WO2005052321A1

WO2005052321A1 - Cooled connection assembly for turbine rotor blades

Info

Publication number: WO2005052321A1
Application number: PCT/DE2004/002439
Authority: WO
Inventors: Martin Fischer; Oskar Ostermeir
Original assignee: Mtu Aero Engines Gmbh
Priority date: 2003-11-26
Filing date: 2004-11-04
Publication date: 2005-06-09
Also published as: DE10355230A1

Abstract

The invention relates to a rotor (10) comprising at least two stages (11, 12), each stage (11, 12) having a rotor disc (14, 15) with moving blades (17) that are fixed to said disc. Opposing rotor discs (14, 15) of adjoining stages (11, 12) are detachably interconnected by means of flanges (22, 23) that are allocated to the rotor discs (14, 15), in such a way that at least one fixing element connects a first flange (22) of a first rotor disc (14) to a second flange (23) of a second rotor disc (15) that lies opposite. The fixing element or each fixing element engages in cavities or bores (26) of the flanges (22, 23). According to the invention, in addition to the cavity or each cavity or bore(s) (26) for the fixing element or each fixing element, a cavity, notch (34) or grooves (35, 36) for conducting air is/are integrated into at least one of the flanges (23) of the opposing rotor discs, said air conduction enabling the temperature of the rotor to be regulated.

Description

COOLED CONNECTION ARRANGEMENT FOR TURBINE ROTOR SLIDING

The invention relates to a rotor for a turbomachine, in particular for a gas turbine, according to the preamble of claim 1. Furthermore, the invention relates to a turbomachine, a stationary gas turbine and an aircraft engine.

Turbomachine rotors generally have several stages, each stage comprising a rotor disk and several rotor blades rotating together with the rotor being fastened to the rotor disk of each stage. The rotor disks of the multiple stages of the rotor can be connected to one another in different ways, for example by welding or detachably by screwing. The present invention relates to rotors whose rotor disks are detachably connected to one another.

DE 1 6 27 386 A1 discloses a connection arrangement for two adjacent turbine rotor disks, each of the adjacent rotor disks to be connected to one another having at least one shell which extends in the axial direction, and at the ends of the shells which extend in the axial direction Flanges are arranged. According to DE 196 27 386 A1, a fastening means designed as an expansion bolt penetrates the opposite bottle of two adjacent rotor disks to be connected to one another and is detachably connected to the flanges by nuts.

DE 198 28 817 C2 discloses a rotor for a turbomachine, with at least two bladed stages, the rotor disks of which are detachably connected to one another. In the rotor according to DE 198 28 817 C2, only every second rotor disk has an essentially axially extending shell with a flange arranged at the end of the respective shell. A rotor disk positioned between two such rotor disks and to be connected to these rotor disks has flanges in the region of the side faces of the respective rotor disk. DE 198 28 817 C2 uses a fastening means designed as a screw bolt to connect two flanges of rotor disks to be connected to one another. The rotors of a turbomachine are subject to high loads, in particular high heating, during the operation of the turbomachine. For temperature control or cooling of the rotor, it is therefore necessary to dissipate from the rotor any heating or heating that arises in the area of the rotor and accumulates in the area of the rotor. Neither DE 196 27 386 A1 nor DE 198 28 817 C2 propose measures for cooling or tempering the rotor.

Proceeding from this, the present invention is based on the problem of creating a novel rotor for a turbomachine, in particular for a gas turbine.

This problem is solved in that the rotor mentioned at the outset is further developed by the features of the characterizing part of patent claim 1.

According to the invention, at least one recess or notch for air guidance is integrated in at least one of the flanges of the opposing rotor disks to be connected to one another, in addition to the or each recess or bore for the or each fastening means, the rotor being heatable via the air duct.

According to an advantageous development of the invention, a flange or a flange section of an intermediate stage seal is clamped between the flanges of the opposing rotor disks to be connected to one another, the flange or flange section of the intermediate stage seal having at least one recess or groove for air guidance. The or each recess or groove in the region of the flange or the flange section of the intermediate stage seal cooperates with the or each recess or notch in the region of the flange of the rotor disk for forced ventilation and thus for temperature control of the rotor.

Preferred developments of the invention result from the dependent subclaims and the following description. The turbomachine according to the invention is defined in claim 8, the stationary gas turbine according to the invention is defined in claim 9 and the aircraft engine according to the invention is defined in claim 10.

Exemplary embodiments of the invention are explained in more detail with reference to the drawing, without being restricted to this. The drawing shows:

1 shows a section of a flange of a rotor disk of a rotor according to the invention, which is designed as a disk ring, in the direction indicated in FIGS. 2 and 3 by the section line I-1;

FIG. 2 shows a detail from a rotor according to the invention according to a first exemplary embodiment of the invention in longitudinal section, the illustration in FIG. 2 showing the flange of a rotor disk designed as a disk ring in the cutting direction II-II according to FIG. 1;

3 shows a further section of the rotor according to the invention according to the first embodiment of the invention in longitudinal section, the illustration in FIG. 3 showing the flange of a rotor disk designed as a disk ring in the cutting direction III-III in accordance with FIG. 1;

4: a detail of the rotor according to the invention from FIGS. 1 to 3;

5: a detail from a rotor according to the invention according to a second embodiment of the invention in longitudinal section analogous to FIG. 2; and

6: a section of a rotor according to the invention according to a further exemplary embodiment of the invention in longitudinal section analogous to FIGS. 2 and 5. The present invention is described in greater detail below with reference to FIGS. 1 to 6, FIGS. 1 to 4 showing different details of a first exemplary embodiment of the invention. 5 and 6, however, show alternative embodiments of the invention.

FIG. 2 shows a longitudinal section of a first exemplary embodiment of a rotor 10 according to the invention for a turbomachine, the rotor 10 according to FIG. 2 having three stages 11, 12 and 13. Each stage 11, 12 and 13 is formed by a rotor disk 14, 15 and 16, respectively, with rotor blades 17 being attached to each of the rotor disks 14, 15 and 16 at the radially outer end. The blades 17 are only partially shown in FIG. 2.

In the exemplary embodiment in FIG. 2, each of the rotor disks 14, 15 or 16 has at least one cylindrical or conical shell which extends essentially in the axial direction. The rotor disk 14 on the left in FIG. 2 comprises a cylindrical shell 18 on its right side. The rotor disk 15 in the middle in FIG. 2 has a conical shell 19 on its left side and a cylindrical shell 20 on its right side 2, the right-hand rotor disk 16 in turn has a conical shell 21 on its left side. Flanges 22, 23, 24 and 25 are arranged at the ends of the shells 18, 19, 20 and 21. The two rotor disks 14 and 15 are over the flanges 22 and 23 and over the flanges

24 and 25, the two rotor disks 15 and 16 are to be releasably connected to one another. As can be seen in FIG. 2, the flanges 22, 23, 24 and

25 holes 26 are aligned. Fastening means (not shown, preferably designed as screw bolts) engage in these bores 26 for the releasable fastening of the rotor disks 14 and 15 or 15 and 16.

As can also be seen in FIG. 2, one of the two flanges 22 and 23 and 24 and 25 to be connected to one another has a support section 27 that extends essentially in the axial direction. In the exemplary embodiment in FIG. 2, these are the right flanges 22 in each case and 24. The support sections 27 of the flanges 22 and 24 engage under the other flange 23 and 25 in the axial direction, the fastening means, not shown, being attached to one another can support the support portions 27 to prevent rotation of the fasteners.

FIG. 2 also shows that a so-called intermediate stage seal 28 and 29 is arranged between two adjacent rotor disks 11 and 12 and 12 and 13. The intermediate stage seals 28 and 29 are essentially formed by sections 30 and 31, respectively, which extend in the axial direction. In the exemplary embodiment in FIG. 2, the sections 30 and 31 of the intermediate stage seals 28 and 29 which extend in the axial directions are each assigned two sealing projections 32 radially on the outside. The sealing projections 32 are designed as closed rings which extend in the circumferential direction of the rotor 10 and serve to seal a gap between radially inner ends of stationary guide vanes (not shown) and the rotor 10. The sealing projections 32 are also referred to as sealing fins. The difference between the intermediate stage seal 28 and 29 in FIG. 2 can be seen in the fact that the intermediate stage seal 28 is clamped between the two flanges 22 and 23 with a flange 33.

During operation of the turbomachine, the rotor 10 in particular is subject to excessive heating. In order to minimize the loads on the rotor 10 as a result of the heating, it is necessary to remove the heat generated at the rotor 10 from the rotor 10. The invention now proposes measures that serve to dissipate heat from the rotor 10 and thus to cool the rotor 10.

The measures proposed for this in the sense of the invention are described below for the exemplary embodiment of FIGS. 1 to 4 with reference to FIGS. 1, 3 and 4, FIGS. 1, 3 and 4 showing details of the arrangement according to FIG. 2 in different views ,

1 shows a partial section from the flange 23 of the rotor disk 15. The flange 23 is designed as a disk ring, wherein, as can be seen in FIG. 1, a plurality of bores 26 are arranged along the circumference of the flange 23 for engagement by fastening means (not shown) are. Between every two In the exemplary embodiment in FIG. 1, adjacent groups of three bores 26 each are integrated into the flange 23, the notches 34 serving to guide the air and thus the temperature of the rotor 10. The notches 34 in the region of the flange 23 cannot be seen in FIG. 2, but in FIG. 3, which, as shown in FIG. 1, shows a longitudinal section through the rotor 10 in the region of the steps which is offset by approximately 30 ° from FIG. 2 1 1 and 12 shows. Thus, the notches 34 in the region of the flange 23 allow a flow through the same in the radial direction. The notches 34 interact in the area of the flanges 23 in the exemplary embodiment shown in FIG. 3 with recesses or grooves 35 and 36 which are associated with the flange 33 of the intermediate stage seal 28. Thus, the notches 34 in the area of the flange 33 together with the grooves 35 and 36 in the area of the flange 33 allow a flow in the radial direction of the flanges which are otherwise only used for connection purposes. For the flow, the pressure potential that is present at the rotor 10 is used, which of course depends on whether the rotor 10 according to the invention is used in the compressor area or turbine area of the turbomachine.

To further support the air flow and thus temperature control or cooling of the rotor 10, 28 recesses or bores 37 are made in the axially extending section 30 of the intermediate stage seal. A flow through the arrangement shown from the radially inner region of the rotor 10 into a main flow channel of the turbomachine is possible via the recesses 34, 35, 36 and 37. Fig. 4 shows the intermediate stage seal 28 alone. 4, the recesses 35, 36 and 37 are highlighted in black for clarity.

Already at this point it should be pointed out that, in the sense of the present invention, the recesses for air guidance and thus for temperature control of the rotor are placed according to the invention in the area of the flanges which, according to the prior art, serve exclusively to connect two adjacent rotor disks. The invention is based on the knowledge that a different positioning of the recesses would be disadvantageous for reasons of stability. A relocation of the Recesses for air guidance in the area of the cylindrical or wedge-shaped shells 18, 19, 20 or 21 would be disadvantageous for reasons of strength, since the shells must reliably absorb the torsional forces acting during operation of the rotor. Recesses in the area of the shells 18, 19, 20 and 21 would impair their torsional rigidity. Air routing through the flanges, on the other hand, does not affect the torsional rigidity and thus the life of the shells and thus the rotor disks. Furthermore, the invention makes it possible to avoid high temperature gradients between adjacent components. This also increases the life of the rotor.

The embodiment of FIG. 5 essentially corresponds to the embodiment of FIGS. 1 to 4, so that the same reference numbers are used to avoid unnecessary repetitions for the same assemblies. The embodiment of FIG. 5 differs, as can best be seen from a comparison with FIG. 2, from the embodiment of FIGS. 1 to 4 only in the configuration of the flange 23 of the rotor disk 15 and the flange 33 of the intermediate stage seal 28 the flange 33 of the intermediate stage seal 28 in the exemplary embodiment of FIG. 2 via grooves 35 which extend in the radial direction and via grooves 36 which run in the axial direction. According to FIG. 2, the axially extending grooves 36 of the flange 33 are encompassed by a section 38 of the flange 23 that extends essentially in the axial direction. In the exemplary embodiment in FIG. 5, however, the flange 33 of the intermediate stage seal 28 has only the grooves 35 extending in the radial direction. In the exemplary embodiment, the grooves 36 extending in the axial direction and the section 38 of the flange 23 extending essentially in the axial direction are shown in FIG Fig. 5 waived. The mode of operation of the air duct and thus the temperature control of the rotor 10 is not changed by this.

The same applies to the embodiment of FIG. 6, for which again the same reference numbers are used to avoid unnecessary repetitions for the same assemblies. 6, the flange 33 of the intermediate stage seal 28 in turn has only grooves 35 extending in the radial direction, but the flange 23 of the rotor disk 15 is adjacent The notches 34 (not shown in FIG. 6) are assigned grooves 39 which run in the axial direction and are encompassed by a section 40 of the intermediate stage seal 28. The air flow according to the invention and thus temperature control or cooling of the rotor 10 is also possible with the embodiment of the present invention shown in FIG. 6.

The rotor 10 according to the invention is preferably used in gas turbines, in particular in aircraft engines.

Claims

claims

1. rotor for a turbomachine, in particular for a gas turbine, with at least two stages (1 1, 12), each stage (1 1, 12) having a rotor disk (14, 15) with rotor blades (17) attached to the rotor disk, Opposing rotor disks (14, 15) of adjacent steps (11, 12) on the flanges (22, 23) assigned to the rotor disks (14, 15) are detachably connected to one another such that at least one fastening means has a first flange (22) of a first rotor disk (14) with a second flange (23) of a second, opposite rotor disc (15), and wherein the or each fastening means engages in recesses or bores (26) of the flanges (22, 23), characterized in that in at least one the flanges (23) of the opposing rotor disks, in addition to the or each recess or bore (26) for the or each fastening means, at least one recess or notch (34) for air guidance is integrated, where if the rotor can be tempered via the air duct.

2. Rotor according to claim 1, characterized in that a flange (33) or a flange portion of an intermediate stage seal (28) is clamped between the first flange (22) and the second flange (23).

3. Rotor according to claim 2, characterized in that the flange (33) or the flange portion of the intermediate stage seal (28) has at least one recess or groove (35, 36) for air guidance.

4. Rotor according to claim 3, characterized in that the or each recess or groove (25, 36) in the region of the flange (33) or the flange portion of the intermediate stage seal (28) with the or each recess or notch (34) interacts in the area of the flange (23) of the rotor disk (15) for forced ventilation and thus for temperature control of the rotor.

5. Rotor according to one or more of claims 1 to 4, characterized in that the rotor disks (14, 15) have at least on one side an axially extending, cylindrical or conical shell (18, 19), at one end a flange (22, 23) of the rotor disk is arranged in each shell.

6. Rotor according to one or more of claims 1 to 4, characterized in that each second rotor disk has at least on one side an axially extending, cylindrical or conical shell, with a flange of the rotor disk being arranged at one end of each shell , and that a rotor disk is positioned between two rotor disks having at least one shell, the flanges of which side surfaces are assigned to the rotor disk.

7. Rotor according to one or more of claims 2 to 6, characterized in that a section (30) of the intermediate stage seal (28) extending in the axial direction has at least one sealing projection (32) radially on the outside, the section extending in the axial direction Section (30) at least one recess or bore (37) is introduced for air guidance.

8. Turbo machine with at least one rotor according to one or more of claims 1 to 7.

9. Stationary gas turbine with at least one rotor according to one or more of claims 1 to 7.

10. aircraft engine with at least one rotor according to one or more of claims 1 to 7.