Guide vane segment

Patent metadata

Field	Value
Publication number	US-10550720-B2
Application number	US-201715483565-A
Country	US
Kind code	B2
Filing date	Apr 10, 2017
Priority date	Apr 11, 2016
Publication date	Feb 4, 2020
Grant date	Feb 4, 2020

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.

First claim

What is claimed is:

1. 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;
wherein the at least one impulse element is spherical in shape and wherein a clearance of motion of the at least one impulse element is at most 10 mm or at most 100% of a maximum diameter of the impulse element.

2. The guide vane segment as recited in claim 1 wherein the detuning region extends from an inner boundary facing away from the end face at most to the outermost guide vane.

3. The guide vane segment as recited in claim 1 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.

4. The guide vane segment as recited in claim 1 wherein at least 25% of all impulse elements configured at or in the inner ring segment are located at or in the detuning region.

5. The guide vane segment as recited in claim 1 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.

6. The guide vane segment as recited in claim 1 wherein the at least one impulse element is accommodated unrestrainably in a cavity.

7. The guide vane segment as recited in claim 1 wherein the at least cavity is configured in a separately produced housing.

8. The guide vane segment as recited in claim 7 wherein the at least one cavity is air-tight.

9. The guide vane segment as recited in claim 1 wherein the impulse element has a mass of at least 0.01 g or of at most of 0.05 g.

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

11. The guide vane segment as recited in claim 1 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.

12. The guide vane segment as recited in claim 1 wherein the at least one impulse element is designed for detuning cluster modes of the guide vane segment.

13. A turbomachine stage comprising the guide vane segment as recited in claim 1 .

14. A compressor or turbine stage comprising the turbomachine stage as recited in claim 13 .

15. A turbomachine comprising the turbomachine stage as recited in claim 13 .

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

17. An aircraft engine gas turbine comprising the gas turbine as recited in claim 16 .

18. 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 two cavities each containing at least one impulse element with clearance of motion for providing impact contacts, the at least two cavities being at or in at least one detuning region of the inner ring segment; a first 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, at least a first of the two cavities being in the first detuning region; and a second detuning region extending circumferentially in a portion of the inner ring segment between a second outermost guide vane of the guide vanes and a second inner guide vane of the guide vanes circumferentially adjacent to the second outermost guide vane, a second of the cavities being in the second detuning region.

Assignees

• MTU Aero Engines AG

Inventors

• Schlemmer Markus
• Hartung Andreas
• Richter Karl-Hermann
• Hanrieder Herbert

Classifications

• F05D2230/51

  in a modular way, e.g. using several identical or complementary parts or features · CPC title

• F01D5/16

  for counteracting blade vibration · CPC title

• F05D2250/241

  spherical · 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

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title