Rotor comprising a rotor component arranged between two rotor disks

Abstract

A rotor of a gas turbine, having two adjacent rotor disks having a plurality of blade-holding grooves for receiving rotor blades, distributed around the periphery thereof, and having an axially extending peripheral ring projection radially beneath the blade-holding grooves. A peripheral rotor component is fixed to the ring projections, between the rotor disks. In order to protect the periphery, the rotor disk or the rotor component includes at least two recesses arranged on the periphery in a distributed manner, in each of which engaging shoulders of the rotor component or the rotor disk engage.

Claims

1. A rotor, comprising: a first rotor disk of two rotor disks which comprises, distributed over a circumference, blade retaining grooves which pierce the first rotor disk axially, for accommodating rotor blades and, radially below the blade retaining grooves, an axially extending circumferential first annular protrusion; a second rotor disk of the two rotor disks, fastened to the first rotor disk, which second rotor disk comprises, distributed over the circumference, of blade retaining grooves which pierce the second rotor disk axially, for accommodating rotor blades and, radially below the blade retaining grooves, a circumferential second annular protrusion which extends axially toward to the first annular protrusion; and a circumferential rotor component, arranged between the two rotor disks, which circumferential rotor component comprises a first support section which comes to bear against the first annular protrusion on the side of the first annular protrusion facing a rotor axis, and a second support section which comes to bear against the second annular protrusion on the side of the second annular protrusion facing the rotor axis; wherein a geometric interlock configured to prevent circumferential motion of the rotor component relative to at least one of: the first rotor disk; and the first rotor disk and the second rotor disk, comprises at least one of: first rotor disk recesses disposed on the first rotor disk radially outward of the first annular protrusion and first end engagement projections projecting from and circumferentially fixed relative to a first axial end of the rotor component and configured to cooperate with the first rotor disk recesses; and first rotor disk projections disposed on the first rotor disk radially outward of the first annular protrusion and first end recesses disposed on the first axial end of the rotor component and configured to cooperate with the first rotor disk projections, plus second rotor disk projections disposed on the second rotor disk radially outward of the second annular protrusion and second end recesses disposed on a second axial end of the rotor component and configured to cooperate with the second rotor disk projections; and wherein the first axial end of the rotor component comprises: a radially extending disk section which at least partly covers the blade retaining grooves of the first rotor disk; a first region with a first material thickness; and radially outside the first region, a second region with a material thickness at least double the first material thickness.

2. The rotor as claimed in claim 1, wherein the first axial end of the rotor component comprises an axially open first annular groove surrounding the first annular protrusion and the second axial end of the rotor component comprises an axially open second annular groove surrounding the second annular protrusion.

3. The rotor as claimed in claim 2, wherein a first radially outer flank of the first annular groove bears against the first annular protrusion and a second radially outer flank of the second annular groove bears against the second annular protrusion.

4. The rotor as claimed in claim 1, wherein the geometric interlock comprises the first rotor disk recesses and the first rotor disk projections, and wherein the first rotor disk recesses are disposed between respective first rotor disk projections.

5. The rotor as claimed in claim 1, wherein the geometric interlock comprises the first rotor disk projections; wherein the first rotor disk projections are arranged in each case in a circumferential direction between two respective blade retaining grooves.

6. The rotor as claimed in claim 5, wherein a length of the first rotor disk projections in the circumferential direction is in each case smaller than or the same as a smallest distance between two blade retaining grooves.

7. The rotor as claimed in claim 1, wherein the second rotor disk projections are arranged on a radially outward facing side of the second annular protrusion, spaced apart from an axially free end of the second annular protrusion.

8. The rotor as claimed in claim 1, wherein the second region is formed by a thickened area on a side of the radially extending disk section facing away from first rotor disk.

9. The rotor as claimed in claim 8, wherein the geometric interlock comprises the first end engagement projections; and wherein the first end engagement projections are arranged in the second region.

10. The rotor as claimed in claim 1, wherein the rotor comprises a rotor of a gas turbine.

11. The rotor as claimed in claim 1, wherein the geometric interlock comprises the second end recesses; and wherein the rotor component comprises a circumferential annular projection in which the second end recesses are disposed.

12. The rotor as claimed in claim 1, wherein the geometric interlock comprises the first rotor disk recesses; and wherein the first rotor disk recesses are arranged in each case in a respective extension of the blade retaining grooves.

13. The rotor as claimed in claim 1, wherein the geometric interlock comprises the first end recesses; and wherein the first end recesses are arranged in the second region.

14. A rotor, comprising: a first rotor disk of two rotor disks which comprises, distributed over a circumference, blade retaining grooves which pierce the first rotor disk axially, for accommodating rotor blades and, radially below the blade retaining grooves, an axially extending circumferential first annular protrusion; a second rotor disk of the two rotor disks, fastened to the first rotor disk, which second rotor disk comprises, distributed over the circumference, blade retaining grooves which pierce the second rotor disk axially, for accommodating rotor blades and, radially below the blade retaining grooves, a circumferential second annular protrusion which extends axially toward to the first annular protrusion; and a circumferential rotor component, arranged between the two rotor disks, which circumferential rotor component comprises a first support section which comes to bear against the first annular protrusion on the side of the first annular protrusion facing a rotor axis, and a second support section which comes to bear against the second annular protrusion on the side of the second annular protrusion facing the rotor axis; wherein a geometric interlock configured to prevent circumferential motion of the rotor component relative to at least one of: the first rotor disk; and the first rotor disk and the second rotor disk, comprises: first rotor disk recesses disposed on the first rotor disk radially outward of the first annular protrusion and first end engagement projections projecting from and circumferentially fixed relative to a first axial end of the rotor component and configured to cooperate with the first rotor disk recesses; and first rotor disk projections disposed on the first rotor disk radially outward of the first annular protrusion and first end recesses disposed on the first axial end of the rotor component and configured to cooperate with the first rotor disk projections, plus second rotor disk projections disposed on the second rotor disk radially outward of the second annular protrusion and second end recesses disposed on a second axial end of the rotor component and configured to cooperate with the second rotor disk projections; and wherein the first axial end of the rotor component comprises: a radially extending disk section which at least partly covers the blade retaining grooves of the first rotor disk; a first region with a first material thickness; and radially outside the first region, a second region with a material thickness at least double the first material thickness.

15. A rotor, comprising: a first rotor disk of two rotor disks which comprises, distributed over a circumference, blade retaining grooves which pierce the first rotor disk axially, for accommodating rotor blades and, radially below the blade retaining grooves, an axially extending circumferential first annular protrusion; a second rotor disk of the two rotor disks, fastened to the first rotor disk, which second rotor disk comprises, distributed over the circumference, blade retaining grooves which pierce the second rotor disk axially, for accommodating rotor blades and, radially below the blade retaining grooves, a circumferential second annular protrusion which extends axially toward to the first annular protrusion; and a circumferential rotor component, arranged between the two rotor disks, which circumferential rotor component comprises a first support section which comes to bear against the first annular protrusion on the side of the first annular protrusion facing a rotor axis, and a second support section which comes to bear against the second annular protrusion on the side of the second annular protrusion facing the rotor axis; wherein a geometric interlock configured to prevent circumferential motion of the rotor component relative to at least one of: the first rotor disk; and the first rotor disk and the second rotor disk, comprises at least one of: first rotor disk recesses disposed on the first rotor disk radially outward of the first annular protrusion and first end engagement projections integrally formed with and projecting from a first axial end of the rotor component and configured to cooperate with the first rotor disk recesses; and first rotor disk projections disposed on the first rotor disk radially outward of the first annular protrusion and first end recesses disposed on the first axial end of the rotor component and configured to cooperate with the first rotor disk projections, plus second rotor disk projections disposed on the second rotor disk radially outward of the second annular protrusion and second end recesses disposed on a second axial end of the rotor component and configured to cooperate with the second rotor disk projections; and wherein the first axial end of the rotor component comprises: a radially extending disk section which at least partly covers the blade retaining grooves of the first rotor disk; a first region with a first material thickness; and radially outside the first region, a second region with a material thickness at least double the first material thickness.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Two exemplary embodiments for a rotor according to the invention in the region of the rotor component are depicted partially in the following drawings, in which:

(2) FIG. 1 shows part of the rotor in a longitudinal section in the region of the rotor component in a first embodiment;

(3) FIG. 2 shows the first rotor disk to be implemented from FIG. 1;

(4) FIG. 3 shows the rotor component to be implemented from FIG. 1;

(5) FIG. 4 shows part of the rotor in a longitudinal section in the region of the rotor component in a second embodiment;

(6) FIG. 5 shows the rotor component to be implemented from FIG. 4;

(7) FIG. 6 shows the first rotor disk to be implemented from FIG. 4.

DETAILED DESCRIPTION OF INVENTION

(8) A rotor in a first exemplary embodiment is depicted in a longitudinal section in FIG. 1 only in the region of the rotor component 1. Further configuration of the rotor can be selected with the aid of customary embodiments. The rotor at least has a first rotor disk 01 and a second rotor disk 06. A circumferential axially extending annular protrusion 03, 08 is in each case arranged on said rotor disks 01, 06.

(9) The rotor component 11 which has a respective circumferential annular groove 12, 17 for attachment to the rotor disks 01, 06 is situated between the rotor disks 01, 06, wherein the first annular protrusion 03 engages in the first annular groove 12, and the second annular protrusion 08 engages in the second annular groove 17. A support section 13, 18 formed by the rotor component 11 is situated radially below the respective annular protrusion 03, 08. Said support sections 13, 18 are supported on the respective annular protrusion 03, 08 at least when centrifugal force is present.

(10) It can furthermore be seen that the rotor component 11 has a circumferential radially extending disk section 20.

(11) The coupling between the rotor component 11 and the first rotor disk 01 is situated in the radially outer region in this exemplary embodiment.

(12) FIG. 2 depicts the first rotor disk 01 in a perspective view. The circumferential annular protrusion 03 and, radially outside, the blade retaining grooves 02 which axially pierce the first rotor disk 01 can be seen. A first engagement projection 05 is situated between in each case two blade retaining grooves 02. A corresponding first recess is situated between in each case two engagement sections 05.

(13) FIG. 3 shows the rotor component 11 which is complementary hereto. Visible again are the circumferential annular grooves 12, 17 with those support sections 13, 18 which are arranged on the side facing the rotor axis. The disk section 20 which extends radially at one axial end, immediately adjacent to the first rotor disk 01, is divided into a radially inner first region and a radially outer second region, wherein the second region has a thickened area 19 and consequently has at least twice the material thickness of the first region. In order to ensure a reliable coupling between the rotor component 11 and the first rotor disk 01 when centrifugal forces occur, in this exemplary embodiment the second engagement projections 15 arranged on the rotor component 11 and the second recesses 14 situated between them are arranged opposite the thickened area 19 in the radially outer region.

(14) In a similar fashion to FIG. 1, FIG. 4 shows a rotor in a second exemplary embodiment. The rotor hereby has a first rotor disk 21 and a second rotor disk 26. A circumferential axially extending annular protrusion 23, 28 is in each case arranged on said rotor disks 21, 26.

(15) The rotor component 31 which has a circumferential annular groove 32, 37 in each case for attachment to the rotor disks 21, 26 is situated between the rotor disks 21, 26.

(16) It can furthermore be seen that the rotor component 31 has a circumferential radially extending disk section 40.

(17) The coupling between the rotor component 31 and the first rotor disk 21 is situated immediately radially outside the first annular protrusion 23.

(18) FIG. 5 shows the rotor component 31 in a perspective view. Visible again is the circumferential first annular groove 32 with the support sections arranged on the side facing the rotor axis. The disk section 40 which extends radially immediately adjacent to the second rotor disk 26 at one axial end has a similar design to that above.

(19) In contrast to the previous design, in this case it is provided that the rotor component has a circumferential annular projection 35 on the radially outer situated flank of the first annular groove 32 on the side facing the rotor axis. Said annular projection 35 is interrupted multiple times by second recesses 34 which are arranged in each case distributed over the circumference.

(20) FIG. 6 shows the first rotor disk 21 in a perspective view. The circumferential annular protrusion 23 and the blade retaining grooves 02 can be seen. In order to effect the coupling, the first rotor disk 21 has the first engagement projections 25, which complement the second recesses 34, on the radially outer situated side on the first annular protrusion 23.