TURBOMACHINE BLADE SYSTEM

Abstract

A turbomachine blade system, in particular for a compressor or turbine stage of a gas turbine, which includes at least one blade, in particular a moving or guide blade, and at least one moving body for reducing the vibrations of this blade, at least one area of a guide for guiding the body and/or at least one area of a supporting structure for resiliently mounting the body and/or at least one area of the body being or becoming generatively manufactured together with at least one area of the blade, in particular of a vane and/or blade root and/or a shroud situated thereon.

Claims

1. A turbomachine blade system comprising: at least one blade; a cavity radially inward of the blade; and at least one moving body for reducing the vibrations of the blade and located in the cavity, at least one area of the body being generatively manufactured together with at least one area of the blade, the moving body being a spherical body with a diameter larger than a maximum clearance in an axial or circumferential direction of the spherical body in the cavity.

2. The turbomachine blade system as recited in claim 1 wherein the body is an impulse body for reducing the vibrations of the blade through multiple impact contacts.

3. The turbomachine blade system as recited in claim 1 wherein the generatively manufactured area of the blade has a contact surface for contacting the body.

4. The turbomachine blade system as recited in claim 1 wherein the generatively manufactured area of the blade, or the generatively manufactured area of the body includes metal.

5. The turbomachine blade system as recited in claim 4 wherein the generatively manufactured area of the blade or the generatively manufactured area of the body is manufactured from metal powder.

6. The turbomachine blade system as recited in claim 1 wherein the body is in a closed hollow space defined by a guide connected to the blade, the body being situated with the maximum clearance in the axial and circumferential direction in the closed hollow space.

7. The turbomachine blade system as recited claim 1 wherein a maximum outer dimension of the body is larger than a maximum inner dimension of a through-opening of a wall of a hollow space defined by a guide in the cavity, the hollow space being an open hollow space.

8. The turbomachine blade system as recited in claim 1 wherein the body, a guide or the supporting structure is situated in the cavity, the cavity at least partially defined by the blade.

9. The turbomachine blade system as recited in claim 1 wherein the body, a guide or the supporting structure is situated in the cavity, the cavity being a closed cavity at least partially defined by the generatively manufactured area of the blade.

10. The turbomachine blade system as recited in claim 1 wherein the blade is a moving blade.

11. The turbomachine blade system as recited in claim 1 wherein the blade is a guide blade.

12. The turbomachine blade system as recited in claim 1 wherein the generatively area of the blade is on a vane or blade root or a shroud.

13. A compressor or turbine stage of a gas turbine comprising the turbomachine blade system as recited in claim 1.

14. A turbomachine comprising at least one turbomachine blade system as recited in claim 1.

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

16. A method for manufacturing a turbomachine blade system as recited in claim 1 wherein the area of the guide, the supporting structure or the body is generatively manufactured together with the area of the blade.

17. A turbomachine blade system comprising: at least one blade; a cavity radially inward of the blade; and at least one moving body for reducing the vibrations of the blade and located in the cavity, at least one area of the body being generatively manufactured together with at least one area of the blade, the moving body being a spherical body connected to the cavity via a supporting structure, a diameter of the moving body being larger than a minimum thickness of the supporting structure.

18. The turbomachine blade system as recited in claim 17 wherein the minimum thickness is at most 50% of the diameter.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Further advantageous refinements of the present invention are derived from the subclaims and the following description of preferred embodiments, showing a partially schematic illustration.

[0047] FIG. 1 shows a section of a turbomachine blade system of a gas turbine according to one embodiment of the present invention; and

[0048] FIG. 2 shows a section of a turbomachine blade system of a gas turbine according to another embodiment of the present invention.

DETAILED DESCRIPTION

[0049] FIG. 1 shows a section of a turbomachine blade system of a gas turbine according to one embodiment of the present invention, including a moving or guide blade 10, of which one section of a vane 11, a blade root 12 and a shroud 13 situated thereon are illustrated in FIG. 1.

[0050] Blade root 12 is situated on a housing or rotor 2 and defines a closed cavity 3 therewith.

[0051] Situated in cavity 3 is a guide 50 for movably guiding a body 4 to reduce vibrations of blade 10 due to multiple impact contacts therewith, the cavity including an open hollow space 51, in which spherical body 4 is situated with clearance in a translatory degree of freedom (vertical in FIG. 1) and three rotational degrees of freedom, one part of blade root 12 or shroud 13 having or forming a contact surface 14 for contacting body 4.

[0052] As is indicated in the partially schematic representation in FIG. 1, the outer diameter of spherical body 4 is larger than a maximum inner diameter or inside width of a through-opening 52 of a wall 53 of the guide or the open hollow space and is also larger than a maximum clearance s of body 4 in guide 50 or hollow space 51.

[0053] Vane 11, blade root 12, shroud 13, (wall 52 of) guide 50 or hollow space 51 and (impulse) body 4 will be or are generatively manufactured together from metal powder. Body 4, in particular, may be captively manufactured or situated in hollow space 51 in one work step. By subsequently connecting blade root 12 to the housing or rotor 2 or cavity 3 defined hereby, body 4 is advantageously protected against working fluid of the gas turbine in open hollow space 51.

[0054] In a manner corresponding to FIG. 1, FIG. 2 shows a section of a turbomachine blade system of a gas turbine according to another embodiment of the present invention. Corresponding features are identified by identical reference numerals, so that reference is hereby made to the preceding description and only the differences are discussed below.

[0055] In the embodiment in FIG. 2, spherical body 4 is not mounted in a guide but rather elastically supported or connected on blade root 12 in cavity 3 by a thin-walled supporting structure 6, which will be or is generatively manufactured from metal powder together with vane 11, blade root 12, shroud 13 and (impulse) body 4.

[0056] Body 4, in particular, may in turn be captively manufactured or situated in cavity 3 in one work step. By subsequently connecting blade root 12 to the housing or rotor 2, body 4 and supporting structure 6 are, in turn, advantageously protected against working fluid of the gas turbine.

[0057] While the description above explained exemplary embodiments, it should be pointed out that a plurality of modifications is possible.

[0058] For example, body 4 in the embodiments in FIGS. 1, 2 may also be situated in vane 11 or a diametrically opposed (additional) shroud (not illustrated) instead of on a side of blade root 12 facing away from the vane, which is or will be generatively manufactured at least partially together with the guide or supporting structure for this purpose.

[0059] Additionally or alternatively, guide 50, in particular in the embodiment in FIG. 1, or supporting structure 6 in the embodiment in FIG. 2, which each define (impact) kinematics, may be eliminated, and (impulse) body 4 accommodated in cavity 3 may be or become generatively manufactured together with (at least) one area of blade 10, for example blade root 12, shroud 13 and/or vane 11 or a part thereof.

[0060] Moreover, it should be pointed out that the exemplary embodiments are only examples which are not intended to limit the scope of protection, the applications and the design in any way. Rather, the description above gives those skilled in the art a guideline for implementing at least one exemplary embodiment, various modifications being possible, in particular with respect to the function and positioning of the described components, without departing from the scope of protection as it is derived from the claims and feature combinations equivalent to the claims.

LIST OF REFERENCE NUMERALS

[0061] 10 blade [0062] 11 vane [0063] 12 blade root [0064] 13 shroud [0065] 14 contact surface [0066] 2 housing/rotor [0067] 3 cavity [0068] 4 (impulse) body [0069] 50 guide [0070] 51 hollow space [0071] 52 opening [0072] 53 wall [0073] 6 supporting structure [0074] s (maximum) clearance