Guide Vane Segment

Abstract

A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

Claims

1-14. (canceled)

15. A guide vane segment for a turbomachine stage comprising: an inner ring segment; a plurality of guide vanes configured on the inner ring segment; and at least one cavity containing at least one impulse element with clearance of motion for providing impact contacts, the at least one cavity being at or in at least one detuning region of the inner ring segment; the at least one detuning region extending circumferentially in a portion of the inner ring segment from an end face of the inner ring segment to an inner guide vane of the guide vanes circumferentially adjacent to an outermost guide vane of the guide vanes adjacent to the end face or extending at most over an outermost third of a length of the inner ring segment bounded by the end face.

16. The guide vane segment as recited in claim 15 wherein the detuning region extends from an inner boundary facing away from the end face at most to the outermost guide vane.

17. The guide vane segment as recited in claim 15 wherein an outer boundary of the detuning region facing the end face is spaced apart from the end face by at least 0.5 mm.

18. The guide vane segment as recited in claim 15 wherein at least 25% of all impulse elements configured at or in the inner ring segment are located at or in the detuning region.

19. The guide vane segment as recited in claim 15 wherein the at least one impulse element is spherical in shape.

20. The guide vane segment as recited in claim 15 wherein exactly one impulse element or at least two impulse elements of the at least one impulse element are located in at least one cavity.

21. The guide vane segment as recited in claim 15 wherein the at least one impulse element is accommodated unrestrainably in a cavity.

22. The guide vane segment as recited in claim 15 wherein the at least cavity is configured in a separately produced housing.

23. The guide vane segment as recited in claim 22 wherein the at least one cavity is air-tight.

24. The guide vane segment as recited in claim 15 wherein the impulse element has a mass of at least 0.01 g or of at most of 0.05 g.

25. The guide vane segment as recited in claim 15 wherein the impulse element has a minimum or maximum diameter of at least 1 mm or of at most 5 mm.

26. The guide vane segment as recited in claim 15 wherein a clearance of motion of the at least one impulse element is at least 0.01 mm or at least 1% of a minimum diameter of the impulse element or at most 10 mm or at most 100% of a maximum diameter of the impulse element.

27. The guide vane segment as recited in claim 15 wherein the at least one impulse element is designed for detuning cluster modes of the guide vane segment.

28. A turbomachine stage comprising the guide vane segment as recited in claim 15.

29. A compressor or turbine stage comprising the turbomachine stage as recited in claim 28.

30. A turbomachine comprising the turbomachine stage as recited in claim 28.

31. A gas turbine comprising the turbomachine as recited in claim 30 claim 32 (new) An aircraft engine gas turbine comprising the gas turbine as recited in claim 31.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Other advantageous embodiments of the present invention will become apparent from the dependent claims and the following description of preferred embodiments. To this end, the drawing shows, partly in schematic form, in:

[0052] FIG. 1: a guide vane segment of a turbomachine in accordance with a variant of the present invention in an axial plan view; and

[0053] FIG. 2: the guide vane segment in a lateral view in the circumferential direction.

DETAILED DESCRIPTION

[0054] FIG. 1 shows schematically a guide vane segment of a turbomachine 1000 shown schematically as an aircraft engine gas turbine, in accordance with a variant of the present invention in an axial plan view; FIG. 2 shows a lateral view in the circumferential direction.

[0055] The guide vane segment has an inner ring segment 10 and a plurality of guide vanes 21, 22, 23, 24, 25 that are integrally formed with inner ring segment 10.

[0056] Attached in each case to a first detuning region A (to the left in FIG. 1) of inner ring segment 10 and to a second detuning region B (to the right in FIG. 1) of inner ring segment 10 is a separately produced housing 110 having a plurality of air-filled cavities 112 in each of which a spherical impulse element 100 is configured unrestrainably and with clearance of motion for inducing impact contacts, and which are sealed airtight by a shared cover 111.

[0057] First detuning region A extends circumferentially (horizontally in FIG. 1; orthogonally to the image plane of FIG. 2) between a first outermost guide vane 21 and inner guide vane 22 adjacent thereto and thus, in particular, in a (left in FIG. 1) portion of inner ring segment 10 that extends from a first end face 11 of inner ring segment 10 to inner guide vane 22, as well as circumferentially at most over a first outermost third of a length L of inner ring segment bounded by first end face 11 of inner ring segment 10, in particular at most from inner boundary a, thereof facing away from first end face 11, to first outermost guide vane 21. Outer boundary a.sub.a thereof facing first end face 11 is spaced apart from first end face 11 by at least 1 mm.

[0058] Analogously, second detuning region B extends circumferentially (horizontally in FIG. 1; orthogonally to the image plane of FIG. 2) between a second outermost guide vane 25 and inner guide vane 24 adjacent thereto and thus, in particular, in a (right in FIG. 1) portion of inner ring segment 10 that extends from a second end face 12 of inner ring segment 10 to this inner guide vane 24, as well as at most over a second outermost third of length L bounded by second end face 12 of inner ring segment 10, in particular at most from inner boundary b.sub.i thereof facing away from second end face 12 thereof, to second outermost guide vane 25. Outer boundary b.sub.a thereof facing second end face 12 is spaced apart from second end face 12 by at least 1 mm.

[0059] Although exemplary embodiments are explained in the preceding description, it should be noted that many modifications are possible.

[0060] Thus, in particular, it is also possible for only one housing 110 having cavities 112, respectively impulse elements 100 accommodated therein to be provided; or for the guide vane segment to only have one single detuning region (A or B).

[0061] Similarly, in one variation, cavities 112 may also be directly formed in inner ring segment 10, respectively impulse elements 100 directly configured in inner ring segment 10 without a separately produced housing 110.

[0062] It should also be appreciated that the exemplary embodiments are merely examples, and are in no way intended to restrict the scope of protection, the uses or the design. Rather, the foregoing description provides one skilled in the art with a guideline for realizing at least one exemplary embodiment, various modifications being possible, particularly with regard to the function and configuration of the described components, without departing from the scope of protection as is derived from the claims and the combinations of features equivalent thereto.

LIST OF REFERENCE NUMERALS

[0063] 10 inner ring segment

[0064] 11 first end face

[0065] 12 second end face

[0066] 21 first outermost guide vane

[0067] 22 inner guide vane

[0068] 23 guide vane

[0069] 24 inner guide vane

[0070] 25 second outermost guide vane

[0071] 100 impulse element

[0072] 110 housing

[0073] 111 cover

[0074] 112 cavity

[0075] 1000 aircraft engine gas turbine

[0076] A first detuning region

[0077] a.sub.a/i outer/inner boundary

[0078] B second detuning region

[0079] b.sub.a/i outer/inner boundary

[0080] L length