METHOD FOR PRODUCING A ROTATING DISK FOR A TURBOMACHINE

Abstract

The present invention is directed to a method for producing a rotating disk for a turbomachine, forming blade root uptakes on a plurality of circumferential positions, for which, in each case, an axially extending profile groove that is bounded circumferentially by inner wall surfaces of the rotating disk is introduced on a respective circumferential position, in which production method, initially first profile grooves are introduced in a disk on first circumferential positions, and subsequently, a second profile groove is introduced in the disk on a second circumferential position located circumferentially between the first profile grooves.

Claims

1. A method for producing a rotating disk for a turbomachine, which forms blade root uptakes on a plurality of circumferential positions, for which, in each case, an axially extending profile groove that is bounded circumferentially by inner wall surfaces of the rotating disk is introduced on a respective circumferential position, in which production process comprising the steps of: initially introducing first profile grooves in a disk on first circumferential positions, and subsequently, introducing a second profile groove in the disk on a second circumferential position located circumferentially between the first profile grooves, wherein, in each case, there is always at least one second circumferential position located circumferentially between two first circumferential positions, and wherein, during the introduction of a respective second profile groove, a circumferentially immediately adjacent first profile groove is supported at the inner wall surfaces.

2. The method according to claim 1, wherein an insert that is applied to the inner wall surfaces for support and is removed again after the introduction of the respective second profile groove is inserted in the circumferentially immediately adjacent first profile groove.

3. The method according to claim 2, wherein the insert has a clamping device and, after the insert is introduced into the circumferentially immediately adjacent first profile groove, by activating the clamping device, it is widened in the circumferential direction, and is thus spread apart, bracing the inner wall surfaces.

4. The method according to claim 1, wherein a backfilling material is introduced into the circumferentially immediately adjacent first profile groove and is applied against the inner wall surfaces for support, being converted into a dimensionally stable state in the profile groove.

5. The method according to claim 4, wherein, when the backfilling material is introduced, it is at least viscous free-flowing and hardens in the circumferentially immediately adjacent first profile groove.

6. The method according to claim 4, wherein, along with the backfilling material, a shaped object is fixed in place in the circumferentially immediately adjacent first profile groove, which is already in a dimensionally stable state during the introduction into the profile groove.

7. The method according to claim 1, wherein the first and the second circumferential positions alternately follow one another circumferentially, and when each second profile groove is introduced, both circumferentially immediately adjacent first profile grooves are supported at their inner wall surfaces each time.

8. The method according to claim 7, wherein initially all first profile grooves are introduced, and only subsequently are the second profile grooves introduced.

9. The method according to claim 7, wherein, when a respective second profile groove is introduced, all first profile grooves are each supported at their inner wall surfaces.

10. The method according to claim 1, wherein the first profile grooves are introduced by removing material by machining, preferably by broaching.

11. The method according to claim 1, wherein the second profile grooves are introduced by removing material by machining, preferably by broaching.

12. The method according to claim 1, wherein the second profile grooves are introduced by a removal method without machining.

13. The method according to claim 1, wherein a land remaining between two circumferentially immediately adjacent profile grooves has a width W taken in the circumferential direction, which is taken radially at the level of a constriction of the land, and the profile grooves each have a radially taken depth D, wherein D/W2.5.

14. The method according to claim 1, wherein the profile grooves are configured in the form of fir tree grooves, wherein a plurality of support flanks are formed each time at each of the inner wall surfaces.

15. The method according to claim 1, wherein the rotating disk is configured and arranged in a module with a rotating blade wheel and rotating blades, the rotating blades with a respective rotating blade root are inserted into the profile grooves.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In the following, the invention will be explained more closely on the basis of an exemplary embodiment, wherein the individual features in the scope of the independent or coordinated claims can also be essential to the invention in another combination, and wherein also no distinction is made individually between the different claim categories.

[0027] Taken individually,

[0028] FIG. 1 shows a jet engine in an axial section;

[0029] FIG. 2 shows an excerpt of a rotating disk with a profile groove;

[0030] FIG. 3 shows in schematic representation a rotating blade with a blade root for inserting into the rotating disk according to FIG. 2;

[0031] FIGS. 4a-c show a rotating disk in schematic representation for illustrating the production process according to the invention.

DESCRIPTION OF THE INVENTION

[0032] FIG. 1 shows a turbomachine 1, concretely a turbofan engine, in an axial section. Functionally, the turbomachine 1 is divided into compressor 1a, combustion chamber 1b, and turbine 1c. Both the compressor 1a as well as the turbine 1c are each constructed from two stages. Each of the stages is composed of a guide vane ring and a following rotating blade wheel. For reasons of clarity, for the turbine 1c, reference numbers are given only to one of the stages for the guide vane ring 3 and the rotating blade wheel 4 belonging thereto. Aspirated air is compressed in the compressor 1a and is then burned in the downstream combustion chamber 1b with kerosene mixed in. The hot gas flows through the hot-gas channel and in this way propels the rotating blade wheel 4 or the rotating blade wheels, which rotate(s) around the axis of rotation 2.

[0033] FIG. 2 shows a detail view of a part of the rotating blade wheel 4, namely a rotating disk 20. A profile groove 21 is introduced into this disk, and a blade root 30 of a rotating blade 31 is inserted into this groove; compare FIG. 3 for illustration. Based on the profiling of the profile groove 21, thus based on the contour of the inner wall surfaces 20a, the rotating blade 31 is held radially therein in form-fitting manner.

[0034] The production of the rotating disk 20 is explained on the basis of FIGS. 4a-c. In a first step according to FIG. 4a, the first profile grooves 21.1 are introduced in the disk 20 onto the first circumferential positions 40.1 Between each of the first circumferential positions 40.1 is arranged each time a second circumferential position 40.2; thus, intermediate positions initially remain free. Correspondingly, if sufficient material is always still present circumferentially, the first profile grooves 21.1 thus can be introduced by broaching.

[0035] Subsequently, according to FIG. 4b, an insert 45 or backfilling material 46 is arranged in the first profile grooves 21.1. In practice, typically one of the two alternatives is selected; for reasons of clarity, both are depicted in FIG. 4b. Then, according to FIG. 4b, when the second profile grooves 21.2 are introduced on the second circumferential positions 40.2, the first profile grooves 21.1 are supported in this way. Correspondingly, the second profile grooves 21.2 can also be introduced by broaching; refer to the information on advantages given in the introduction to the description. The inserts 45 or the backfilling material 46 is or are then removed again; see FIG. 4c. There results a close staggering of the profile grooves 21.1, 21.2) or a large D/W ratio.