Turbomachine rotor and method for manufacturing it

Abstract

Turbomachine rotor (10, 20), with a radially inner hub body (11, 21), with a radially outer cover body (12, 22), with running blades (13, 23) extending between the hub body (11, 21) and the cover body (12, 22), having running blades (14, 24), wherein the guide vanes (13, 23) are, according to a first alternative, an integral part of the hub body (11) and are metallurgically connected to the cover body (12), or, according to a second alternative, an integral part of the cover body (22) and are metallurgically connected to the hub body (21), characterized in that The rotor blades (13, 23) have an integral base (15, 25) adjacent to the cover body (12) according to the first alternative or adjacent to the hub body (21) according to the second alternative, via which the rotor blades (13, 23) are materially connected to the cover body (12) according to the first alternative or to the hub body (21) according to the second alternative, wherein the rotor blades (13, 23) have a transition radius in a transition region between the respective rotor blade (14, 24) and the respective base (15, 25) which is between 0.5% and 2.5% of an outer diameter of the turbomachine rotor (10, 20), wherein the transition radius in the respective transition region (16, 26) is larger than a radius in the region of the respective materially connected connection (17, 27).

Description

[0001] The invention relates to a turbomachine rotor. Furthermore, the invention relates to a method for manufacturing such a turbomachine rotor.

[0002] Turbomachinery, such as turbines or compressors, has stator-side and rotor-side components. The rotor-side components of a turbomachine include the rotor itself, which comprises a radially inner hub, rotor blades extending radially outward from the hub, and, in closed designs, a shroud extending radially outward from the rotor blades. The blades of the rotor blades extend between the radially inner hub and the radially outer shroud of a closed turbomachine rotor.

[0003] Such turbomachines are known from EP 1 785 590 A1, US 2011 / 0 318 183 A1 and KR 10 2011 0 073 921 A.

[0004] Known closed turbomachine rotors are constructed in such a way that, according to a first alternative, the rotor blades are an integral part of the hub body and are materially bonded to the cover body, or according to a second alternative, the rotor blades are an integral part of the cover body and are materially bonded to the hub body.

[0005] If the rotor blades are an integral part of the hub body, then the rotor blades and the hub body form a monolithic assembly. Conversely, if the rotor blades are an integral part of the cover body, then the rotor blades and the cover body form a monolithic assembly.

[0006] To increase the performance of a turbomachine, it is necessary to operate the respective turbomachine rotor at increasingly higher speeds. However, turbomachine rotors known from practical experience cannot be operated at increasingly higher speeds because the bonded connection, especially a brazed one, between the rotor blades and, according to the first alternative, the shroud or, according to the second alternative, the hub body, can fail at increasingly higher speeds. Therefore, there is a need for a turbomachine rotor that can be operated at higher speeds.

[0007] Based on this, the present invention aims to create a novel turbomachine rotor and a method for manufacturing it.

[0008] This problem is solved by a turbomachine rotor according to claim 1.

[0009] According to the invention, the guide vanes according to the first alternative have an integral base adjacent to the cover body or according to the second alternative adjacent to the hub body, via which the guide vanes according to the first alternative are materially connected to the cover body or according to the second alternative to the hub body.

[0010] By providing an integral base on the rotor blades and by the material-bonded connection between the base and, according to the first alternative, the cover body or, according to the second alternative, the hub body, the respective material-bonded connection can be improved, in particular stresses in the area of ​​the same are reduced, so that ultimately the turbomachine rotor can be operated at higher speeds and thus the power of the turbomachine can be increased.

[0011] According to the invention, the rotor blades have a transition radius in a transition area between the respective blade and the respective base, which is between 0.5% and 2.5%, particularly preferably between 1.0% and 2.0%, of the outer diameter of the turbomachine rotor. Such a transition radius between the blade and the base allows the strength of the respective bonded connection and thus the maximum rotational speed of a turbomachine rotor to be increased particularly advantageously.

[0012] Preferably, according to the first alternative, the hub body, the rotor blades, and the bases, or according to the second alternative, the cover body, the rotor blades, and the bases are each formed by milling as integral and thus monolithic assemblies, wherein, according to the first alternative, the rotor blades and the cover body, or according to the second alternative, the rotor blades and the hub body are joined to each other at the bases of the rotor blades by brazing. This allows for the provision of a turbomachine rotor that can be operated at particularly high speeds.

[0013] The inventive method for manufacturing the turbomachine rotor is defined in claim 7.

[0014] Preferred embodiments of the invention are described in the dependent claims and the following description. Exemplary embodiments of the invention are explained in more detail with reference to the drawing, without being limited thereto. The drawing shows: Fig. 1: a highly schematic detail of a first turbomachine rotor; and Fig. 2: a highly schematic detail of a second turbomachine rotor.

[0015] The invention relates to a turbomachine rotor, namely a so-called closed turbomachine rotor, in particular a closed turbomachine rotor of a turbine or a compressor. Closed turbomachine rotors have a cover body.

[0016] Fig. Figure 1 shows a highly schematic section of a first turbomachine rotor 10 according to the invention, comprising a radially inner hub body 11, a radially outer cover body 12, and rotor blades 13 extending between the radially inner hub body 11 and the radially outer cover body 12, each blade having a blade 14. The radially inner hub body 11 is also referred to as the hub disk and the radially outer cover body 12 as the cover disk.

[0017] In the exemplary embodiment of the Fig. 1 The guide vanes 13 are an integral part of the hub body 11. The guide vanes 13 and the hub body 11 therefore form a monolithic assembly.

[0018] In Fig. 1 the guide vanes 13 are bonded to the cover body 12 by means of a material bond, in particular by soldering.

[0019] According to the invention, the running blades 13 have in the Fig. In the embodiment shown in Figure 1, an integral and therefore monolithic base 15 is located adjacent to the cover body 12, i.e., at one end of the impeller blades 13 facing the cover body 12, via which the impeller blades 13 are metallurgically connected to the cover body. A metallurgical connection 17, preferably a soldered connection, is thus formed between the base 15 of the respective impeller blade 13 and the cover body 12. Fig. 1 shows a radius in the area of ​​the material-bonded connection 17.

[0020] The hub body 11, the integral guide vanes 13 of the hub body 11, and the integral bases 15 of the guide vanes 13 are preferably machined as an integral assembly. The hub body 11, the guide vanes 13, and the bases 15 thus form a monolithic assembly.

[0021] The rotor blades 13 have a defined transition radius in the transition area 16 between the respective rotor blade 14 and the respective base 15. This transition radius is larger than the radius in the area of ​​the bonded connection 17 and is between 0.5% and 2.5% of the outer diameter of the turbomachine rotor 10. This outer diameter of the turbomachine rotor 10 is defined by the largest diameter of the cover body 12.

[0022] Preferably the transition radius in the transition region 16 is between 0.5% and 2% or between 1.0% and 2.5%, particularly preferably between 1.0% and 2.0%, of this outer diameter of the turbomachine rotor 10.

[0023] Fig. Figure 2 shows an alternative embodiment of a turbomachine rotor 20 with a radially inner hub body 21, a radially outer cover body 22 and with rotor blades 23 extending between the radially inner hub body 21 and the radially outer hub body 22, which have rotor blades 24.

[0024] In the variant of Fig. 2. The guide vanes 23 are an integral part of the cover body 22 and are materially bonded to the hub body 21 via bases 25, which are integral parts of the respective guide vane 23. The guide vanes 23, namely the guide vane blades 24 thereof, have the respective base 25 adjacent to the hub body 21 or at an end opposite the hub body 21, via which the guide vanes 23 are materially bonded to the hub body 21.

[0025] In Fig. The cover body 22, the guide vanes 23, and the bases 25 form an integral assembly, i.e., a monolithic assembly, which is preferably formed by milling. This monolithic assembly is materially bonded to the hub body 21 via the bases 25 of the guide vanes 23, in particular by brazing. Fig. Figure 2 shows a radius in the area of ​​the material-bonded connection 27.

[0026] In the transition area 26 between the respective rotor blade 24 of the respective rotor blade 23 and the respective base 25, a defined transition radius is formed which is larger than the radius in the area of ​​the material-bonded connection 27 and which is between 0.5% and 2.5%, preferably between 0.5% and 2.0% or between 1.5% and 2.5%, particularly preferably between 1.0% and 2.0%, of the outer diameter of the turbomachine rotor 20.

[0027] The invention presented here further relates to a method for manufacturing such a turbomachine rotor 10 or 20.

[0028] In a first step, according to the first alternative, a hub body 11 integrally bladed with the running blades 13 or according to the second alternative, a cover body 22 integrally bladed with the running blades 23 is provided.

[0029] In a second step, a separate cover body 12 is provided according to the first alternative, or a separate hub body 21 according to the second alternative. These assemblies are preferably manufactured by milling or additive manufacturing. According to the first alternative, the hub body 11, the guide vanes 13, and the base 15 form an integral, monolithic assembly manufactured by milling. According to the second alternative, the cover body 22, the guide vanes 23, and the base 25 form an integral, monolithic assembly manufactured by milling.

[0030] In a third step, hub bodies 11 or 21 and cover bodies 12 or 22 are joined together by means of a material bond via the bases 15 or 25 of the running blades 13 or 23, preferably by soldering.

[0031] A transition radius, preferably formed by milling, in the respective transition area 16, 26 is larger than a radius in the area of ​​the respective material-bonded connection 17, 27. In the variant of Fig. 1. Therefore, the transition radius in the transition area 16 between the base 15 and the rotor blade 14 is larger than the radius in the connection area between the base 15 and the cover body 12. In the variant of Fig. 2. The transition radius in the transition area 26 between base 25 and blade 24 is larger than the radius in the connection area between the base 25 and the hub body 21.

[0032] In the turbomachine rotor 10, 20 according to the invention, stresses can be reduced by the shaping. Furthermore, rotational speeds of the turbomachine rotor 10, 20 can be increased, which ultimately increases the performance of a turbomachine. Reference symbol list 10 Turbomachine rotor 11 Hub bodies 12 cover bodies 13 Running blade 14 guide vane blade 15 sockets 16 Transition area 17 material-bonded connection 20 Turbomachine rotor 21 Hub bodies 22 Cover bodies 23 Running shovel 24 guide vane blades 25 sockets 26 Transition area 27 material-bonded connection

Claims

[1] Turbomachine rotor (10, 20), with a radially inner hub body (11, 21), with a radially outer cover body (12, 22), with running blades (13, 23) extending between the hub body (11, 21) and the cover body (12, 22), having running blades (14, 24), wherein, according to a first alternative, the guide vanes (13, 23) are an integral part of the hub body (11) and are metallurgically connected to the cover body (12), or according to a second alternative, are an integral part of the cover body (22) and are metallurgically connected to the hub body (21), characterized by , that The rotor blades (13, 23) have an integral base (15, 25) adjacent to the cover body (12) according to the first alternative or adjacent to the hub body (21) according to the second alternative, via which the rotor blades (13, 23) are materially connected to the cover body (12) according to the first alternative or to the hub body (21) according to the second alternative, wherein the rotor blades (13, 23) have a transition radius in a transition region between the respective rotor blade (14, 24) and the respective base (15, 25) which is between 0.5% and 2.5% of an outer diameter of the turbomachine rotor (10, 20), wherein the transition radius in the respective transition region (16, 26) is larger than a radius in the region of the respective materially connected connection (17, 27). [2] Turbomachine rotor according to claim 1, characterized by , that the transition radius is between 0.5% and 2.0% of the outer diameter of the turbomachine rotor. [3] Turbomachine rotor according to claim 1, characterized by , that the transition radius is between 1.0% and 2.5% of the outer diameter of the turbomachine rotor. [4] Turbomachine rotor according to claim 2 or 3, characterized by , that the transition radius is between 1.0% and 2.0% of the outer diameter of the turbomachine rotor. [5] Turbomachine rotor according to any one of claims 1 to 4, characterized by , that according to the first alternative the hub body (11), the guide vanes (13) and the bases (15) or according to the second alternative the cover body (22), the guide vanes (23) and the bases (25) are each manufactured as integral assemblies by milling. [6] Turbomachine rotor according to any one of claims 1 to 5, characterized by, that according to the first alternative the guide vanes (13) and the cover body (12) or according to the second alternative the guide vanes (23) and the hub body (21) are joined together by soldering. [7] Method for manufacturing a turbomachine rotor according to any one of claims 1 to 6, comprising at least the following steps: Providing a hub body (11) integrally bladed with the running blades (13) according to the first alternative or a cover body (22) integrally bladed with the running blades (23) according to the second alternative, Providing a separate cover body (12) according to the first alternative or a separate hub body (21) according to the second alternative, connecting the hub body (11, 21) and cover body (12, 22) by means of a material bond via the bases (15, 25) of the guide vanes (13, 23). [8] Method for manufacturing a turbomachine rotor according to claim 7, characterized by, that according to the first alternative the hub body (11), the guide vanes (13) and the bases (15) or according to the second alternative the cover body (22), the guide vanes (23) and the bases (25) are each provided as integral assemblies by milling. [9] Method for manufacturing a turbomachine rotor according to claim 7 or 8, characterized by , that according to the first alternative the guide vanes (13) and the cover body (12) or according to the second alternative the guide vanes (23) and the hub body (21) are connected to each other by soldering in the area of ​​the bases (15, 25) of the guide vanes (13, 23).

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