ROTOR DISK AND ROTOR BLADE FOR A GAS TURBINE COMPRESSOR OR TURBINE STAGE OF AN AEROENGINE

Abstract

A method for producing a rotor disk or a rotor blade for a gas turbine compressor stage or turbine stage of an aeroengine, wherein at least one blade groove of the rotor disk for arrangement of a blade foot of a rotor blade for fastening the rotor blade to the rotor disk, or a blade foot of the rotor blade for arrangement in a blade groove of a rotor disk for fastening the rotor blade to the rotor disk is fabricated using an electrochemical material removal and in the axial direction has a profile which is curved once or more.

Claims

1.-15. (canceled)

16. A method for producing (i) a rotor disk or (ii) a rotor blade for a gas turbine compressor stage or turbine stage of an aeroengine, wherein the rotor disk (i) comprises at least one blade groove for arrangement of a blade foot of a rotor blade for fastening the rotor blade to the rotor disk, the blade groove produced by using an electrochemical material removal and in an axial direction having a profile which is curved once or more; or wherein the rotor blade (ii) comprises a blade foot for arrangement in a blade groove of a rotor disk for fastening the rotor blade to the rotor disk, the blade foot produced by using an electrochemical material removal and in an axial direction having a profile which is curved once or more.

17. The method of claim 16, wherein the rotor disk (i) is produced.

18. The method of claim 16, wherein the rotor blade (ii) is produced.

19. The method of claim 16, wherein the curved profile has or is a circular path around a circle center point and/or runs at least in part within a plane.

20. The method of claim 19, wherein the circle center point, as viewed in an axial direction and/or radial direction, lies within the disk to be produced.

21. The method of claim 19, wherein the circle center point, as viewed in an axial direction and/or radial direction, lies outside the disk to be produced.

22. The method of claim 19, wherein the plane runs parallel to an axial direction and/or runs perpendicularly to a radial direction.

23. The method of claim 19, wherein the plane runs at a tilt to an axial direction.

24. The method of claim 16, wherein at least a portion of a contour of the blade groove of the disk to be produced or of the blade foot of the rotor blade to be produced is finished by means of electrochemical material removal and/or the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced is generated by means of electrochemical material removal.

25. The method of claim 16, wherein the electrochemical material removal for fabricating the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced comprises a PECM, pulse ECM, ECF and/or ECDM method.

26. The method of claim 16, wherein a tool for electrochemical material removal, for fabricating the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced has a curved contour and/or is guided over a curved path, and/or the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced has a circle segment-shaped profile.

27. The method of claim 26, wherein a radius of the circle segment is at least half and/or at most 100 times an axial distance between an upstream axial end face of the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced and a downstream axial end face of the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced and/or a center point of the circle segment has a distance from an axial center of the rotor disk to be produced or the blade foot of the rotor blade to be produced in an axial direction which is at most equal to a difference of a radius of the circle segment minus half an axial distance between an upstream axial end face of the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced and a downstream axial end face of the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced.

28. The method of claim 16, wherein an upstream axial end face of the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced is not offset in relation to a downstream axial end face of the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced is offset in or against a rotation direction and/or has an axial distance of at least 10 mm and/or at most 100 mm.

29. The method of claim 16, wherein the blade groove of the disk to be produced or the blade foot of the rotor blade to be produced has, at least in some portions, an average roughness value of at most 2.0 μm, and/or the blade groove and/or the blade foot, in a radial direction, comprises one or more undercuts.

30. A rotor disk for a gas turbine compressor stage or turbine stage of an aeroengine, wherein the rotor disk is produced by the method of claim 16.

31. The rotor disk of claim 30, wherein the blade groove runs partially or fully over its cross section continuously in an axial direction through the rotor disk.

32. A rotor blade for a gas turbine compressor stage or turbine stage of an aeroengine, wherein the rotor blade is produced by the method of claim 16.

33. A gas turbine compressor stage or turbine stage for an aeroengine with at least one rotor disk and at least one rotor blade with a blade foot, which for fastening of the rotor blade to the rotor disk is arranged in a blade groove of the rotor disk, wherein the rotor disk is a rotor disk according to claim 30.

34. A gas turbine compressor stage or turbine stage for an aeroengine with at least one rotor disk and at least one rotor blade with a blade foot, which for fastening of the rotor blade to the rotor disk is arranged in a blade groove of the rotor disk, wherein the rotor blade is a rotor blade according to claim 32.

35. An aeroengine gas turbine with at least one rotor disk and/or rotor blade produced in accordance with the method of claim 16.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0091] Further advantageous refinements of the present invention will become clear from the dependent claims and the following description of preferred embodiments. To this end, the figures show, partly in schematized form:

[0092] FIG. 1 a plan view of a lateral surface of a rotor disk according to an embodiment of the invention;

[0093] FIG. 2 a partial section of a blade groove of the rotor disk along line II-II in FIG. 1;

[0094] FIG. 3 a plan view corresponding to FIG. 1 during production of the rotor disk;

[0095] FIG. 4 the bladed rotor disk; and

[0096] FIG. 5 part of a rotor blade according to an embodiment of the present invention.

DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS

[0097] The particulars shown herein are by way of example and for purposes of illustrative discussion of the embodiments of the present invention only and are presented in the cause of providing what is believed to be the most useful and readily understood description of the principles and conceptual aspects of the present invention. In this regard, no attempt is made to show details of the present invention in more detail than is necessary for the fundamental understanding of the present invention, the description in combination with the drawings making apparent to those of skill in the art how the several forms of the present invention may be embodied in practice.

[0098] FIG. 1 shows a plan view of a lateral surface of a rotor disk 1 for a gas turbine compressor stage or turbine stage of an aeroengine according to an embodiment of the present invention.

[0099] The rotor disk 1 comprises blade grooves 2 distributed in the circumferential direction (vertically in FIG. 1) for fastening rotor blades 3 to the rotor disk, which rotor blades have a curved, circle segment-shaped profile in the axial direction (horizontally in FIG. 1), wherein a radius R of the (particular) circle segment is preferably at least c/2 and/or 100c, in particular at most 50c, in one embodiment at most 30c, in a refinement at most 20c and in one embodiment at most 5c, and/or a center point M of the circle segment has a distance a from an axial center of the rotor disk in the axial direction (in each case) of at most (R-c/2), in particular (R-c), in one embodiment at most (R-5c).

[0100] Here, c denotes the axial distance between an upstream axial end face 2.2 of a blade groove and a downstream axial end face 2.3 of said blade groove.

[0101] FIG. 2 shows, in a partial section along line II-II in FIG. 1, a cross section of one of the homogeneous(ly produced) blade grooves 2 with a fir tree profile.

[0102] To produce the rotor disks, core regions 2a of the grooves 2 can first be milled, as indicated in the upper part of FIG. 3. In a preferred embodiment, core regions 2a can also be produced additionally or particularly preferably alternatively by means of electrochemical material removal.

[0103] A tool 4, which has a curved contour corresponding to the circle segment, is then guided by means of a guide 5, which is merely symbolized very schematically, along a correspondingly curved circular path of radius R and with a center point M in order to finish the contour of the particular blade groove 2, in particular its groove flanks 2.1 (see FIG. 2) by means of electrochemical material removal. The radius R and center point M serve here merely to define the trajectory and expressly are not intended to imply a specific design of the manufacturing machine. The radius R and/or center point M in particular can be (purely) virtual.

[0104] In an alternative, particularly preferred embodiment, the blade grooves 2 can also be generated by means of electrochemical material removal, i.e., without prior milling out or electrochemical material removal of core regions 2a. In one embodiment, the fabrication time can thus be reduced. Correspondingly, in FIG. 3 the core regions 2a are shown by dashed lines in order to indicate that these or their prior forming is omitted in a particularly preferred embodiment.

[0105] The upstream axial, open end face 2.2 of the blade grooves 2 are offset in relation to the downstream axial open, end face 2.3 of the particular blade groove in the circumferential direction by b and in the axial direction have the spacing c (see FIG. 1). The axial distance, not shown separately in the drawings, between an upstream axial end face of the blade foot and a downstream axial end face of the blade foot can likewise be c, for example.

[0106] FIG. 4 shows a heavily schematized view of the rotor disk 1 fitted with blades 3 in an axial plan view.

[0107] FIG. 5 shows, in a (rotated) section corresponding to FIG. 2, part of one of the rotor blades 3 or blade foot 3A thereof with blade foot flanks 3.1.

[0108] As is the case throughout the entire disclosure, the descriptions provided in respect of the rotor disk and blade groove(s) thereof apply similarly to the rotor blade and blade foot thereof, and vice versa. Nevertheless, it is noted that the rotor disk and rotor blade aspects can also each be provided independently and therefore are expressly also claimed independently. In particular, a rotor disk described here can be fitted with rotor blades fabricated in a different way or a rotor blade described here can be fitted with a rotor disk fabricated in a different way, wherein, in particular on account of mutually corresponding surfaces and/or jointly used fabrication equipment, both aspects advantageously can be provided jointly and therefore expressly also claimed jointly.

[0109] Although exemplary embodiments have been explained in the foregoing description, it is noted that a large number of modifications are possible. In addition, it is noted that the exemplary embodiments are merely examples which are not in any way intended to limit the scope of protection, the applications, or the design. Rather, the foregoing description is intended to provide a person skilled in the art with a guideline for implementing at least one exemplary embodiment, wherein various modifications, in particular in respect of the function and arrangement of the described components, can be made without departing from the scope of protection, as is evident from the claims and feature combinations equivalent thereto.

LIST OF REFERENCE SIGNS

[0110] 1 rotor disk

[0111] 2 blade groove

[0112] 2a core region

[0113] 2.1 groove flank

[0114] 2.2 upstream blade groove end face

[0115] 2.3 downstream blade groove end face

[0116] 3 rotor blade

[0117] 3A blade foot

[0118] 3.1 blade foot flank

[0119] 4 tool

[0120] 5 guide (symbolic)

[0121] a axial distance between rotor disk center and center point

[0122] b distance between upstream and downstream blade groove end face in circumferential direction

[0123] c axial distance between upstream and downstream blade groove end face

[0124] M center point

[0125] R radius