阅读说明：本技术 涡轮机转子及用于制造该涡轮机转子的方法 (Turbomachine rotor and method for manufacturing the turbomachine rotor ) 是由 A.博恩霍恩 S.施彭格勒 S.魏哈德 C.武尔姆 C.莱滕迈尔 L.奥拉斯 于 2020-03-18 设计创作，主要内容包括：本发明涉及涡轮机转子及用于制造该涡轮机转子的方法。一种涡轮机转子(10),具有：径向内部的轴(11)；轮毂体(12),其在径向外部跟随所述轴(11)；动叶片(13),其从所述轮毂体(12)发出,至少延伸到径向外部,并且在适当的情况下沿所述轴(11)的方向延伸到径向内部；以及减振器(14),其一体地形成在所述轮毂体(12)和/或所述动叶片(13)上,以便抑制所述涡轮机转子(10)的操作引起的振动。(The invention relates to a turbine rotor and a method for manufacturing the same. A turbine rotor (10) having: a radially inner shaft (11); a hub body (12) which follows the shaft (11) radially outside; rotor blades (13) which issue from the hub body (12), extend at least to the radially outer part and, where appropriate, in the direction of the shaft (11) to the radially inner part; and a damper (14) integrally formed on the hub body (12) and/or the rotor blade (13) so as to suppress vibration caused by operation of the turbine rotor (10).)

1. A turbine rotor (10) having:

a radially inner shaft (11),

a hub body (12) radially outwardly abutting the shaft (11),

rotor blades (13) which issue from the hub body (12), extend at least to the radially outer side and, where appropriate, in the direction of the shaft (11) to the radially inner side,

a damper (14) integrally formed on the hub body (12) and/or the rotor blade (13) so as to damp vibration caused by operation of the turbine rotor (10).

2. The turbomachine rotor according to claim 1, wherein a friction damper (15) as a damper (14) is integrally formed on the hub body (12) between each adjacent moving blade (13), the friction damper (15) including friction surfaces (16, 17) extending in a radial direction and a circumferential direction.

3. A turbine rotor according to claim 2, characterised in that the friction damper (15) is positioned off-centre between adjacent rotor blades (13) as seen in the circumferential direction.

4. The turbomachine rotor according to one of the claims 1 to 3, characterized in that deformation dampers (18) are integrally formed on the rotor blades (13) on outer blade sections (13 a) as dampers (14), respectively, radially outside the hub body (12), the deformation dampers (18) each extending between adjacent rotor blades (13), the deformation dampers (18) having a curved profile.

5. Turbomachine rotor according to claim 4, characterised in that a plurality of deformation dampers (18) are formed, viewed in the radial direction, the radial position and/or profile of the deformation dampers (18) being matched to the vibration mode of the vibration to be dampened.

6. The turbomachine rotor according to one of the claims 1 to 5, characterized in that a friction damper (15) is integrally formed on the inner blade section (13 b) on the moving blades (13) as a damper (14) on a radially inner portion of the hub body (12) and a radially outer portion of the shaft (11).

7. The turbomachine rotor according to one of claims 1 to 6, characterized in that a deformation damper (18) is integrally formed on the inner blade section (13 b) on the moving blades (13) as a damper (14) on a radially inner portion of the hub body (12) and a radially outer portion of the shaft (11).

8. Turbomachine rotor according to one of the claims 1 to 7, characterised in that the rotor blades (13) have sections (19, 20) of different strength.

9. The turbine rotor of any one of claims 1 to 8, wherein the turbine rotor is integrally formed or formed as a single body.

10. Method for manufacturing a turbine rotor according to one of claims 1 to 9, characterized in that the turbine rotor is manufactured by means of an additive manufacturing method, in particular by 3D printing.

11. A method according to claim 10, characterized in that a friction damper (15) is formed in that at least one metal powder layer is not exposed and does not fuse at least in certain sections during the additive manufacturing method.

12. Method according to claim 10, characterized in that sections (19, 20) of different strength are formed as at least one metal powder layer is not exposed in certain parts and does not fuse so as to form a hollow space filled with metal powder during the additive manufacturing method.

Technical Field

The present invention relates to a turbine rotor. The invention further relates to a method for producing such a turbine rotor.

Background

A turbomachine (turbo machine), such as a turbine (turbo) or compressor, includes a stator-side assembly and a rotor-side assembly. The rotor-side assembly of a turbine comprises a so-called turbine rotor comprising a shaft, a hub body and at least moving blades emanating from the hub body, which moving blades extend to the radially outer portion.

During operation, the moving blades of the turbine rotor are exposed to a primary load. Thus, during operation, the blades of the turbine rotor may be exposed to vibrations, which may lead to a malfunction of the moving blades. For this reason, it is known from practice to mount damping elements on the turbine rotor.

Accordingly, DE 102009010502 a1 shows a turbine rotor in the case of which damping wires extend between adjacent rotor blades. The damper tie bar acts as a damper.

Another turbine rotor is known from US 2017/0191366 a1, in which case slot damper pins (slitdamper pins) are used as dampers between adjacent rotor blades.

In the case of the turbine rotors known from the prior art, the vibration dampers are each formed as separate components which have to be manufactured separately and subsequently mounted on the turbine rotor. This is a disadvantage. There is a need to provide damping on a turbine rotor in an easier way.

Disclosure of Invention

Based on this, the invention is based on the following objects: a new type of turbine rotor and a method for manufacturing the turbine rotor are created.

This object is solved by a turbine rotor according to claim 1.

The turbine rotor according to the invention comprises: at least one radially inner shaft; a hub body radially outwardly abutting the axle; rotor blades emanating from the hub body, extending at least to the exterior, and preferably extending to the radially interior in the direction of the shaft; and a damper integrally formed on the hub body and/or on the rotor blade so as to suppress operation-induced vibration of the turbine rotor.

With the present invention, it is proposed to integrally form a damper on a hub body and/or a rotor blade of the turbine rotor so as to suppress vibration of the turbine rotor. Thus, the damper is no longer a separate component that must be manufactured separately and subsequently installed or assembled, but rather is an integral damper that does not need to be manufactured separately and subsequently installed, but rather is formed as an integral part during the manufacture of the turbine rotor.

According to a further advantageous development of the invention, friction dampers are integrally formed on the hub body between respectively adjacent rotor blades, which friction dampers have friction surfaces extending in the radial direction and in the circumferential direction. Alternatively or additionally, a deformation damper is integrally formed on the rotor blades to the outer rotor blade section radially outwardly of the hub body, extending between adjacent rotor blades, respectively, the deformation damper having a curved profile. Alternatively or additionally, the friction damper and/or the deformation damper are integrally formed on the inner blade section on the rotor blade radially inside the hub body and radially outside the shaft. Alternatively or additionally, the rotor blade has sections of different strength. Such a damper is particularly suitable for one-piece designs.

According to an advantageous further development of the invention, the turbine rotor is integrally formed or formed as a single body, in particular by means of an additive manufacturing method, in particular by 3D printing. The entire turbine rotor is integrally formed and, therefore, is formed as a single body or piece. The turbine rotor may be easily constructed by an additive manufacturing method, i.e. comprising said vibration damper, which is integrally formed on the hub body and/or the rotor blade.

A method for manufacturing a turbine rotor according to the invention is defined in claim 10.

Preferred further developments of the invention result from the dependent claims and the subsequent description. Exemplary embodiments of the invention are explained in more detail with the aid of the figures without being limited thereto.

Drawings

The figures show:

fig. 1 shows a highly schematic, extracted view (extract) of a first turbine rotor;

FIG. 2 shows detail II of FIG. 1;

fig. 3 shows a highly schematic, extracted view of a second turbine rotor;

fig. 4 shows a highly schematic, extracted view of a third turbine rotor;

fig. 5 shows a highly schematic, extracted view of another turbine rotor.

Detailed Description

Fig. 1 shows a highly schematic, extracted view of a turbine rotor 10 in the region of a radially inner shaft 11, a hub body 12 and rotor blades 13. The shaft 11 is used for mounting the turbine rotor 10. The hub body 12 follows the shaft 11 radially outside and surrounds this shaft 11 on the outside at least in sections. The rotor blades 13 serve for the flow guidance of the medium and for this purpose comprise a flow front edge, a flow rear edge and flow guide surfaces extending between the flow front edge and the flow rear edge, which flow guide surfaces form in particular a suction side and a pressure side. The rotor blades 13 extend with an outer rotor blade section 13a for flow conduction, which outer rotor blade section 13a issues from the hub body 12 to the radially outer side, and an inner rotor blade section 13b not for flow conduction, which inner rotor blade section 13b issues from the hub body 12 to the radially inner side in the direction of the axis 11.

On the turbine rotor 10, i.e., on the hub body 12 in fig. 1, a damper 14 is integrally formed so as to compensate for operation-induced vibrations of the turbine rotor 10, in particular, operation-induced vibrations of the moving blades 13.

As can be seen from detail II of fig. 1 (see fig. 2), for this purpose, a friction damper 15, which provides a damper 14, is integrally formed on the hub body 12 between each two adjacent rotor blades 13. In the region of this friction damper 15, the hub 12 is interrupted and, therefore, is not formed continuously in a firmly bonded or material-bonded manner, so that friction surfaces 16, 17 are formed, which friction surfaces 16, 17 rub along one another during operation for damping. These friction surfaces 16, 17 extend on the one hand in the radial direction and on the other hand in the circumferential direction. Here, the portions of the hub 12 which are not connected in a firmly bonded or materially bonded manner and therefore lie loosely adjacent to one another overlap here.

As is evident from detail II according to fig. 1 (see fig. 2), the respective friction damper 15 is preferably positioned off-center between the respective adjacent rotor blades 13, viewed in the circumferential direction, wherein the division ratio can be selected depending on the vibrations to be damped.

Fig. 3 shows a further highly schematic, extracted view of a turbine rotor 10 according to the invention in the region of a hub 12 and a blade section 13a of a blade 13 extending from the hub 12 to the outside. In the exemplary embodiment shown in fig. 3, the deformation dampers 18 are integrally formed on the rotor blades 13, i.e. on the outer rotor blade section 13a, which deformation dampers 18 respectively extend between adjacent rotor blades 13, which deformation dampers 18 provide the respective dampers 14. These deformation dampers 18 act on the rotor blades 13 on both sides in a firmly bonded or bonded manner, the deformation dampers 18 extending between the rotor blades 13, wherein the deformation dampers 18 have a curved or corrugated profile, as viewed in the circumferential direction.

In fig. 3, a plurality of deformation dampers 18 are formed between the rotor blades 13, i.e., integrally on the rotor blades 13, as viewed in the radial direction, wherein the radial position of the deformation dampers 18 and/or the profile of the deformation dampers 18 is matched to the vibration pattern of the respective vibration to be damped. In the case where the moving blades 13 vibrate, the deformation dampers 18 undergo deformation, thereby suppressing the vibration.

Fig. 4 shows a partial view of a further turbine rotor 10 according to the invention, also in the region of the shaft 11, the hub 12 and the rotor blades 13, wherein, in the exemplary embodiment of fig. 4, the vibration dampers 14 are likewise integrally formed on the turbine rotor 10, i.e. on the inner blade sections 13b of the rotor blades 13 which are not used for flow conduction. Here, the damper 14 shown in fig. 4 is designed as a deformation damper 18. The damper 14 can also be designed as a friction damper.

It is again pointed out here that the inner blade section 13b of the rotor blade 13, which extends between the shaft 11 and the hub 12, is not used for flow conduction. Only the outer blade sections 13a of the rotor blades 13 extending outwardly in the radial direction away from the hub body 12 are used for such flow conduction.

For this reason, the inner blade section 13b extending between the hub body 12 and the shaft 11 may also be referred to as a reinforcing bracket for structural reinforcement of the turbine rotor 10 between the shaft 11 and the hub body 12. Such reinforcing struts may also be offset in the circumferential direction relative to the flow-conducting rotor blade section 13a of the rotor blade 13.

Fig. 5 shows an extracted view of a further turbine rotor 10 according to the invention in the region of the rotor blade 13. For damping, the rotor blades 13 comprise sections 19, 20 of different strength as dampers 14. This can be a section 20 or a hollow space which is filled with a different material structure than the section 19 of the rotor blade 13, which section 19 surrounds the hollow space. By means of this, vibrations on the rotor blades 13 of the turbine rotor 10 can also be advantageously suppressed.

As already explained, the turbine rotor 10 is preferably of unitary or monolithic or one-piece construction. Preferably, it is manufactured by means of an additive manufacturing method, in particular by 3D printing.

Details regarding 3D printing of metal parts that are constructed in layers due to the fusion of multiple layers of metal powder on top of each other are familiar to those skilled in the art to which this document is directed. For fusing the metal powder, the metal powder is in particular exposed to a laser beam.

If the above-described friction damper is to be formed during 3D printing, the at least one metal powder layer is not exposed and therefore does not fuse at least in certain sections to prevent a strong or material-bonded connection from being formed. Similarly, a section or hollow space 20 may be formed in the region of the moving blade 13 filled with the metal powder, and then, this section or hollow space 20 has another or different strength than those sections 19 surrounding the powder-filled hollow space 20. Thus, the damper 14 can be advantageously and easily formed during 3D printing in this manner.

The turbine rotor 10 according to the invention may be a rotor of a turbine or a compressor. The turbine or compressor may be a component of a turbomachine. The invention may also be used for other turbine rotors, such as for compressors, turbines and aircraft engines.

List of reference numerals

10 turbine rotor

11 axle

12 wheel hub body

13 moving blade

13a outer bucket blade section

13b inner blade section

14 vibration damper

15 friction damper

16 friction surface

17 friction surface

18 deformation vibration damper

19 section

20 sections.