EP1647671A1 - Thermally stressed component of a turbomachine - Google Patents

Thermally stressed component of a turbomachine Download PDF

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Publication number
EP1647671A1
EP1647671A1 EP04024420A EP04024420A EP1647671A1 EP 1647671 A1 EP1647671 A1 EP 1647671A1 EP 04024420 A EP04024420 A EP 04024420A EP 04024420 A EP04024420 A EP 04024420A EP 1647671 A1 EP1647671 A1 EP 1647671A1
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EP
European Patent Office
Prior art keywords
component
rotor
inner material
thermally stressed
weight
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
EP04024420A
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German (de)
French (fr)
Inventor
Werner-Holger Heine
Friedhelm Schmitz
Kai Dr. Wieghardt
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Siemens AG
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Siemens AG
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 AG filed Critical Siemens AG
Priority to EP04024420A priority Critical patent/EP1647671A1/en
Publication of EP1647671A1 publication Critical patent/EP1647671A1/en
Withdrawn legal-status Critical Current

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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
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/207—Heat transfer, e.g. cooling using a phase changing mass, e.g. heat absorbing by melting or boiling
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/172—Copper alloys
    • 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 component in a turbomachine, in particular steam turbine.
  • One way to increase the efficiency of a steam turbine is to use high steam inlet temperatures.
  • steam turbines are designed for steam inlet temperatures of more than 600 ° C.
  • the demands on the materials are particularly high at such high temperatures.
  • thermally resilient materials or through the use of thermal barrier coatings. Cooling by external supply of cooling media has also already been used.
  • a turbine blade which is designed such that solid-formed pins which are made of a material which have a higher thermal conductivity than the material from which the turbine blade is made, are installed in the turbine blade surface, that heat is continuously transported from the hot area in and on the surface of the turbine blade to the cooler area inside the turbine blade.
  • the invention is based on the object to provide a component that is easy to manufacture and is characterized by favorable properties in terms of heat dissipation.
  • thermoly stressed component in a turbomachine, in particular steam turbine, wherein the component consists of an outer material and at least one inner core formed as a second material, wherein the inner material has a higher thermal conductivity than the outer material.
  • a thermally stressed component can be designed more cost-effectively by the use of an outer material and an inner second material.
  • the inner second material is provided in the form of a core.
  • This may be, for example, a single core which, adapted to the outer shape of the component, provides favorable heat dissipation properties. It is also possible that, adapted to an outer shape of the component, a plurality of cores are provided.
  • the outer material may consist of a less expensive base material, which is e.g. leads to a reduction in a wall thickness of the corresponding thermally stressed component.
  • the invention assumes that heat from the hotter area in and on the surface of the thermally stressed component is continuously conducted into the inner area.
  • the inner second material formed with a higher thermal conductivity than the outer material absorbs the heat rapidly, resulting in a rapid uniform distribution of heat in the inner second material.
  • the heat contained in the inner second material can eventually dissipate at the points in the component, which are less thermally stressed.
  • the outer shape of the inner material of the thermal stress of the outer material is adjusted.
  • the inner second material is made of at least 70 wt .-% aluminum, nickel-aluminum base alloy or copper.
  • a copper alloy can serve as a material for the second inner material.
  • low melting materials such as sodium can be used as the inner second material.
  • the aforementioned materials are particularly cost-effective materials presented, which are also characterized by a high thermal conductivity.
  • the thermally stressed component is formed as a rotor.
  • the rotor of a turbomachine in particular steam turbine is thermally heavily loaded on its surface.
  • the rotor is thermally stressed at the location of the steam inlet. As seen in the flow direction, the temperatures on the surface of the rotor decrease.
  • a second internal material which conducts the heat quickly due to its high thermal conductivity compared to the outer material of a thermally stressed point to a less thermally stressed point, the heat energy can dissipate quickly at the less thermally stressed point.
  • the component is designed as a turbine blade.
  • FIG. 1 shows a section through a thermally stressed component 1.
  • the thermally stressed component 1 is formed as a rotor.
  • live steam will flow at an inflow region 2 onto a rotor surface 3.
  • the rotor surface 3 is subjected to high thermal stress at this point.
  • the heat propagates from the rotor surface 3 into the interior of the rotor.
  • the rotor is made with at least one inner core material 2, with the inner material 4 having a higher thermal conductivity than the outer material 5.
  • the inner material 4 is executed in the embodiment of FIG. 1 rotationally symmetrical to the axis of rotation 6.
  • the inner material 4 may have other shapes.
  • the outer shape of the inner material 4 can be formed such that the distribution of the heat on the rotor surface 3 is taken into account and thus the thermal load of the outer material 5 is adjusted.
  • the live steam flows in a flow direction 7 along the rotor surface 3.
  • the temperature of the live steam decreases this off.
  • the temperature of the rotor surface 3 in a downstream second region 8 is generally lower than in the inflow region 2.
  • Fig. 2 is a section through the line I-I shown.
  • FIG. 3 shows a turbine blade 9 as an embodiment of a thermally stressed component 1.
  • the turbine blade 9 is made of an outer material 10 and at least one inner material 11, which is formed as a core, wherein the inner material 11 has a higher thermal conductivity than the outer material 10th
  • the turbine blade 9 is subjected to high thermal stress in the flow region 12.
  • the temperature is generally lower than in the flow region 12.
  • the inner material 11 is made of at least 70% by weight of aluminum, nickel-aluminum base alloy, copper, copper alloy or low melting materials such as sodium, except for manufacturing impurities.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Steam tubine blade comprising an outer material (5) and an inner material (4) as core where the heat conductivity of the inner material is higher than that of the outer material.

Description

Die Erfindung betrifft ein Bauteil in einer Strömungsmaschine, insbesondere Dampfturbine.The invention relates to a component in a turbomachine, in particular steam turbine.

Eine Möglichkeit um den Wirkungsgrad einer Dampfturbine zu erhöhen, ist der Einsatz von hohen Dampfeinlasstemperaturen. Zur Zeit werden Dampfturbinen für Dampfeinlasstemperaturen von mehr als 600°C ausgelegt. Die Anforderungen an die Materialien sind bei solch hohen Temperaturen besonders hoch.One way to increase the efficiency of a steam turbine is to use high steam inlet temperatures. At present, steam turbines are designed for steam inlet temperatures of more than 600 ° C. The demands on the materials are particularly high at such high temperatures.

Eine Möglichkeit thermisch belastete Bauteile einer Dampfturbine vor thermischer Überlastung zu schützen, besteht durch den Einsatz thermisch belastbarer Materialien oder durch den Einsatz von Wärmedämmschichten. Kühlung durch externe Zufuhr von Kühlmedien ist auch bereits eingesetzt worden.One way to protect thermally stressed components of a steam turbine from thermal overload is through the use of thermally resilient materials or through the use of thermal barrier coatings. Cooling by external supply of cooling media has also already been used.

In der DE 199 26 817 wird eine Turbinenschaufel vorgestellt, die derart ausgebildet ist, dass massiv ausgebildete Stifte die aus einem Werkstoff gefertigt sind, die eine höhere Wärmeleitfähigkeit aufweisen als der Werkstoff, aus der die Turbinenschaufel gefertigt ist, derart in die Turbinenschaufeloberfläche eingebaut sind, dass Wärme kontinuierlich aus dem heißen Bereich in und an der Oberfläche der Turbinenschaufel in den kühleren Bereich im Inneren der Turbinenschaufel transportiert wird.In DE 199 26 817 a turbine blade is presented, which is designed such that solid-formed pins which are made of a material which have a higher thermal conductivity than the material from which the turbine blade is made, are installed in the turbine blade surface, that heat is continuously transported from the hot area in and on the surface of the turbine blade to the cooler area inside the turbine blade.

Der Erfindung liegt die Aufgabe zu Grunde, ein Bauteil anzugeben, das einfach herzustellen ist und sich durch günstige Eigenschaften hinsichtlich einer Wärmeableitung auszeichnet.The invention is based on the object to provide a component that is easy to manufacture and is characterized by favorable properties in terms of heat dissipation.

Diese Aufgabe wird durch ein thermisch beanspruchtes Bauteil in einer Strömungsmaschine, insbesondere Dampfturbine, gelöst, wobei das Bauteil aus einem äußeren Material und wenigstens einem inneren, als Kern ausgebildeten, zweiten Material besteht, wobei das innere Material eine höhere Wärmeleitfähigkeit aufweist als das äußere Material.This object is achieved by a thermally stressed component in a turbomachine, in particular steam turbine, wherein the component consists of an outer material and at least one inner core formed as a second material, wherein the inner material has a higher thermal conductivity than the outer material.

Die Erfindung geht davon aus, dass durch den Einsatz von einem äußeren Material und einem inneren zweiten Material ein thermisch beanspruchtes Bauteil kostengünstiger ausgelegt werden kann. Dabei ist das innere zweite Material in Form eines Kerns vorgesehen. Dies kann beispielsweise ein einziger Kern sein, der an die äußere Form des Bauteils angepasst für günstige Wärmeableiteigenschaften sorgt. Es ist ebenso möglich, dass, angepasst an eine äußere Form des Bauteils, mehrere Kerne vorgesehen sind. Insbesondere kann hierbei das äußere Material aus einem kostengünstigeren Grundmaterial bestehen, was z.B. zu einer Reduzierung einer Wandstärke des entsprechenden thermisch beanspruchten Bauteils führt.The invention assumes that a thermally stressed component can be designed more cost-effectively by the use of an outer material and an inner second material. In this case, the inner second material is provided in the form of a core. This may be, for example, a single core which, adapted to the outer shape of the component, provides favorable heat dissipation properties. It is also possible that, adapted to an outer shape of the component, a plurality of cores are provided. In particular, in this case, the outer material may consist of a less expensive base material, which is e.g. leads to a reduction in a wall thickness of the corresponding thermally stressed component.

Die Erfindung geht davon aus, dass kontinuierlich Wärme aus dem heißeren Bereich in und an der Oberfläche des thermisch beanspruchten Bauteils in den inneren Bereich geleitet wird. Das mit einer höheren Wärmeleitfähigkeit als das äußere Material ausgebildete innere zweite Material nimmt die Wärme schnell auf, was zu einer schnellen Gleichverteilung der Wärme im inneren zweiten Material führt. Die im inneren zweiten Material enthaltene Wärme kann schließlich an den Stellen im Bauteil dissipieren, die weniger thermisch beansprucht werden.The invention assumes that heat from the hotter area in and on the surface of the thermally stressed component is continuously conducted into the inner area. The inner second material formed with a higher thermal conductivity than the outer material absorbs the heat rapidly, resulting in a rapid uniform distribution of heat in the inner second material. The heat contained in the inner second material can eventually dissipate at the points in the component, which are less thermally stressed.

In einer vorteilhaften Ausgestaltung der Erfindung wird die äußere Form des inneren Materials der thermischen Belastung des äußeren Materials angepasst.In an advantageous embodiment of the invention, the outer shape of the inner material of the thermal stress of the outer material is adjusted.

Dadurch ist es möglich, gezielt eine Massenverteilung des inneren Materials an den Stellen im Bauteil zu erhöhen, wo Wärme besonders schnell abgeführt werden muss.This makes it possible to selectively increase a mass distribution of the inner material at the points in the component where heat must be removed very quickly.

In einer vorteilhaften Ausgestaltung wird das innere zweite Material aus wenigstens 70 Gew.-% Aluminium, Nickel-Aluminium-Basislegierung oder Kupfer hergestellt. Auch eine Kupferlegierung kann als Material für das zweite innere Material dienen. Ebenso können niedrigschmelzende Materialien wie Natrium als inneres zweites Material eingesetzt werden. Durch die vorgenannten Materialien sind besonders kostengünstige Materialien vorgestellt, die sich darüber hinaus durch eine hohe Wärmeleitfähigkeit auszeichnen.In an advantageous embodiment, the inner second material is made of at least 70 wt .-% aluminum, nickel-aluminum base alloy or copper. Also, a copper alloy can serve as a material for the second inner material. Similarly, low melting materials such as sodium can be used as the inner second material. The aforementioned materials are particularly cost-effective materials presented, which are also characterized by a high thermal conductivity.

Zweckdienlicherweise wird das thermisch beanspruchte Bauteil als Rotor ausgebildet.Conveniently, the thermally stressed component is formed as a rotor.

Gerade der Rotor einer Strömungsmaschine, insbesondere Dampfturbine wird an seiner Oberfläche thermisch stark belastet. In der Regel wird der Rotor am Ort des Dampfeinlasses thermisch stark beansprucht. In Strömungsrichtung gesehen, sinken die Temperaturen auf der Oberfläche des Rotors. Durch den Einsatz eines zweiten inneren Materials, das die Wärme durch seine hohe Wärmeleitfähigkeit im Vergleich zu dem äußeren Material schnell von einer thermisch stark beanspruchten Stelle zu einer weniger thermisch beanspruchten Stelle leitet, kann die Wärmeenergie an der thermisch weniger stark beanspruchten Stelle schnell dissipieren.Especially the rotor of a turbomachine, in particular steam turbine is thermally heavily loaded on its surface. In general, the rotor is thermally stressed at the location of the steam inlet. As seen in the flow direction, the temperatures on the surface of the rotor decrease. By using a second internal material, which conducts the heat quickly due to its high thermal conductivity compared to the outer material of a thermally stressed point to a less thermally stressed point, the heat energy can dissipate quickly at the less thermally stressed point.

In einer weiteren Ausgestaltung wird das Bauteil als Turbinenschaufel ausgeführt.In a further embodiment, the component is designed as a turbine blade.

Neben dem Rotor werden insbesondere Turbinenschaufeln thermisch besonders stark beansprucht. Auch hier wird durch den Einsatz eines zweiten inneren Materials, das eine höhere Wärmeleitfähigkeit aufweist als das äußere Material die Wärme von Stellen starker thermischer Beanspruchung an Stellen weniger starker thermischer Beanspruchung weitergeleitet und dort dissipieren.In addition to the rotor turbine blades in particular are thermally stressed particularly strong. Again, by the use of a second inner material, which has a higher thermal conductivity than the outer material, the heat passed from places of high thermal stress in places less severe thermal stress and dissipate there.

Anhand der nachfolgenden Beschreibung werden Ausführungsbeispiele der Erfindung unter Bezugnahme auf die Zeichnungen noch näher erläutert. Dabei zeigen:

Fig. 1
einen Querschnitt durch einen Rotor einer Dampfturbine;
Fig. 2
ein Schnitt I-I durch den Rotor aus Fig. 1;
Fig. 3
ein Schnitt durch eine erfindungsgemäße Turbinenschaufel.
Reference to the following description, embodiments of the invention will be explained in more detail with reference to the drawings. Showing:
Fig. 1
a cross section through a rotor of a steam turbine;
Fig. 2
a section II through the rotor of Fig. 1;
Fig. 3
a section through a turbine blade according to the invention.

In Figur 1 ist ein Schnitt durch ein thermisch beanspruchtes Bauteil 1 dargestellt. Im Ausführungsbeispiel gemäß Fig. 1 ist das thermisch beanspruchte Bauteil 1 als Rotor ausgebildet. In der Regel wird Frischdampf an einem Einströmbereich 2 auf eine Rotoroberfläche 3 strömen. Die Rotoroberfläche 3 wird an dieser Stelle stark thermisch beansprucht. Die Wärme breitet sich von der Rotoroberfläche 3 in das Innere des Rotors aus. Der Rotor ist mit wenigstens einem inneren, als Kern ausgebildeten, zweiten Material 4 hergestellt, wobei das innere Material 4 eine höhere Wärmeleitfähigkeit aufweist als das äußere Material 5.FIG. 1 shows a section through a thermally stressed component 1. In the embodiment of FIG. 1, the thermally stressed component 1 is formed as a rotor. As a rule, live steam will flow at an inflow region 2 onto a rotor surface 3. The rotor surface 3 is subjected to high thermal stress at this point. The heat propagates from the rotor surface 3 into the interior of the rotor. The rotor is made with at least one inner core material 2, with the inner material 4 having a higher thermal conductivity than the outer material 5.

Das innere Material 4 ist im Ausführungsbeispiel gemäß Fig. 1 rotationssymmetrisch zur Rotationsachse 6 ausgeführt. In alternativen Ausführungsformen kann das innere Material 4 andere Formen aufweisen. Insbesondere kann die äußere Form des inneren Materials 4 derart ausgebildet werden, dass die Verteilung der Wärme auf der Rotoroberfläche 3 berücksichtigt wird und somit der thermischen Belastung des äußeren Materials 5 angepasst ist.The inner material 4 is executed in the embodiment of FIG. 1 rotationally symmetrical to the axis of rotation 6. In alternative embodiments, the inner material 4 may have other shapes. In particular, the outer shape of the inner material 4 can be formed such that the distribution of the heat on the rotor surface 3 is taken into account and thus the thermal load of the outer material 5 is adjusted.

Der Frischdampf strömt in einer Strömungsrichtung 7 entlang der Rotoroberfläche 3. Die Temperatur des Frischdampfes nimmt hierbei ab. Die Temperatur der Rotoroberfläche 3 in einem stromabwärts liegenden zweiten Bereich 8 ist in der Regel niedriger als im Einströmbereich 2. Die Wärme, die im Einströmbereich 2 vom inneren Material 4 aufgenommen wird und in Folge der hohen Wärmeleitfähigkeit an den zweiten Bereich 8 schnell geführt wird, disspiert im zweiten Bereich 8.The live steam flows in a flow direction 7 along the rotor surface 3. The temperature of the live steam decreases this off. The temperature of the rotor surface 3 in a downstream second region 8 is generally lower than in the inflow region 2. The heat that is absorbed by the inner material 4 in the inflow region 2 and is conducted rapidly to the second region 8 as a result of the high thermal conductivity, dissipates in the second area 8.

In Fig. 2 ist ein Schnitt durch die Linie I-I dargestellt.In Fig. 2 is a section through the line I-I shown.

In Fig. 3 ist eine Turbinenschaufel 9 als Ausführungsform eines thermisch beanspruchten Bauteils 1 dargestellt. Die Turbinenschaufel 9 besteht aus einem äußeren Material 10 und wenigstens einem inneren Material 11, das als Kern ausgebildet ist, wobei das innere Material 11 eine höhere Wärmeleitfähigkeit aufweist als das äußere Material 10.FIG. 3 shows a turbine blade 9 as an embodiment of a thermally stressed component 1. The turbine blade 9 is made of an outer material 10 and at least one inner material 11, which is formed as a core, wherein the inner material 11 has a higher thermal conductivity than the outer material 10th

In der Regel wird die Turbinenschaufel 9 im Strömungsbereich 12 thermisch stark beansprucht. Im Schaufelfußbereich 13 ist die Temperatur in der Regel geringer als im Strömungsbereich 12. Die Wärme, die im Strömungsbereich 12 ins Innere der Turbinenschaufel 9 geleitet wird, wird durch das innere Material 11 schnell zum Schaufelfußbereich 13 in Folge der hohen Wärmeleitfähigkeit gegenüber dem äußeren Material 10 geleitet und dort schließlich schnell dissipiert.As a rule, the turbine blade 9 is subjected to high thermal stress in the flow region 12. In the blade root region 13, the temperature is generally lower than in the flow region 12. The heat which is conducted in the flow region 12 into the interior of the turbine blade 9, by the inner material 11 quickly to Schaufelfußbereich 13 due to the high thermal conductivity compared to the outer material passed and finally dissipated there quickly.

Das innere Material 11 wird abgesehen von herstellungsbedingten Verunreinigungen aus wenigstens 70 Gew.-% Aluminium, Nickel-Aluminium-Basislegierung, Kupfer, Kupferlegierung oder niedrigschmelzenden Materialien wie Natrium hergestellt.The inner material 11 is made of at least 70% by weight of aluminum, nickel-aluminum base alloy, copper, copper alloy or low melting materials such as sodium, except for manufacturing impurities.

Claims (12)

Bauteil (1) einer Strömungsmaschine, insbesondere Dampfturbine,
dadurch gekennzeichnet, dass
das Bauteil (1) aus einem äußeren Material (5, 10) und wenigstens einem inneren, als Kern ausgebildeten, zweiten Material (4, 11) besteht, wobei das innere Material (4, 11) eine höhere Wärmeleitfähigkeit aufweist als das äußere Material(5, 10).Component (1) of a turbomachine, in particular steam turbine,
characterized in that
the component (1) consists of an outer material (5, 10) and at least one inner, second core material (4, 11), the inner material (4, 11) having a higher thermal conductivity than the outer material ( 5, 10). Bauteil (1) nach Anspruch 1,
dadurch gekennzeichnet, dass
die äußere Form des inneren Materials (4, 11) an eine thermische Belastung des äußeren Materials (5, 10) angepasst ist.Component (1) according to claim 1,
characterized in that
the outer shape of the inner material (4, 11) is adapted to a thermal loading of the outer material (5, 10). Bauteil (1) nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass
das innere Material (4, 11) aus wenigstens 70 Gew.-% Aluminium hergestellt ist.Component (1) according to claim 1 or 2,
characterized in that
the inner material (4, 11) is made of at least 70% by weight of aluminum. Bauteil (1) nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass
das innere Material (4, 11) aus wenigstens 70 Gew.-% einer Nickel-Aluminium-Basislegierung hergestellt ist.Component (1) according to claim 1 or 2,
characterized in that
the inner material (4, 11) is made of at least 70% by weight of a nickel-aluminum base alloy. Bauteil (1) nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass
das innere Material (4, 11) aus wenigstens 70 Gew.-% Kupfer hergestellt ist.Component (1) according to claim 1 or 2,
characterized in that
the inner material (4, 11) is made of at least 70% by weight of copper. Bauteil (1) nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass
das innere Material (4, 11) aus wenigstens 70 Gew.-% einer Kupferlegierung hergestellt ist.Component (1) according to claim 1 or 2,
characterized in that
the inner material (4, 11) is made of at least 70% by weight of a copper alloy. Bauteil (1) nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass
das innere Material (4, 11) aus wenigstens 70 Gew.-% eines niedrig schmelzenden Materials hergestellt ist.Component (1) according to claim 1 or 2,
characterized in that
the inner material (4, 11) is made of at least 70% by weight of a low melting material. Bauteil (1) nach Anspruch 7,
dadurch gekennzeichnet, dass
das innere Material (4, 11) aus Natrium hergestellt ist.Component (1) according to claim 7,
characterized in that
the inner material (4, 11) is made of sodium. Bauteil (1) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass
das Bauteil als Rotor ausgebildet ist.Component (1) according to one of the preceding claims,
characterized in that
the component is designed as a rotor. Bauteil (1) nach Anspruch 9,
dadurch gekennzeichnet, dass
der Kern entlang einer Achse des Rotors angeordnet ist.Component (1) according to claim 9,
characterized in that
the core is disposed along an axis of the rotor. Bauteil (1) nach einem der Ansprüche 1 - 8,
dadurch gekennzeichnet, dass
das Bauteil als Turbinenschaufel (9) ausgebildet ist.Component (1) according to one of claims 1 - 8,
characterized in that
the component is designed as a turbine blade (9). Bauteil (1) nach Anspruch 11,
dadurch gekennzeichnet, dass
der Kern in Längsrichtung der Turbinenschaufel (9) in einem Schaufelfußbereich (13) verläuft.Component (1) according to claim 11,
characterized in that
the core extends in the longitudinal direction of the turbine blade (9) in a Schaufelfußbereich (13).
EP04024420A 2004-10-13 2004-10-13 Thermally stressed component of a turbomachine Withdrawn EP1647671A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04024420A EP1647671A1 (en) 2004-10-13 2004-10-13 Thermally stressed component of a turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04024420A EP1647671A1 (en) 2004-10-13 2004-10-13 Thermally stressed component of a turbomachine

Publications (1)

Publication Number Publication Date
EP1647671A1 true EP1647671A1 (en) 2006-04-19

Family

ID=34926980

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04024420A Withdrawn EP1647671A1 (en) 2004-10-13 2004-10-13 Thermally stressed component of a turbomachine

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Country Link
EP (1) EP1647671A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1873356A1 (en) * 2006-06-30 2008-01-02 Siemens Aktiengesellschaft Shaft for turbomachine and process for manufacturing
WO2014175766A1 (en) * 2013-04-25 2014-10-30 Siemens Aktiengesellschaft Rotor element for a turbo-machine and turbo-machine
WO2017200828A1 (en) * 2016-05-20 2017-11-23 Borgwarner Inc. Hollow filled turbocharger rotor shaft
FR3074519A1 (en) * 2017-12-04 2019-06-07 Safran Aircraft Engines ROTARY PIECE FOR TURBOMACHINE

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE559676C (en) * 1931-08-20 1932-09-22 E H Hans Holzwarth Dr Ing Method for cooling blades, in particular for internal combustion turbines
US2256479A (en) * 1938-03-21 1941-09-23 Holzwarth Gas Turbine Co Blade for rotary machines operated by high temperature media
FR969557A (en) * 1947-08-07 1950-12-21 Improvements to the rotors of turbines or the like
US2659530A (en) * 1947-07-11 1953-11-17 Construction De Moteurs D Avia Hollow drive shaft construction for turbine driven compressors
CH381026A (en) * 1961-02-14 1964-08-15 Bbc Brown Boveri & Cie Thermal protection of a warehouse
DE1476730A1 (en) * 1966-06-30 1970-03-26 Winter Dr Heinrich Combination materials for turbine blades
US3623825A (en) * 1969-11-13 1971-11-30 Avco Corp Liquid-metal-filled rotor blade

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE559676C (en) * 1931-08-20 1932-09-22 E H Hans Holzwarth Dr Ing Method for cooling blades, in particular for internal combustion turbines
US2256479A (en) * 1938-03-21 1941-09-23 Holzwarth Gas Turbine Co Blade for rotary machines operated by high temperature media
US2659530A (en) * 1947-07-11 1953-11-17 Construction De Moteurs D Avia Hollow drive shaft construction for turbine driven compressors
FR969557A (en) * 1947-08-07 1950-12-21 Improvements to the rotors of turbines or the like
CH381026A (en) * 1961-02-14 1964-08-15 Bbc Brown Boveri & Cie Thermal protection of a warehouse
DE1476730A1 (en) * 1966-06-30 1970-03-26 Winter Dr Heinrich Combination materials for turbine blades
US3623825A (en) * 1969-11-13 1971-11-30 Avco Corp Liquid-metal-filled rotor blade

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1873356A1 (en) * 2006-06-30 2008-01-02 Siemens Aktiengesellschaft Shaft for turbomachine and process for manufacturing
WO2014175766A1 (en) * 2013-04-25 2014-10-30 Siemens Aktiengesellschaft Rotor element for a turbo-machine and turbo-machine
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
FR3074519A1 (en) * 2017-12-04 2019-06-07 Safran Aircraft Engines ROTARY PIECE FOR TURBOMACHINE

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