Impulse element module for a turbomachine

Patent metadata

Field	Value
Publication number	US-10570752-B2
Application number	US-201715587724-A
Country	US
Kind code	B2
Filing date	May 5, 2017
Priority date	May 9, 2016
Publication date	Feb 25, 2020
Grant date	Feb 25, 2020

Abstract

An impulse element module for a turbomachine, in particular a turbine stage of a gas turbine, preferably an aircraft gas turbine, including a single-unit receptacle component having a base and side walls that extend peripherally thereon, the side walls and the base bounding a receiving space; a single-unit insert component having a form that is inserted into receiving space of receptacle component; together, the receptacle component and the insert component accommodated therein being designed to define a plurality of spaced apart cavities; and an impulse element, in particular a sphere, being accommodated in each cavity; and a single-unit sealing component that is joined in a material-to-material bond to the receptacle component in a way that allows the receiving space to be sealed and the insert component to be surrounded by the receptacle component and the sealing component.

First claim

What is claimed is:

1. An impulse element module installed in an installation space of a rotor blade assembly of a turbomachine, the impulse element module comprising
a single-unit receptacle component having a base and side walls extending peripherally thereon, the side walls and the base bounding a receiving space;
a single-unit insert component inserted into a receiving space of the receptacle component; together, the receptacle component and the insert component accommodated therein being designed to define a plurality of spaced apart cavities; and an impulse element being accommodated in each cavity; and
a single-unit seal component joined in a material-to-material bond to the receptacle component to allow the receiving space to be sealed, and the insert component to be surrounded by the receptacle component and the seal component.

2. The impulse element module as recited in claim 1 wherein the insert component has a terminating wall, the terminal wall, in the inserted state of the insert component in the receptacle component, sealing the receiving space.

3. The impulse element module as recited in claim 2 wherein the terminating wall, via an outer side facing away from the receiving space, ending flush with at least one front face of the side walls of the receptacle component, the side walls being surrounding side walls.

4. The impulse element module as recited in claim 2 wherein the terminating wall, at an inner side facing the receiving space, has a plurality of webs projecting from the inner side.

5. The impulse element module as recited in claim 4 wherein the webs include longitudinal and transverse webs.

6. The impulse element module as recited in claim 1 wherein the base and the side walls of the receptacle component have a flat form on inner surfaces thereof facing the receiving space.

7. The impulse element module as recited in claim 6 wherein the insert component has a plurality of longitudinal webs and transverse webs forming a grid-like structure; the longitudinal webs and the transverse webs, together with at least one of inner surfaces of the base or of the side walls, bounding the plurality of cavities, at least in portions thereof.

8. The impulse element module as recited in claim 1 wherein on an inner surface facing the receiving space, the base has a plurality of webs projecting into the receiving space to allow the webs and the inner surface of the base to form a partial volume of the plurality of cavities.

9. The impulse element module as recited in claim 8 wherein the webs include longitudinal and transverse webs.

10. The impulse element module as recited in claim 2 wherein the insert component has a plurality of webs and the receptacle component has a plurality of other webs; wherein the insert component and the receptacle component are configured in a way that allows front faces of the plurality of webs of the insert component and other front faces of the other plurality of webs of the receptacle component to rest against each other in the inserted state of the insert component, in a way that allows the plurality of cavities to be bounded by the webs of the insert component, the other webs of the receptacle component, an inner surface of the base and by an inner side of the terminating wall.

11. The impulse element module as recited in claim 2 wherein the seal component is joined in a material-to-material bond to the terminating wall of the insert component.

12. The impulse element module as recited in claim 1 wherein the receptacle component, the insert component, and the seal component are additively manufactured.

13. The impulse element module as recited in claim 1 wherein the receptacle component, the insert component, and the seal component are additively manufactured by a selective laser melting process.

14. The impulse element module as recited in claim 1 wherein the receptacle component or the insert component or the seal component is at least partially manufactured in a machining process or in a powder metal injection molding process.

15. The impulse element module as recited in claim 14 wherein the receptacle component or the insert component or the seal component is at least partially manufactured in a machining process, the machining process being electrochemical machining.

16. The impulse element as recited in claim 1 wherein the impulse element is a sphere.

17. A method for manufacturing an impulse element module for a turbomachine, the method comprising the steps of:
manufacturing a receptacle component by building up the receptacle component layer by layer using an additive manufacturing process, the receptacle component having a base and side walls extending peripherally thereon; the side walls being built up starting from the base to allow a receiving space to be formed within the side walls;
manufacturing an insert component grid-like at least in portions by building up the insert component layer by layer using the additive manufacturing process;
inserting the insert component into the receiving space of the receptacle component; prior to or during the insertion, impulse elements being inserted into cavities jointly formed by the receptacle component and the insert component;
using the additive manufacturing process to build up a seal component layer by layer on the receptacle component having the insert component inserted therein, to mutually join the receptacle component and the seal component in a material-to-material bond and form a single-unit enclosure for the insert component and the impulse elements contained therein.

18. The method as recited in claim 17 wherein the additive manufacturing process is a selective laser melting process.

19. The method as recited in claim 18 wherein the impulse elements are spheres.

20. A rotor blade assembly of a compressor stage or of a turbine stage of a gas turbine, comprising:
a depression, the impulse element module as recited in claim 1 being inserted in the depression, the depression defining at least a part of the installation space.

21. The rotor blade assembly as recited in claim 20 wherein the depression is in a rotor blade root region.

22. A gas turbine comprising the impulse element module as recited in claim 1 associated with a compressor stage or a turbine stage.

23. The gas turbine as recited in claim 22 wherein a plurality of impulse element modules are associated with a rotor component.

24. The gas turbine as recited in claim 23 wherein the rotor component is in a rotor blade ring, a compressor stage or a turbine stage.

25. The gas turbine as recited in claim 22 wherein a single impulse element module is associated with a single rotor blade assembly of the rotor blade ring.

26. An aircraft gas turbine comprising the gas turbine of claim 22 .

Assignees

• MTU Aero Engines AG

Inventors

• Roesele Gerhard-Heinz
• Schlemmer Markus
• Hartung Andreas

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

• F16F7/10

  using inertia effect (F16F13/108, F16F13/22, F16F15/10, F16F15/22 take precedence; stabilising vehicle bodies by means of movable masses B62D37/04; protection of buildings against vibrations or shocks by mass dampers E04H9/0215; arrangements or devices for damping mechanical oscillations of power lines H02G7/14) · CPC title

• F04D29/668

  damping or preventing mechanical vibrations · CPC title