WO2014175766A1 - Rotor element for a turbo-machine and turbo-machine - Google Patents

Rotor element for a turbo-machine and turbo-machine Download PDF

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Publication number
WO2014175766A1
WO2014175766A1 PCT/RU2013/000365 RU2013000365W WO2014175766A1 WO 2014175766 A1 WO2014175766 A1 WO 2014175766A1 RU 2013000365 W RU2013000365 W RU 2013000365W WO 2014175766 A1 WO2014175766 A1 WO 2014175766A1
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WO
WIPO (PCT)
Prior art keywords
rotor shaft
rotor
heat conducting
turbo
machine
Prior art date
Application number
PCT/RU2013/000365
Other languages
French (fr)
Inventor
Andrey Leonidovich PAVLEVICH
Anton Gaerovich VALEEV
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/RU2013/000365 priority Critical patent/WO2014175766A1/en
Publication of WO2014175766A1 publication Critical patent/WO2014175766A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5024—Heat conductivity

Definitions

  • the invention relates to a rotor element for a turbo-machine according to the preamble of patent claim 1 as well as a turbo-machine.
  • Rotor elements for turbo-machines are well known from the general prior art.
  • a rotor element is, for example, known from US 6,227,799 Bl .
  • the rotor element comprises a rotor shaft which has a hollow cross-section at least in a portion of the rotor shaft.
  • the hollow cross-section forms an orifice extending in the longitudinal direction of the rotor shaft across said portion.
  • the hollow cross-section which can be a closed hollow cross-section is used as a cooling duct through which a cooling fluid can flow.
  • Said cooling fluid can be a cooling gas.
  • power for pumping is needed.
  • the application of cooling ducts within the rotor shaft can lead to bleeding of the cooling fluid.
  • the efficiency of the turbo-machine is reduced.
  • the design of the rotor shaft having special cooling ducts is very complicated. Hence, the rotor shaft is very expensive.
  • a first aspect of the invention relates to a rotor element for a turbo-machine.
  • the turbo-machine can be a steam turbine or a turbo generator.
  • the rotor element comprises a rotor shaft which has a hollow cross-section at least in a portion of the rotor shaft.
  • Said hollow cross-section can be a closed hollow cross-section. This means that the hollow- cross-section can be closed in the circumferential direction of the rotor shaft.
  • the hollow cross-section forms an orifice of the rotor shaft, the orifice extending in the longitudinal direction of the rotor shaft across said portion.
  • the rotor element has at least one blade section with at least one blade mounted on the rotor shaft.
  • the rotor element can be driven about an axis of rotation in such a way that a fluid, in particular, a gas, flows through the blade section.
  • the rotor element comprises at least one heat conducting element for distributing heat at least across said portion of the rotor shaft, the heat conducting element is arranged in the hollow cross- section at least partially.
  • the heat conducting element is completely arranged in the hollow cross-section.
  • the idea behind the present invention is that, conventionally, there is a high unevenness of the temperature field in rotor shafts not being equipped with a heat conducting element. That unevenness leads to high thermal deformations and stresses in the rotor shaft and to the risk of an operational loss of the rotor shaft due to high thermal loads. This applies particularly for epoxy parts of the rotor element.
  • the heat conducting element causes a redistribution of the temperature field in the rotor shaft so that high temperatures in corresponding areas of the rotor shaft decrease and low temperatures in corresponding areas of the rotor shaft increase.
  • the thermal state of the rotor shaft becomes more uniform.
  • the heat conducting element serves for reducing the temperature gradient in the rotor shaft because the heat conducting element intensifies the heat transfer between hot and cold areas.
  • the rotor element can be used for a turbo-machine of a waste heat utilization device utilizing a thermodynamic cycle, in particular, an organic rankine cycle.
  • the fluid driving the rotor element is working fluid, in particular, an organic working fluid which flows through the turbo-machine in a gaseous state.
  • Waste energy in the form of waste heat contained in the working fluid can be used by means of the turbo- machine, the rotor element transforming the waste energy contained in the working fluid at least partly into mechanical energy.
  • the turbo-machine can comprise a generator coupled to the rotor shaft, the generator being capable of transforming mechanical energy provided by the rotor shaft into electric energy. Thereby, the waste heat can be transformed into electric energy at least partly by means of the turbo-machine.
  • the temperature distribution in the rotor shaft also effects deformations, in particular, linear deformations, of the rotor shaft and as a consequence operational clearances of the turbo-machine.
  • operational gaps between rotating and stationary parts of the turbo-machine decrease or even disappear. In conventional turbo-machines this can lead to damages of the rotor elements.
  • the heat conducting element in the rotor shaft according to the invention the disappearance of the operational gaps can be prevented because of a more uniform temperature field in the rotor shaft. Hence, damages of the rotor element and of the turbo-machine as a whole can be avoided.
  • the heat conducting element is made of a first material which has a higher thermal conductivity than a second material the rotor shaft is made of.
  • the heat conducting element has a hollow cross-section, in particular, a closed hollow cross-section extending across a major portion of the longitudinal extension of the heat conducting element.
  • the heat conducting element does not affect the rotor elements dynamic performance due to increasing the stiffness of the rotor shaft. Moreover, the mass of the rotor element can be kept to a minimum. Furthermore, a very good structural performance of the rotor element can be realised.
  • the heat conducting element's hollow cross-section is closed in the longitudinal direction of the heat conducting element at least at one side of the heat conducting element.
  • the heat conducting element is made of aluminium and/or copper.
  • the rotor shaft is made of steel. This leads to a very high stiffness of the rotor shaft allowing for a very good performance of the rotor element as a whole.
  • the heat conducting element extends at least across a major portion of the rotor shaft. This allows for realising a particularly uniform distribution of temperature field in the rotor shaft. As a consequence, thermal and thermal-based loads as well as thermal deformations of the rotor shaft can be kept to a minimum.
  • a second aspect of the invention relates to a turbo-machine comprising the rotor element according to the present invention.
  • Advantageous embodiments of the rotor element according to the invention are to be regarded as advantageous embodiments of the turbo-machine according to the invention and vice versa.
  • the heat conducting element for distributing the heat across at least a portion of the rotor shaft, thermal deformations, thermal and thermal-based loads acting upon the rotor shaft can be kept to a minimum. As a consequence, the disappearance of operational gaps between the rotor element and stationary parts of the turbo-machine can be avoided, thus keeping the risk of a damage of the turbo-machine to a minimum.
  • FIG 1 part of a schematic, longitudinal sectional view of a rotor element for a turbo-machine, the rotor element comprising a rotor shaft which has a hollow cross-section at least in a portion of the rotor shaft, wherein the rotor element comprises at least one heat conducting element for distributing heat at least across said portion of the rotor shaft, the heat conducting element being arranged in the hollow cross-section; and
  • FIG 2 a comparison between a temperature distribution in the rotor element according to FIG 1 and a temperature distribution in the rotor shaft, not being equipped with the heat conducting element.
  • FIG 1 shows a rotor element 10 for a turbo-machine.
  • the turbo-machine for example, can be a turbo generator.
  • the rotor element 10 comprises a rotor shaft 12 which is, for example, made of steel.
  • the rotor shaft 12 has a longitudinal direction illustrated by a directional arrow 14.
  • the longitudinal direction coincides with an axis of rotation not shown in FIG 1.
  • the rotor element 10 is rotatable about the axis of rotation and, for example, rotatably supported on a housing of the turbo-machine.
  • the rotor element 10 can comprise at least one blading region or blade section corresponding to a turbine stage of the turbo-machine.
  • the blading region comprises blades which are mounted on the rotor shaft 12.
  • the rotor element 10 can be driven about the axis of rotation in such a way, that a fluid, for example, in the form of a gas, in particular, steam, can flow through the blading region of the rotor element 10.
  • the turbo-machine in the form of the turbo generator serves for transforming energy contained in the fluid into electric energy.
  • at least one bearing element not shown in FIG 1 can be used.
  • the bearing element is, for example, configured as a roller bearing.
  • the rotor shaft 12 has a hollow cross-section 15 at least in a portion 16 of the rotor shaft 12, the hollow cross-section 15 bounding an orifice 18 of the rotor shaft 12 and being a closed hollow cross-section.
  • the hollow cross-section 15 or the orifice 18 extends across a major portion of the rotor shaft 12.
  • the hollow cross-section 15 of the rotor shaft 12 is closed in the longitudinal direction of the rotor shaft 12 at least at one end 20 of the rotor shaft 12.
  • the rotor shaft 12 is made of steel. As a consequence, a very good performance of the rotor shaft 12 and the rotor element 10 respectively can be realised.
  • the rotor element 10 also comprises at least one heat conducting element in the form of a heat conducting barrel 22.
  • the heat conducting barrel 22 serves for distributing heat at least across the portion 16 of the rotor shaft 12, the heat conducting barrel 22 being arranged in the hollow cross-section 15 or in the orifice 18 respectively.
  • the heat conducting barrel 22 is made of aluminium. Thereby, the heat conducting barrel 22 is made of a first material (aluminium) which has a higher conductivity than a second material (steel) the rotor shaft 12 is made of.
  • the idea behind using the heat conducting barrel 22 is that the hollow heat conducting barrel 22 mounted in the orifice 18 intensifies heat transfer between hot and cold sides and areas of the rotor shaft 12.
  • the turbo generator due to thermal expansions of the rotor shaft 12 and the heat conducting barrel 22 respectively a very good thermal contact between the heat conducting barrel 22 and the rotor shaft 12 is provided.
  • the heat or the temperature respectively in the rotor shaft 12 can be distributed very fast and very equally.
  • the usage of the heat conducting barrel 22 allows for protecting rotor epoxy parts of the rotor element 10 from high temperatures. In other words, the temperature gradient in the rotor shaft 12 can be reduced in comparison with the rotor shaft 12 not being equipped with the heat conducting barrel 22. Moreover, the heat conducting barrel 22 does not affect the dynamic performance of the rotor element 10 negatively. By configuring the heat conducting element as the hollow heat conducting barrel 22, the moment of inertia of the heat conducting element and the rotor element 10 as a whole can be kept to a minimum.
  • the stiffness of the rotor element 10 is increased by the heat conducting barrel 22. Furthermore, the mass or the weight of the rotor element 10 as a whole can be kept very low, because the heat conducting barrel 22 is hollow, too.
  • the heat conducting element has a hollow cross-section 24 which extends across at least a major portion of the longitudinal extension of the heat conducting barrel 22. As can be seen from FIG 1, the hollow cross-section 24 of the heat conducting barrel 22 is closed in the longitudinal direction of the heat conducting barrel 22 at least at one end 26 of the heat conducting barrel 22.
  • At least a major portion of an outer surface 28 of the heat conducting barrel 22 is in thermal contact with an inner surface 30 of the rotor shaft 12, the inner surface 30 bounding the hollow cross-section 15 or the orifice 18 respectively.
  • the surfaces 28, 30 contact each other directly and completely.
  • the application of the heat conducting element in form of the heat conducting barrel 22 in comparison with the application of cooling ducts and heat pipes is much more efficient with regard to realising a uniform temperature field in the rotor shaft 12.
  • the rotor shaft 12 can be equipped with the heat conducting barrel 22 in a very easy and cost-efficient way.
  • the heat conducting barrel 22 allows for a very good protection of the rotor shaft 12 from thermal stresses.
  • thermal stresses due to the thermal expansion of the rotor shaft 12 and the heat conducting barrel 22 respectively can be kept very low.
  • the heat conducting barrel 22 can be made of materials having very high thermal conductivities, very low thermal expansions, very good mass properties and only very little production costs respectively. This can give additional benefits to realise a uniform temperature field in the rotor shaft 12.
  • FIG 2 shows a comparison between the rotor shaft 12 being equipped with the heat conducting barrel 22 and the rotor shaft 12 not being equipped with the heat conducting barrel 22, the rotor shaft 12 not being equipped with the heat conducting barrel 22 being designated by reference 12' in FIG 2.
  • the rotor shaft 12' shown in FIG 2 is the rotor shaft 12, however, the heat conducting barrel 22 is not arranged in the cross section 15 of the rotor shaft 12'.
  • the heat conducting barrel 22 causes a very intense heat transfer from the hot distal end 20 to a cold distal end 32 of the rotor shaft 12, the end 32 being arranged at a distance from the end 20 in the longitudinal direction of the rotor shaft 12. This means that the heat conducting barrel 22 supports the distribution of heat across the rotor shaft 12.
  • the rotor shaft 12' Since the rotor shaft 12' is not equipped with a heat conducting element, the distribution of heat across the rotor hast 12' is not supported or intensified. Hence, the end 20 of the rotor shaft 12' has a higher temperature than the end 20 of the rotor shaft 12. Furthermore, the temperature distribution in the rotor shaft 12' is much more uneven than the temperature distribution in the rotor shaft 12. As a consequence, thermal and thermal-based loads acting upon the rotor shaft 12 are much lower than thermal and thermal -based loads acting upon the rotor shaft 12'.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The inventions relates to a rotor element (10) for a turbo-machine, the rotor (10) element comprising a rotor shaft (12) which has a hollow cross-section (15) at least in a portion (16) of the rotor shaft (12), wherein at least one heat conducting element (22) for distributing heat at least across the portion (16) of the rotor shaft (12) is arranged in the hollow cross-section (15) at least partially.

Description

ROTOR ELEMENT FOR A TURBO-MACHINE AND TURBO-MACHINE
DESCRIPTION The invention relates to a rotor element for a turbo-machine according to the preamble of patent claim 1 as well as a turbo-machine.
Rotor elements for turbo-machines are well known from the general prior art. Such a rotor element is, for example, known from US 6,227,799 Bl . The rotor element comprises a rotor shaft which has a hollow cross-section at least in a portion of the rotor shaft. In other words, the hollow cross-section forms an orifice extending in the longitudinal direction of the rotor shaft across said portion.
Usually, the hollow cross-section which can be a closed hollow cross-section is used as a cooling duct through which a cooling fluid can flow. Said cooling fluid can be a cooling gas. In order to guide or pump the cooling fluid through the rotor shaft, power for pumping is needed. Moreover, the application of cooling ducts within the rotor shaft can lead to bleeding of the cooling fluid. Thus the efficiency of the turbo-machine is reduced. Moreover, the design of the rotor shaft having special cooling ducts is very complicated. Hence, the rotor shaft is very expensive.
It is therefore an object of the present invention to provide a rotor element for a turbo- machine as well as a turbo-machine which allow for a particularly effective and cost- efficient protection of the rotor shaft from thermal and thermal-based loads.
This object is solved by a rotor element for a turbo-machine having the features of patent claim 1 and a turbo-machine having the features of patent claim 9. Advantageous embodiments with expedient and non-trivial developments of the invention are indicated in the other patent claims.
A first aspect of the invention relates to a rotor element for a turbo-machine. For example, the turbo-machine can be a steam turbine or a turbo generator. The rotor element comprises a rotor shaft which has a hollow cross-section at least in a portion of the rotor shaft. Said hollow cross-section can be a closed hollow cross-section. This means that the hollow- cross-section can be closed in the circumferential direction of the rotor shaft. The hollow cross-section forms an orifice of the rotor shaft, the orifice extending in the longitudinal direction of the rotor shaft across said portion.
Usually, the rotor element has at least one blade section with at least one blade mounted on the rotor shaft. The rotor element can be driven about an axis of rotation in such a way that a fluid, in particular, a gas, flows through the blade section.
In order to facilitate an effective and cost-efficient protection of the rotor shaft from thermal and thermal-based loads, according to the present invention the rotor element comprises at least one heat conducting element for distributing heat at least across said portion of the rotor shaft, the heat conducting element is arranged in the hollow cross- section at least partially. Advantageously, with regard to the longitudinal extension of the rotor shaft and the heat conducting element respectively, at least a major portion of the heat conducting element is arranged in the hollow cross-section of the rotor shaft. Advantageously, with regard to the longitudinal extension of the rotor shaft and the heat conducting element respectively, the heat conducting element is completely arranged in the hollow cross-section.
The idea behind the present invention is that, conventionally, there is a high unevenness of the temperature field in rotor shafts not being equipped with a heat conducting element. That unevenness leads to high thermal deformations and stresses in the rotor shaft and to the risk of an operational loss of the rotor shaft due to high thermal loads. This applies particularly for epoxy parts of the rotor element.
In the rotor element according to the present invention, the heat conducting element causes a redistribution of the temperature field in the rotor shaft so that high temperatures in corresponding areas of the rotor shaft decrease and low temperatures in corresponding areas of the rotor shaft increase. Thus, the thermal state of the rotor shaft becomes more uniform. In other words, the heat conducting element serves for reducing the temperature gradient in the rotor shaft because the heat conducting element intensifies the heat transfer between hot and cold areas. Thus, thermal deformations, stresses and the risk of operational loss, in particular of epoxy parts of the rotor element, can be kept to minimum.
The rotor element can be used for a turbo-machine of a waste heat utilization device utilizing a thermodynamic cycle, in particular, an organic rankine cycle. In this regard, the fluid driving the rotor element is working fluid, in particular, an organic working fluid which flows through the turbo-machine in a gaseous state. Waste energy in the form of waste heat contained in the working fluid can be used by means of the turbo- machine, the rotor element transforming the waste energy contained in the working fluid at least partly into mechanical energy. Furthermore, the turbo-machine can comprise a generator coupled to the rotor shaft, the generator being capable of transforming mechanical energy provided by the rotor shaft into electric energy. Thereby, the waste heat can be transformed into electric energy at least partly by means of the turbo-machine.
The temperature distribution in the rotor shaft also effects deformations, in particular, linear deformations, of the rotor shaft and as a consequence operational clearances of the turbo-machine. The higher the temperature unevenness is the more thermal deformations occur. As a consequence, operational gaps between rotating and stationary parts of the turbo-machine decrease or even disappear. In conventional turbo-machines this can lead to damages of the rotor elements. By using the heat conducting element in the rotor shaft according to the invention the disappearance of the operational gaps can be prevented because of a more uniform temperature field in the rotor shaft. Hence, damages of the rotor element and of the turbo-machine as a whole can be avoided. In an advantageous embodiment of the invention the heat conducting element is made of a first material which has a higher thermal conductivity than a second material the rotor shaft is made of. Thereby, a very good temperature distribution can be realised, thus leading to a very uniform temperature field in the rotor shaft. Hence, thermal and thermal-based loads can be kept to a minimum.
It has turned out to be particularly advantageous, if, with regard to the longitudinal direction of the heat conducting element, at least a major portion of an outer surface of the heat conducting element is in thermal contact with an inner surface of the rotor shaft, the inner surface bounding the hollow cross-section. In this embodiment, a very efficient heat transfer between the rotor shaft and the heat conducting element across a very large area is possible. Hence, the temperature or the heat can be distributed very equally and very fast across the rotor shaft. The surfaces can be in a direct contact with each other, thus allowing for a very good heat transfer.
In a further particularly advantageous embodiment of the invention the heat conducting element has a hollow cross-section, in particular, a closed hollow cross-section extending across a major portion of the longitudinal extension of the heat conducting element. The heat conducting element does not affect the rotor elements dynamic performance due to increasing the stiffness of the rotor shaft. Moreover, the mass of the rotor element can be kept to a minimum. Furthermore, a very good structural performance of the rotor element can be realised.
In order to realise a particularly good heat transfer and heat distribution, in a further embodiment of the invention the heat conducting element's hollow cross-section is closed in the longitudinal direction of the heat conducting element at least at one side of the heat conducting element.
In order to realise a particularly good heat transfer and heat distribution, in a further embodiment of the invention the heat conducting element is made of aluminium and/or copper. Advantageously, the rotor shaft is made of steel. This leads to a very high stiffness of the rotor shaft allowing for a very good performance of the rotor element as a whole. In a further advantageous embodiment of the invention, with regard to the longitudinal direction of the rotor shaft, the heat conducting element extends at least across a major portion of the rotor shaft. This allows for realising a particularly uniform distribution of temperature field in the rotor shaft. As a consequence, thermal and thermal-based loads as well as thermal deformations of the rotor shaft can be kept to a minimum.
A second aspect of the invention relates to a turbo-machine comprising the rotor element according to the present invention. Advantageous embodiments of the rotor element according to the invention are to be regarded as advantageous embodiments of the turbo-machine according to the invention and vice versa.
By using the heat conducting element for distributing the heat across at least a portion of the rotor shaft, thermal deformations, thermal and thermal-based loads acting upon the rotor shaft can be kept to a minimum. As a consequence, the disappearance of operational gaps between the rotor element and stationary parts of the turbo-machine can be avoided, thus keeping the risk of a damage of the turbo-machine to a minimum.
Further advantages, features, and details of the invention derive from the following description of preferred embodiments as well as from the drawing. The features and feature combinations previously mentioned in the description as well as the features and feature combinations mentioned in the following description of the figures and/or shown in the figures alone can be employed not only in the respective indicated combination but also in any other combination or taken alone without leaving the scope of the invention.
The drawing shows in:
FIG 1 part of a schematic, longitudinal sectional view of a rotor element for a turbo-machine, the rotor element comprising a rotor shaft which has a hollow cross-section at least in a portion of the rotor shaft, wherein the rotor element comprises at least one heat conducting element for distributing heat at least across said portion of the rotor shaft, the heat conducting element being arranged in the hollow cross-section; and
FIG 2 a comparison between a temperature distribution in the rotor element according to FIG 1 and a temperature distribution in the rotor shaft, not being equipped with the heat conducting element.
In the figures the same elements or elements having the same functions are equipped with the same reference. FIG 1 shows a rotor element 10 for a turbo-machine. The turbo-machine, for example, can be a turbo generator. The rotor element 10 comprises a rotor shaft 12 which is, for example, made of steel.
The rotor shaft 12 has a longitudinal direction illustrated by a directional arrow 14. The longitudinal direction coincides with an axis of rotation not shown in FIG 1. The rotor element 10 is rotatable about the axis of rotation and, for example, rotatably supported on a housing of the turbo-machine.
The rotor element 10 can comprise at least one blading region or blade section corresponding to a turbine stage of the turbo-machine. The blading region comprises blades which are mounted on the rotor shaft 12. The rotor element 10 can be driven about the axis of rotation in such a way, that a fluid, for example, in the form of a gas, in particular, steam, can flow through the blading region of the rotor element 10. The turbo-machine in the form of the turbo generator serves for transforming energy contained in the fluid into electric energy. For supporting the rotor element 10 on the housing, at least one bearing element not shown in FIG 1 can be used. The bearing element is, for example, configured as a roller bearing. As can be seen from FIG 1 , the rotor shaft 12 has a hollow cross-section 15 at least in a portion 16 of the rotor shaft 12, the hollow cross-section 15 bounding an orifice 18 of the rotor shaft 12 and being a closed hollow cross-section. With regard to the longitudinal direction of the rotor shaft 12, the hollow cross-section 15 or the orifice 18 extends across a major portion of the rotor shaft 12. The hollow cross-section 15 of the rotor shaft 12 is closed in the longitudinal direction of the rotor shaft 12 at least at one end 20 of the rotor shaft 12.
In order to facilitate a high stiffness of the rotor shaft 12, the rotor shaft 12 is made of steel. As a consequence, a very good performance of the rotor shaft 12 and the rotor element 10 respectively can be realised. In order to realise a very effective and cost-efficient protection of the rotor shaft 12 from thermal and thermal-based loads, the rotor element 10 also comprises at least one heat conducting element in the form of a heat conducting barrel 22. The heat conducting barrel 22 serves for distributing heat at least across the portion 16 of the rotor shaft 12, the heat conducting barrel 22 being arranged in the hollow cross-section 15 or in the orifice 18 respectively.
The heat conducting barrel 22 is made of aluminium. Thereby, the heat conducting barrel 22 is made of a first material (aluminium) which has a higher conductivity than a second material (steel) the rotor shaft 12 is made of. The idea behind using the heat conducting barrel 22 is that the hollow heat conducting barrel 22 mounted in the orifice 18 intensifies heat transfer between hot and cold sides and areas of the rotor shaft 12. During the operation of the turbo generator, due to thermal expansions of the rotor shaft 12 and the heat conducting barrel 22 respectively a very good thermal contact between the heat conducting barrel 22 and the rotor shaft 12 is provided. Thus, the heat or the temperature respectively in the rotor shaft 12 can be distributed very fast and very equally. This results in a very uniform temperature field in the rotor shaft 12, thus only very little thermal deformations and stresses due to thermal loads occur during the operation of the turbo-machine. The usage of the heat conducting barrel 22 allows for protecting rotor epoxy parts of the rotor element 10 from high temperatures. In other words, the temperature gradient in the rotor shaft 12 can be reduced in comparison with the rotor shaft 12 not being equipped with the heat conducting barrel 22. Moreover, the heat conducting barrel 22 does not affect the dynamic performance of the rotor element 10 negatively. By configuring the heat conducting element as the hollow heat conducting barrel 22, the moment of inertia of the heat conducting element and the rotor element 10 as a whole can be kept to a minimum.
The stiffness of the rotor element 10 is increased by the heat conducting barrel 22. Furthermore, the mass or the weight of the rotor element 10 as a whole can be kept very low, because the heat conducting barrel 22 is hollow, too. In other words, the heat conducting element has a hollow cross-section 24 which extends across at least a major portion of the longitudinal extension of the heat conducting barrel 22. As can be seen from FIG 1, the hollow cross-section 24 of the heat conducting barrel 22 is closed in the longitudinal direction of the heat conducting barrel 22 at least at one end 26 of the heat conducting barrel 22.
With regard to the longitudinal extension of the heat conducting barrel 22, at least a major portion of an outer surface 28 of the heat conducting barrel 22 is in thermal contact with an inner surface 30 of the rotor shaft 12, the inner surface 30 bounding the hollow cross-section 15 or the orifice 18 respectively. In the present embodiment according to FIG 1, the surfaces 28, 30 contact each other directly and completely.
The application of the heat conducting element in form of the heat conducting barrel 22 in comparison with the application of cooling ducts and heat pipes is much more efficient with regard to realising a uniform temperature field in the rotor shaft 12. Moreover, the rotor shaft 12 can be equipped with the heat conducting barrel 22 in a very easy and cost-efficient way. Furthermore, the heat conducting barrel 22 allows for a very good protection of the rotor shaft 12 from thermal stresses. Thus, thermal stresses due to the thermal expansion of the rotor shaft 12 and the heat conducting barrel 22 respectively can be kept very low.
Instead of aluminium, the heat conducting barrel 22 can be made of materials having very high thermal conductivities, very low thermal expansions, very good mass properties and only very little production costs respectively. This can give additional benefits to realise a uniform temperature field in the rotor shaft 12.
FIG 2 shows a comparison between the rotor shaft 12 being equipped with the heat conducting barrel 22 and the rotor shaft 12 not being equipped with the heat conducting barrel 22, the rotor shaft 12 not being equipped with the heat conducting barrel 22 being designated by reference 12' in FIG 2. In other words, the rotor shaft 12' shown in FIG 2 is the rotor shaft 12, however, the heat conducting barrel 22 is not arranged in the cross section 15 of the rotor shaft 12'.
The heat conducting barrel 22 causes a very intense heat transfer from the hot distal end 20 to a cold distal end 32 of the rotor shaft 12, the end 32 being arranged at a distance from the end 20 in the longitudinal direction of the rotor shaft 12. This means that the heat conducting barrel 22 supports the distribution of heat across the rotor shaft 12.
Since the rotor shaft 12' is not equipped with a heat conducting element, the distribution of heat across the rotor hast 12' is not supported or intensified. Hence, the end 20 of the rotor shaft 12' has a higher temperature than the end 20 of the rotor shaft 12. Furthermore, the temperature distribution in the rotor shaft 12' is much more uneven than the temperature distribution in the rotor shaft 12. As a consequence, thermal and thermal-based loads acting upon the rotor shaft 12 are much lower than thermal and thermal -based loads acting upon the rotor shaft 12'.

Claims

1. A rotor element (10) for a turbo-machine, the rotor (10) element comprising a rotor shaft (12) which has a hollow cross-section (15) at least in a portion (16) of the rotor shaft (12),
characterized in that
at least one heat conducting element (22) for distributing heat at least across the portion (16) of the rotor shaft (12) is arranged in the hollow cross-section (15) at least partially.
2. The rotor element (10) according to claim 1,
characterized in that
the heat conducting element (22) is made of a first material which has a higher thermal conductivity than a second material the rotor shaft (12) is made of.
3. The rotor element (10) according to any one of claims 1 or 2,
characterized in that
with regard to the longitudinal extension of the heat conducting element (22), at least a major portion of an outer surface (28) of the heat conducting element (22) is in thermal contact with an inner surface (30) of the rotor shaft (12), the inner surface (30) bounding the hollow cross-section (15).
4. The rotor element (10) according to any one of the preceding claims,
characterized in that
the heat conducting element (22) has a hollow cross-section (24) extending at least across a major portion of the longitudinal extension of the heat conducting element (24).
5. The rotor element (10) according to claim 4,
characterized in that
the heat conducting element's (22) hollow cross-section (24) is closed in the longitudinal direction of the heat conducting element (22) at least at one end (26) of the heat conducting element (22).
6. The rotor element (10) according to any one of the preceding claims,
characterized in that
the heat conducting element (22) is made of aluminium and/or copper.
7. The rotor element (10) according to any one of the preceding claims,
characterized in that
the rotor shaft (12) is made of steel.
8. The rotor element (10) according to any one of the preceding claims,
characterized in that
with regard to the longitudinal direction of the rotor shaft (12), the heat conducting element (22) extends at least across a major portion (16) of the rotor shaft (12).
9. A turbo-machine comprising the rotor element (10) according to any one of the preceding claims.
PCT/RU2013/000365 2013-04-25 2013-04-25 Rotor element for a turbo-machine and turbo-machine WO2014175766A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/RU2013/000365 WO2014175766A1 (en) 2013-04-25 2013-04-25 Rotor element for a turbo-machine and turbo-machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2013/000365 WO2014175766A1 (en) 2013-04-25 2013-04-25 Rotor element for a turbo-machine and turbo-machine

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017200828A1 (en) * 2016-05-20 2017-11-23 Borgwarner Inc. Hollow filled turbocharger rotor shaft
EP4117146A1 (en) 2021-07-07 2023-01-11 Celeroton AG Rotor for a high-speed electrical machine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB649465A (en) * 1947-07-11 1951-01-24 Snecma Improvements in and relating to gas turbines
GB962277A (en) * 1961-02-14 1964-07-01 Bbc Brown Boveri & Cie Device for protecting a bearing against heat
US6227799B1 (en) 1997-06-27 2001-05-08 Siemens Aktiengesellschaft Turbine shaft of a steam turbine having internal cooling, and also a method of cooling a turbine shaft
EP1647671A1 (en) * 2004-10-13 2006-04-19 Siemens Aktiengesellschaft Thermally stressed component of a turbomachine
FR2888882A3 (en) * 2005-07-22 2007-01-26 Renault Sas Turbocharger for motor vehicle, has main axle comprising main channel and secondary channels fed by lubricating circuit through appropriate borings formed in axle, where channels are placed at proximity of revolution axis
EP2314878A1 (en) * 2009-10-22 2011-04-27 Honda Motor Co., Ltd. Supercharger
WO2013096462A1 (en) * 2011-12-20 2013-06-27 R. Morley Inc. Shaft for rotating machinery and methods of making and using same

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB649465A (en) * 1947-07-11 1951-01-24 Snecma Improvements in and relating to gas turbines
GB962277A (en) * 1961-02-14 1964-07-01 Bbc Brown Boveri & Cie Device for protecting a bearing against heat
US6227799B1 (en) 1997-06-27 2001-05-08 Siemens Aktiengesellschaft Turbine shaft of a steam turbine having internal cooling, and also a method of cooling a turbine shaft
EP1647671A1 (en) * 2004-10-13 2006-04-19 Siemens Aktiengesellschaft Thermally stressed component of a turbomachine
FR2888882A3 (en) * 2005-07-22 2007-01-26 Renault Sas Turbocharger for motor vehicle, has main axle comprising main channel and secondary channels fed by lubricating circuit through appropriate borings formed in axle, where channels are placed at proximity of revolution axis
EP2314878A1 (en) * 2009-10-22 2011-04-27 Honda Motor Co., Ltd. Supercharger
WO2013096462A1 (en) * 2011-12-20 2013-06-27 R. Morley Inc. Shaft for rotating machinery and methods of making and using same

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017200828A1 (en) * 2016-05-20 2017-11-23 Borgwarner Inc. Hollow filled turbocharger rotor shaft
US10041400B2 (en) 2016-05-20 2018-08-07 Borgwarner Inc. Hollow filled turbocharger rotor shaft
EP4117146A1 (en) 2021-07-07 2023-01-11 Celeroton AG Rotor for a high-speed electrical machine
WO2023280893A1 (en) 2021-07-07 2023-01-12 Celeroton Ag Rotor for a high-speed electrical machine

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