Method for the production of a rotor and rotor

Abstract

A method for producing a rotor, particularly a turbine disk or a turbine ring for a turbine stage of a turbomachine, wherein at least the following steps are carried out: producing a blade ring (14) including a plurality of rotor blades (12), welding adapters (22) together which are disposed in the region of blade footings of the rotor blades (12), wherein at least substantially radial weld seams (30a) having predetermined welding depths are generated, disposing a rotor disk (32) or a rotor ring on the blade ring (14), and welding the rotor disk (32) or the rotor ring to the adapters (22) of the rotor blades (12), wherein at least one further weld seam (30b) is generated. A rotor, particularly a turbine disk or a turbine ring for a turbine stage of a turbomachine is also disclosed.

Claims

1. A method for the production of a rotor comprising the following steps: producing a blade ring comprising a plurality of rotor blades; welding together adapters arranged in an area of roots of the rotor blades to create at least essentially radial weld seams having predefined welding depths; positioning a rotor disk or a rotor ring on the blade ring; and welding the rotor disk or the rotor ring to the adapters of the rotor blades to create at least one additional weld seam, wherein the rotor disk or the rotor ring is welded to the adapters in such a way that the at least one additional weld seam runs axially and/or circularly relative to the axis of rotation of the rotor and/or along a contact area between the adapters and the rotor disk or the rotor ring, wherein the welding depths of the radial weld seams are selected in such a way that they amount to at least 50% of a top surface width of the at least one additional weld seam and wherein the radial weld seams are over-welded with the at least one additional weld seam.

2. The method as recited in claim 1 wherein the rotor blades are arranged in a prescribed installation position of the blade ring in order to produce the blade ring.

3. The method as recited in claim 2 wherein the rotor blades are first detachably secured to a holding device and arranged in the prescribed installation position of the blade ring by moving the holding device.

4. The method as recited in claim 1 wherein a pre-twist is established in the rotor blades before the blade ring is formed and/or after the radial weld seams are created.

5. The method as recited in claim 4 wherein that the pre-twist is established through shrinkage after the radial weld seams have been created.

6. The method as recited in claim 4 wherein the pre-twist is an angle between 0.5 and 5.

7. The method as recited in claim 6 wherein the pre-twist is between 1 and 3.

8. The method as recited in claim 1 wherein the welding depths of the radial weld seams are selected in such a way that they amount to at least 60% of the top surface width of the at least one additional weld seam.

9. The method as recited in claim 1 wherein the radial weld seams are made with welding depths between 3 mm and 10 mm.

10. The method as recited in claim 1 wherein the radial weld seams are made with welding depths between 5 mm and 6 mm.

11. The method as recited in claim 1 wherein the radial weld seams are created so as to be uniformly distributed along an inner circumference of the blade ring.

12. The method as recited in claim 1 wherein electron-beam welding and/or a laser-beam welding is employed for the welding.

13. The method as recited in claim 1 wherein the rotor is a turbine disk or a turbine ring for a turbine stage of a continuous-flow machine.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Additional advantages, features and details of the invention can be gleaned from the description below of embodiments as well as from the drawings in which the same or functionally identical elements are designated by the same reference numerals. The following is shown:

(2) FIG. 1a schematic side view of an embodiment of a holding device to which a rotor blade has been secured;

(3) FIG. 2an enlarged view of the detail II shown in FIG. 1;

(4) FIG. 3a schematic perspective view of a blade ring;

(5) FIG. 4an enlarged view of the detail IV shown in FIG. 3, depicting several weld seams; and

(6) FIG. 5an enlarged and partial sectional perspective view of the detail IV shown in FIG. 3.

DETAILED DESCRIPTION

(7) FIG. 1 shows a schematic side view of an embodiment of a holding device 10 to which a rotor blade 12 for a blade ring 14 (see FIG. 3) of a rotor has been secured. FIG. 1 will be explained below in conjunction with FIG. 2, which shows an enlarged view of the detail II depicted in FIG. 1. The holding device 10 encompasses a base 16 and two holding elements 18a, 18b arranged on the base 16 by means of which the rotor blade 12 is detachably secured and clamped on the base 16. The holding element 18a here is configured on the rotor blade 12 as a clamping shoe and corresponds to the profile of an adapter 22, while the holding element 18b is configured so as to correspond to an outer cover strip profile 20b (Z profile) of the rotor blade 12, so that a positive fit is achieved in certain areas. Moreover, the holding element 18b comprises two partial holding elements 18b, 18b, whereby the partial holding element 18b is also configured as a clamping shoe. An adapter 22, whose function will be explained in greater detail below, is arranged on the root of the rotor blade 12. The holding elements 18a, 18b, in turn, are detachably attached to the base 16 by fastening means 24 configured as screws. The holding elements 18a, 18b are also provided with a protective layer 26 in the area where they make contact with the rotor blade 12 in order to reliably prevent the rotor blades 12 from being scratched or the like.

(8) In order to secure the rotor blade 12 to the holding device 10, the partial holding element 18b configured as a clamping shoe is preferably first secured with a positive fit to a sealing fin 28 (fin sealing lip, sealing web) provided on the outer cover strip profile 20b of the rotor blade 12. Subsequently, the rotor blade 12 is positioned against the holding device 10 and secured by screwing on the partial holding elements 18b, 18b. Then the rotor blade 12 is clamped by means of the holding element 18a arranged on and screwed onto the adapter 22. The rotor blade 12 can be readjusted in the radial direction of the blade ring 14for instance, by means of gentle tappingso as to ensure its concentricity in accordance with the arrows Ia, Ib via the adapter 22 or the holding elements 18a, 18b. Since no direct force is applied onto the secured rotor blade 12, the latter is moved via the holding device 10, thereby reliably preventing it from slipping or being damaged, and also preventing a functional layer that might be present on the rotor blade 12 from chipping off. In this context, it can be provided that the rotor blades 12 are arranged on a suitably configured mounting apparatus (not shown) for purposes of assembling the entire blade ring 14, after which the holding device 10 or its base 16 can be moved along a corresponding sliding guide of the mounting apparatus.

(9) In the present embodiment, the holding elements 18a, 18b are configured in such a way that, when the rotor blade 12 is secured to the base 16, a pre-twist is established in the rotor blade 12 in that the rotor blade is twisted by an angle between 0.5 and 5, for instance, between 1 and 3. Here, it is provided that the holding elements 18a, 18b are geometrically designed in such a way that the pre-twist is established when the rotor blade 12 is secured to the base 16. Therefore, replacing or varying the holding elements 18a, 18b allows the desired pre-twist to be established so as to be variable as a function of the specific structural requirements made of the blade ring 14.

(10) FIG. 3 shows a schematic perspective view of the blade ring 14 that is formed by moving a total of 99 rotor blades 12 into their prescribed installation positions. The entire installation diameter of the blade ring 14 can be checked, for example, with a dial gauge and if applicable readjusted, so as to ensure concentricity. Here, arrow IIIa indicates the pre-twist between the adapter 22 and the outer cover strip profile 20b (Z profile) of the rotor blade 12. The desired pre-twist is established as a result of the fact that the rotor blades 12 only shrink in the area of their adapter 22 whereas their outer cover strip profiles 20b do not undergo shrinkage from the welding procedure. This pre-twist can be systematically selected by defining the wedge thickness of the adapter 22, as a result of which the pre-twist established by means of the holding device 10 can be either reduced or completely eliminated. For the sake of illustration, the arrows IIIb indicate a shrinkage of the blade ring 14 of approximately 2 mm. Here, it should be pointed out that it is fundamentally possible to dispense with the above-mentioned holding device 10 or with the establishment of a pre-twist using the holding device 10 since the pre-twist of the rotor blades 12 can also be established exclusively by means of the shrinkage resulting from the welding. This also has the advantage that the production or repair of the rotor can be done more quickly and cheaply since the pre-twist is achieved in all of the rotor blades 12 together, and the rotor blades 12 do not have to be clamped and measured individually. In this context, it can be fundamentally provided that the outer cover strip profile 20b of the rotor blades 12 is configured or adapted in such a way as to appropriately promote the establishment of the pre-twist.

(11) FIG. 4 shows an enlarged view of the detail IV depicted in FIG. 3. Several rotor blades 12 and adapters 22 of the blade ring 14 shown in FIG. 3 can be seen here which are welded by means of an electron-beam welding method that creates several weld seams 30a, 30b. Here, IVa designates an area without impurities stemming from machining, cleaning agent residues and the like. Arrows IVb, in contrast, designate areas that have such impurities and consequently could leave a gap behind. Especially when high-temperature-resistant materials are employedfor example, Inconel 718for the rotor blades 12 or for the adapters 22, the machining of the blade ring 14 without cooling lubricants (dry) becomes very problematic. This is why the adapters 22 are first tack-welded to each other in that radial weld seams 30a are created that have a depth of at least 60% of the top surface width of the axial weld seam 30b. The radial weld seams 30a are created so as to be uniformly distributed along the inner circumference of the blade ring 14. The welding depth is 5 mm to 6 mm in the present embodiment. Since the welding depth is deeper than necessary, any cooling lubricants that might be present are prevented from penetrating too deeply into the residual gap during the machining. Here, as mentioned above, it can be provided that a larger welding shrinkage is accepted in order to establish a specific pre-twist in the rotor blades 12.

(12) Subsequently, a rotor disk 32 is arranged on the blade ring 14 and welded together with the adapters 22 in order to create a rotor configured as a turbine disk (blisk). For this purpose, the radial weld seams 30a are over-welded as shown by arrow IVc and the axial weld seam 30b is formed. Consequently, in the area marked by the arrow IVd, the axial weld seam 30bwhich runs in a circle relative to the rotational axis of the blade ring 14 or of the rotor, and along a contact area between the adapters 22 and the rotor disk 32does not come into contact with impurities that might be present, as a result of which the formation of pores or flawed sites is ruled out and a suitably high-quality join is achieved. For the welding, an electron-beam welding method is employed, whereby it is also fundamentally possible to employ a laser-beam welding method or the like.

(13) For the sake of better elucidation, FIG. 5 shows an enlarged and partial sectional perspective view of the detail IV depicted in FIG. 3. Here, especially the radial weld seams 30a between the adapters 22 as well as the axial weld seam 30b between the adapters 22 and the rotor disk 32 can be seen. The above-mentioned process steps can be fundamentally employed not only for the production but also for the repair of the blade ring 14 or of the rotor.