Integrally Bladed Turbomachine Rotor

Abstract

An integrally bladed rotor for a turbomachine, in particular a compressor or turbine stage of a gas turbine, to which at least one separately formed impulse element housing (40; 40′) is fastened by at least one fastening element (30; 30′) which engages for this purpose into an opening (41) of the impulse element housing and into an opening (11) of the rotor, the impulse element housing having at least one cavity (44) in which at least one impulse element (5) is accommodated with play.

Claims

1-11. (canceled)

12. A rotor for a turbomachine comprising: an integrally bladed rotor and at least one separately formed impulse element housing fastened to the integrally bladed rotor by at least one fastening element engaging for fastening into an opening of the impulse element housing and into an opening of the integrally bladed rotor, the impulse element housing having at least one cavity, at least one impulse element being accommodated with play in theat least one cavity.

13. The rotor as recited in claim 12 wherein the impulse element housing is disposed on an outer or inner axial end face of the integrally bladed rotor.

14. The rotor as recited in claim 12 wherein the impulse element housing is disposed radially under an inner shroud of the integrally bladed rotor.

15. The rotor as recited in claim 12 wherein the cavity is spaced in the circumferential direction from a leading or trailing edge of a nearest blade of the integrally bladed rotor by no more than 25% of a blade pitch.

16. The rotor as recited in claim 12 wherein the impulse element housing is frictionally fastened to the integrally bladed rotor

17. The rotor as recited in claim 12 wherein the fastening element includes a threaded bolt or a rivet.

18. The rotor as recited in claim 12 wherein the opening of the integrally bladed rotor has a closed periphery or a radially inwardly open slot.

19. The rotor as recited in claim 12 wherein the opening of the integrally bladed rotor is disposed in an annular flange of the rotor.

20. The rotor as recited in claim 19 wherein the opening is disposed in a radially enlarged portion of the annular flange.

21. The rotor as recited in claim 12 wherein the fastening element extends through a through-opening of the impulse element housing defining the opening of the impulse element housing or a through-opening of the integrally bladed rotor defining the opening of the integrally bladed rotor.

22. The rotor as recited in claim 12 wherein the impulse element housing has on either circumferential side of the opening of the impulse element housing the at least one cavity accommodating at least one impulse element with play.

23. The rotor as recited in claim 12 wherein the impulse element housing has at least two radially offset cavities of the at least one cavity, each accommodating at least one impulse element with play.

24. The rotor as recited in claim 12 wherein the impulse element housing has each at least two parts together bounding the cavity and connected together.

25. The rotor as recited in claim 12 wherein the at least two parts are connected together by the fastening element.

26. The rotor as recited in claim 12 wherein the at least two parts are connected together by a material-to-material bond.

27. The rotor as recited in claim 12 wherein the impulse body housing is ring-like or box-like.

28. A compressor or turbine stage of a gas turbine comprising the rotor as recited in claim 12.

29. A turbomachine comprising the rotor as recited in claim 12.

30. A gas turbine comprising the rotor as recited in claim 12.

31. A method for reducing vibrations of the rotor as recited in claim 12 comprising fastening the at least impulse element housing , the at least one housing being separately formed, to the integrally bladed rotor by the at least one fastening element , the fastening element being, at least partially inserted into the opening of the impulse element housing and into the opening of the rotor.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Further advantageous refinements 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:

[0046] FIG. 1 an axial elevation view of a portion of an integrally bladed turbomachine rotor in accordance with an embodiment of the present invention;

[0047] FIG. 2 a view of an impulse element housing fastened to the rotor, as seen radially from the inside;

[0048] FIG. 3 various grid views of the impulse element housing;

[0049] FIG. 4 a view similar to FIG. 1 of a portion of an integrally bladed turbomachine rotor in accordance with another embodiment of the present invention; and

[0050] FIG. 5 a view similar to FIG. 1 of a portion of an integrally bladed turbomachine rotor in accordance with a further embodiment of the present invention; and

[0051] FIG. 6 a view similar to FIG. 1 of a portion of an integrally bladed turbomachine rotor in accordance with another embodiment of the present invention.

DETAILED DESCRIPTION

[0052] FIG. 1 shows an axial elevation view of a portion of an integrally bladed turbomachine rotor in accordance with an embodiment of the present invention.

[0053] The visible parts of the rotor as seen in FIG. 1 are, in particular, a radially inner shroud 1 having an annular flange 10 and leading and trailing edges 2 of blades formed integrally therewith.

[0054] Radially enlarged portions of annular flange 10 have formed therein respective through-openings having a radially inwardly open slot 11. In a modification, the openings have a closed periphery (see also FIG. 6).

[0055] A fastening element in the form of a threaded bolt 30 extends through each of these rotor (through-)openings 11 and also through a through-opening 41 in a separately formed, box-like impulse element housing 40.

[0056] Impulse element housings 40 each have a base 42 and a cover 43, which together bound four cavities 44, in each of which an impulse element 5 is accommodated with play (see FIG. 3).

[0057] Base 42 and cover 43 are welded together airtight along an outer periphery and along a periphery of impulse element housing opening 41, respectively, as indicated by welded seams 45.

[0058] Annular flanges or heads 31 of the threaded bolts 30 are supported on impulse element housings 40 or their covers 43. On the axially opposite side, threaded bolts 30 are threadedly connected to threaded nuts 32.

[0059] FIG. 4 shows in a view similar to FIG. 1 a portion of an integrally bladed turbomachine rotor in accordance with another embodiment of the present invention. Corresponding elements are identified by identical reference numerals, so that reference is made to the above description and only the differences will be discussed below.

[0060] In the embodiment of FIGS. 4, a ring-like impulse element housing 40′ is fastened to the annular flange 10 of the rotor by threaded bolts 30 distributed equidistantly around the circumference thereof. The cavities in impulse element housing 40′ are arranged under the respective blade edges 2 in the same way as in the embodiment of FIG. 1.

[0061] FIG. 5 shows in a view similar to FIGS. 1, 4 a portion of an integrally bladed turbomachine rotor in accordance with a further embodiment of the present invention. Corresponding elements are identified by identical reference numerals, so that reference is made to the above description and only the differences will be discussed below.

[0062] In the embodiment of FIG. 5, impulse element housings 40 are disposed on an outer axial end face of the rotor.

[0063] While exemplary embodiments have been presented in the foregoing detailed description, it should be noted that many modifications are possible.

[0064] For example, impulse element housing 40′ may also be disposed on an outer axial end face.

[0065] Additionally or alternatively, threaded bolts 30 may also be screwed in in the opposite direction, and their annular flanges or heads 31 may be supported on annular flange 10.

[0066] In a modification, rivets 30′ may also be used instead of threaded bolts 30, as exemplarily indicated in FIG. 6, which otherwise corresponds to FIG. 5.

[0067] Additionally or alternatively, the impulse element housings may also rest with their cover against annular flange 10 instead of with their base.

[0068] It should also be appreciated that the exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing at least one exemplary embodiment, it being understood that various changes may be made in the function and arrangement of elements described without departing from the scope of protection as set forth in the appended claims or derived from combinations of features equivalent thereto.

LIST OF REFERENCE NUMERALS

[0069] 1 shroud

[0070] 10 annular (rotor) flange

[0071] 11 opening (slot)

[0072] 2 leading/trailing blade edge

[0073] 30 threaded bolt (fastening element)

[0074] 30′ rivet (fastening element)

[0075] 31 annular flange

[0076] 32 threaded nut

[0077] 40; 40′ impulse element housing

[0078] 41 (impulse element housing) opening

[0079] 42 impulse element housing base

[0080] 43 impulse element housing cover

[0081] 44 cavity

[0082] 45 welded seam

[0083] 5 impulse element