Guide vane segment

Patent metadata

Field	Value
Publication number	US-11002140-B2
Application number	US-201715483478-A
Country	US
Kind code	B2
Filing date	Apr 10, 2017
Priority date	Apr 11, 2016
Publication date	May 11, 2021
Grant date	May 11, 2021

Abstract

A guide vane segment for a turbomachine stage that has an inner ring segment ( 10 ) and a plurality of guide vanes ( 20 ) that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge ( 21 ) of at least one guide vane ( 20 ), in particular of at least 50% of the guide vanes ( 50 ), axially toward a leading edge ( 22 ) of the guide vane ( 20 ) over at most 50% of a width (B) of the inner ring segment ( 10 ) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes ( 20 ), at and/or in which 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; and
a plurality of guide vanes on the inner ring segment;
at least one detuning region of the inner ring segment, each of said at least one detuning regions extending and starting from a trailing edge of a respective guide vane of the plurality of guide vanes, axially toward a leading edge of the respective guide vane over at most 30% of a width of the inner ring segment, or extending over at most 5 mm,
at least one cavity at or in the at least one detuning region and containing at least one impulse element with clearance of motion;
wherein the at least one impulse element is a spherical ball.

2. The guide vane segment as recited in claim 1 wherein at least 75% of a number of the at least one impulse element at or in the inner ring segment are located in the at least one detuning region.

3. The guide vane segment as recited in claim 1 wherein the at least one cavity contains exactly one of the at least one impulse element.

4. The guide vane segment as recited in claim 1 further comprising a housing attached to the inner ring segment, wherein the at least one cavity is in the housing.

5. The guide vane segment as recited in claim 4 wherein the at least one cavity is airtight.

6. The guide vane segment as recited in claim 1 further comprising at least one housing, a total number of the at least one housing being less than or equal to a number of the plurality of guide vanes.

7. The guide vane segment as recited in claim 6 wherein the total number of the at least one housing is less by one than the number of the plurality of guide vanes.

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

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

10. The guide vane segment as recited in claim 1 wherein the 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 at least one impulse element, and at most 10 mm or at most 100% of a maximum diameter of the at least one impulse element.

11. The guide vane segment as recited in claim 1 wherein the at least one impulse element detunes airfoil modes of the guide vane segment.

12. A turbomachine stage comprising at least one guide vane segment as recited in claim 1 .

13. A compressor or turbine stage comprising the turbomachine stage as recited in claim 12 .

14. A turbomachine comprising at least one turbomachine stage as recited in claim 12 .

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

16. An aircraft engine gas turbine comprising the gas turbine as recited in claim 15 .

17. The guide vane segment as recited in claim 1 wherein the at least one impulse element is made of Al 2 O 3 .

18. The guide vane segment as recited in claim 1 wherein the at least one impulse element is made of CrO 2 .

Assignees

• MTU Aero Engines AG

Inventors

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

Classifications

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01D5/26 Primary

  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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D25/06

  for preventing blade vibration (means on blade-carrying members or blades F01D5/00) · CPC title