 has two parts 31, 32, which are joined to each other in an airtight and cohesive manner and which define the cavities.

[0062] Although, in the above description, exemplary embodiments were explained, it is noted that a large number of modifications are possible. Moreover, it is noted that the exemplary embodiments are merely examples, which are not intended to limit the protective scope, the applications, and the design in any way. Instead, the preceding description affords the person skilled in the art a guideline for the implementation of at least one exemplary embodiment, with it being possible to make diverse changes, in particular in regard to the function and arrangement of the described components, without departing from the protective scope that ensues from the claims and combinations of features equivalent to these.

LIST OF REFERENCE NUMBERS

[0063] 10 first turbomachine blade or vane [0064] 11 recess [0065] 12 frame [0066] 13 slot [0067] 20 second turbomachine blade or vane [0068] 21 first rib [0069] 22 second rib [0070] 23 front flange [0071] 30 tuning element guide housing [0072] 31, 32 tuning element guide housing part [0073] 5 tuning element