WO2005119030A1 - Turbine hub cooling system for exhaust-gas turbines - Google Patents

Turbine hub cooling system for exhaust-gas turbines Download PDF

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Publication number
WO2005119030A1
WO2005119030A1 PCT/CH2004/000341 CH2004000341W WO2005119030A1 WO 2005119030 A1 WO2005119030 A1 WO 2005119030A1 CH 2004000341 W CH2004000341 W CH 2004000341W WO 2005119030 A1 WO2005119030 A1 WO 2005119030A1
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WO
WIPO (PCT)
Prior art keywords
turbine
hub
housing
turbine wheel
cooling
Prior art date
Application number
PCT/CH2004/000341
Other languages
German (de)
French (fr)
Inventor
Martin Seiler
Original Assignee
Abb Turbo Systems 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 Abb Turbo Systems Ag filed Critical Abb Turbo Systems Ag
Priority to PCT/CH2004/000341 priority Critical patent/WO2005119030A1/en
Publication of WO2005119030A1 publication Critical patent/WO2005119030A1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/046—Heating, heat insulation 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to the field of exhaust gas turbochargers. It relates to an exhaust gas turbine according to the preamble of patent claim 1.
  • Exhaust gas turbochargers are used to increase the performance of fuel engines.
  • the exhaust gas turbochargers are operated at ever higher speeds.
  • the turbines of the exhaust gas turbocharger are loaded to the current state.
  • the expected service life of the turbine calculated as the time span from the stress to the failure of the turbine, depends mainly on two parameters, the aterial temperature of the turbine wheel and the speed, or the peripheral speed.
  • the blades in the hot entry area of the turbine wheel are particularly loaded. In order to cope with the increased load, the blades have to be built more solidly. However, if the blades are reinforced to achieve higher speeds under creep stress, this has a disadvantageous effect on the bursting behavior. The blades do not separate from the hub and the hub bursts.
  • the invention has for its object to provide a turbine in which the blades of the turbine wheel separate from the hub during natural bursting and which can still be operated at high speeds. According to the invention, this object is achieved with a turbine having the features of patent claim 1.
  • the turbine according to the invention has a cooled turbine wheel.
  • the hub of the turbine wheel is cooled via a cooling duct arranged in the adjacent turbine housing.
  • the resulting lower material temperatures in the turbine wheel allow high speeds when the creep load is applied without the need to thicken the blades.
  • the thin blades disengage from the hub during natural bursting.
  • the cooling of the turbine wheel according to the invention in combination with the thin blades at the same time guarantees high application limits and low manufacturing costs through reduced burst protection measures on the turbine housing.
  • the housing wall between the cooling channel and the turbine hub rear wall can contain a material with improved thermal conductivity.
  • this heat-conducting housing wall can have a surface-enlarging structure, both in the interior of the cooling channel and in relation to the rear wall of the turbine hub.
  • the rear wall of the turbine hub can also be provided with a corresponding surface-enlarging structure in order to improve the heat transfer. Further advantages result from the dependent claims.
  • FIG. 1 is a schematic sectional view of a turbine according to the invention with a cooling chamber
  • FIG. 2 shows a schematic sectional illustration of the turbine according to the invention with a cooling chamber wall with a surface-enlarging structure
  • FIG 3 shows a schematic sectional illustration of the turbine according to the invention with a cooling chamber wall and a turbine wheel hub rear wall with a surface-enlarging structure.
  • FIG. 1 schematically shows the turbine according to the invention.
  • Turbine housing 21, 22, a rotatable turbine wheel is arranged.
  • the turbine wheel comprises a hub 11 and several arranged on the front of the hub; Blades 15 and is connected via a shaft 30 to the compressor wheel, not shown.
  • the turbine housing with the gas inlet side housing part 22 to the left of the turbine wheel and the gas outlet side housing part 21 forms, together with the hub of the turbine wheel, a flow channel 40, in which hot exhaust gases flow through during operation of the exhaust gas turbocharger (see large arrow).
  • the turbine can be designed as a pure radial turbine, with a radial inflow and axial exit of the exhaust gases, or, as shown in FIG. 2, as a so-called mixed flow turbine with an inflow with radial and axial components and an axial exit.
  • a cooling duct 50 is embedded in the back of the hub of the turbine wheel, in the housing 22 on the gas inlet side.
  • the cooling channel extends radially along the hub of the turbine wheel in order to enable it to be optimally cooled.
  • the hub of the turbine wheel is drawn up radially on its rear side 12 up to the gas inlet edges 16 of the rotor blades, as a result of which the heat can be taken directly from the area with the greatest thermal load.
  • the blades are cooled via the hub and can be made less solid thanks to the lower thermal load. Without cooling, the blades would have to be much stronger in the area of the hub attachment, which would make it impossible to detach the blades from the hub in the event of a burst.
  • the hub In the circumferential direction between the blades, the hub can be used to save weight and reduce the moment of inertia with a radial after provided on the inside directed arch edge, and so be guided a little less radially outwards.
  • a heat-transmitting housing wall 23 is arranged between the cooling duct 50 and the rear 12 of the hub of the turbine wheel.
  • the heat from the hub of the turbine wheel is extracted according to the invention through the rear wall 12 of the hub of the turbine wheel and through the heat-transferring housing wall 23 and dissipated to a heat exchanger via a cooling medium, for example cooling water or oil.
  • the heat-transmitting housing wall can contain a material that has an improved thermal conductivity.
  • it can be treated with a subsequently applied material in the corresponding housing wall or made entirely of another material as an independent housing part and connected to the rest of the turbine housing in a positive or non-positive manner.
  • FIG. 2 Another measure is shown in FIG. 2.
  • the corresponding inside of the heat transferring housing wall 24 is provided with a surface-enlarging structure.
  • several fins are provided, which are washed by the cooling medium.
  • Other surface-enlarging structures would also be possible, for example porous material through which the cooling medium flows, or several small cooling channels in the housing wall.
  • the surface rear wall 13 of the hub of the turbine wheel and the opposite heat-transmitting housing wall 25 can also be provided with a surface-enlarged structure according to FIG. 3. More heat can be transported via the enlarged surface, which improves the overall heat flow, indicated by the small arrows.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

The inventive turbine comprises a cooled turbine wheel. The hub (11) of the turbine wheel is cooled by means of a cooling channel (50) that is configured in the neighbouring turbine housing (22). The lower material temperatures thus achieved in the turbine wheel permit high speeds under creep stress, without the need for thicker blades. The thin vanes become detached from the hub by natural cracking.

Description

B E S C H R E I B U N G DESCRIPTION
TURBINENNABENKUHLUNG FÜR ABGASTURBINETURBINE HUB COOLING FOR EXHAUST TURBINE
Technisches GebietTechnical field
Die Erfindung bezieht sich auf das Gebiet der Abgasturbolader. Sie betrifft eine Abgasturbine gemäss dem Oberbegriff des Patentanspruchs 1.The invention relates to the field of exhaust gas turbochargers. It relates to an exhaust gas turbine according to the preamble of patent claim 1.
Stand der TechnikState of the art
Abgasturbolader werden zur Leistungssteigerung von Brennstoffmotoren eingesetzt. Um verdichterseitig das Druckverhältnis zu steigern werden die Abgasturbolader mit immer höheren Drehzahlen betrieben. Bei vielen Anwendungen werden dabei die Turbinen der Abgasturbolader auf Zeitstand belastet. Die erwartete Lebensdauer der Turbine, gerechnet als Zeitspanne der Beanspruchung bis zum Versagen der Turbine, hängt hierbei hauptsächlich von zwei Parametern, der aterialtemperatur des Turbinenrades und der Drehzahl, bzw. der Umfangsgeschwindigkeit, ab. Dabei sind insbesondere die Schaufeln im heissen Eintrittsbereich des Turbinenrades belastet. Um der erhöhten Belastung gerecht zu werden, müssen die Schaufeln massiver gebaut werden. Werden zum Erreichen höherer Drehzahlen unter Zeitstandbelastung die Schaufeln jedoch verstärkt, so wirkt sich dies nachteilig auf das Berstverhalten aus. Die Schaufeln trennen sich nicht von der Nabe und es kommt zum Nabenbersten.Exhaust gas turbochargers are used to increase the performance of fuel engines. In order to increase the pressure ratio on the compressor side, the exhaust gas turbochargers are operated at ever higher speeds. In many applications, the turbines of the exhaust gas turbocharger are loaded to the current state. The expected service life of the turbine, calculated as the time span from the stress to the failure of the turbine, depends mainly on two parameters, the aterial temperature of the turbine wheel and the speed, or the peripheral speed. The blades in the hot entry area of the turbine wheel are particularly loaded. In order to cope with the increased load, the blades have to be built more solidly. However, if the blades are reinforced to achieve higher speeds under creep stress, this has a disadvantageous effect on the bursting behavior. The blades do not separate from the hub and the hub bursts.
Es ist günstig, wenn sich beim natürlichen Bersten der Turbine durch Überdrehzahl die Schaufeln von der Nabe trennen und nicht, wie oben beschrieben, die Nabe selbst versagt. Dadurch können die Berstschutzmassnahmen reduziert werden, was sich vorteilhaft auf die Herstellkosten auswirkt. Schwächt man die Schaufeln soweit, dass sie beim natürlichen Bersten vor der Nabe versagen, sind bei Zeitstandbelastung nur relativ tiefe Drehzahlen zu erreichen. Kurze Darstellung der ErfindungIt is advantageous if the turbine bursts naturally due to overspeed and the blades separate from the hub and not, as described above, the hub itself fails. As a result, the burst protection measures can be reduced, which has an advantageous effect on the production costs. If the blades are weakened to such an extent that they fail to burst naturally in front of the hub, only relatively low speeds can be achieved when the creep is loaded. Brief description of the invention
Der Erfindung liegt die Aufgabe zugrunde, eine Turbine zu schaffen, bei welcher sich die Laufschaufeln des Turbinenrades beim natürlichen Bersten von der Nabe trennen und die dennoch bei hohen Drehzahlen betrieben werden kann. Erfindungsgemäss wird diese Aufgabe mit einer Turbine mit den Merkmalen des Patentanspruchs 1 gelöst.The invention has for its object to provide a turbine in which the blades of the turbine wheel separate from the hub during natural bursting and which can still be operated at high speeds. According to the invention, this object is achieved with a turbine having the features of patent claim 1.
Die erfindungsgemässe Turbine weist ein gekühltes Turbinenrad auf. Dabei wird die Nabe des Turbinenrades über einen im benachbarten Turbinengehäuse angeordneten Kühlkanal gekühlt. Die dadurch erreichten tieferen Materialtemperaturen im Turbinenrad erlauben bei Zeitstandbelastung hohe Drehzahlen, ohne dass die Schaufeln verdickt werden müssen. Die dünnen Laufschaufeln lösen sich beim natürlichen Bersten von der Nabe.The turbine according to the invention has a cooled turbine wheel. The hub of the turbine wheel is cooled via a cooling duct arranged in the adjacent turbine housing. The resulting lower material temperatures in the turbine wheel allow high speeds when the creep load is applied without the need to thicken the blades. The thin blades disengage from the hub during natural bursting.
Die erfindungsgemässe Kühlung des Turbinenrades in Kombination mit den dünnen Schaufeln gewährleistet zugleich hohe Einsatzgrenzen und tiefe Herstellungskosten durch reduzierte Berstschutzmassnahmen am Turbinengehäuse.The cooling of the turbine wheel according to the invention in combination with the thin blades at the same time guarantees high application limits and low manufacturing costs through reduced burst protection measures on the turbine housing.
Zur Verbesserung des Kühleffekts können weitere Massnahmen vorgesehen sein.Further measures can be provided to improve the cooling effect.
Beispielsweise kann die Gehäusewand zwischen dem Kühlkanai und der Turbinennabenrückwand ein Material mit verbesserter Wärmeleitfähigkeit enthalten.For example, the housing wall between the cooling channel and the turbine hub rear wall can contain a material with improved thermal conductivity.
Weiter kann die Oberfläche dieser wärmeleitenden Gehäusewand eine Oberflächenvergrössernde Struktur aufweisen, sowohl im Innern des Kühlkanals als auch gegenüber der Rückwand der Turbinennabe.Furthermore, the surface of this heat-conducting housing wall can have a surface-enlarging structure, both in the interior of the cooling channel and in relation to the rear wall of the turbine hub.
Auch die Rückwand der Turbinennabe kann mit einer entsprechenden oberflächenvergrössernden Struktur versehen sein, um die Wärmeübertragung zu verbessern. Weitere Vorteile ergeben sich aus den abhängigen Ansprüchen.The rear wall of the turbine hub can also be provided with a corresponding surface-enlarging structure in order to improve the heat transfer. Further advantages result from the dependent claims.
Kurze Beschreibung der ZeichnungenBrief description of the drawings
Im folgenden sind anhand der Figuren verschiedene Ausführungsformen der erfindungsgemässen Turbine schematisch dargestellt und näher erläutert.Various embodiments of the turbine according to the invention are shown schematically and explained in more detail below with reference to the figures.
In allen Figuren sind gleichwirkende Elemente mit gleichen Bezugszeichen versehen. Es zeigen:In all figures, elements having the same effect are provided with the same reference symbols. Show it:
Fig. 1 eine schematische Schnittdarstellung einer erfindungsgemässen Turbine mit einer Kühlkammer,1 is a schematic sectional view of a turbine according to the invention with a cooling chamber,
Fig. 2 eine schematische Schnittdarstellung der erfindungsgemässen Turbine mit einer Kühlkammerwand mit oberflächenvergrössemder Struktur, und2 shows a schematic sectional illustration of the turbine according to the invention with a cooling chamber wall with a surface-enlarging structure, and
Fig. 3 eine schematische Schnittdarstellung der erfindungsgemässen Turbine mit einer Kühlkammerwand und einer Turbinenradnabenrückwand mit oberflächenvergrössemder Struktur.3 shows a schematic sectional illustration of the turbine according to the invention with a cooling chamber wall and a turbine wheel hub rear wall with a surface-enlarging structure.
Weg zur Ausführung der Erfindung Fig. 1 zeigt schematisch die erfindungsgemässe Turbine. In einem mehrteiligen1 schematically shows the turbine according to the invention. In a multi-part
Turbinengehäuse 21 , 22 ist ein drehbares Turbinenrad angeordnet. Das Turbinenrad umfasst eine Nabe 11 und mehrere auf der Vorderseite der Nabe angeordnete ; Laufschaufeln 15 und ist über eine Welle 30 mit dem nicht dargestellten Verdichterrad verbunden. Das Turbinengehäuse mit den gaseintrittsseitigen Gehäuseteil 22 zur Linken des Turbinenrades und dem gasaustrittsseitigen Gehäuseteil 21 bildet zusammen mit der Nabe des Turbinenrades einen Strömungskanal 40, in welchem im Betrieb des Abgasturboladers heisse Abgase durchströmen (siehe grosser Pfeil). Die Turbine kann als reine Radialturbine ausgebildet sein, mit radialer Anströmung und axialem Austritt der Abgase, oder, wie in Fig. 2 dargestellt, als sogenannte Mixedflow Turbine mit Anströmung mit radialer und axialer Komponente und axialem Austritt.Turbine housing 21, 22, a rotatable turbine wheel is arranged. The turbine wheel comprises a hub 11 and several arranged on the front of the hub; Blades 15 and is connected via a shaft 30 to the compressor wheel, not shown. The turbine housing with the gas inlet side housing part 22 to the left of the turbine wheel and the gas outlet side housing part 21 forms, together with the hub of the turbine wheel, a flow channel 40, in which hot exhaust gases flow through during operation of the exhaust gas turbocharger (see large arrow). The turbine can be designed as a pure radial turbine, with a radial inflow and axial exit of the exhaust gases, or, as shown in FIG. 2, as a so-called mixed flow turbine with an inflow with radial and axial components and an axial exit.
Im Rücken der Nabe des Turbinenrades, im gaseintrittsseitigen Gehäuse 22 ist ein Kühlkanal 50 eingelassen. Der Kühlkanal erstreckt sich radial entlang der Nabe des Turbinenrades um eine optimale Kühlung desselben zu ermöglichen. Die Nabe des Turbinenrades ist an ihrer Rückseite 12 radial bis zu den Gaseintrittskanten 16 der Laufschaufeln hochgezogen, wodurch die Wärme direkt dem Bereich mit der grössten thermischen Belastung entnommen werden kann. Die Schaufeln werden über die Nabe gekühlt und können dank der geringeren thermischen Belastung weniger massiv ausgebildet sein. Ohne Kühlung müssten die Schaufeln im Bereich der Nabenbefestigung wesentlich stärker ausgebildet sein, was ein Lösen der Schaufeln von der Nabe im Berstfall verunmöglicht. In Umfangsrichtung zwischen den Schaufeln kann die Nabe um Gewicht zu sparen und das Massenträgheitsmoment zu reduzieren mit einer radial nach innen gerichteten Bogenkante versehen, und so radial etwas weniger weit nach aussen geführt sein.A cooling duct 50 is embedded in the back of the hub of the turbine wheel, in the housing 22 on the gas inlet side. The cooling channel extends radially along the hub of the turbine wheel in order to enable it to be optimally cooled. The hub of the turbine wheel is drawn up radially on its rear side 12 up to the gas inlet edges 16 of the rotor blades, as a result of which the heat can be taken directly from the area with the greatest thermal load. The blades are cooled via the hub and can be made less solid thanks to the lower thermal load. Without cooling, the blades would have to be much stronger in the area of the hub attachment, which would make it impossible to detach the blades from the hub in the event of a burst. In the circumferential direction between the blades, the hub can be used to save weight and reduce the moment of inertia with a radial after provided on the inside directed arch edge, and so be guided a little less radially outwards.
Zwischen dem Kühlkanal 50 und der Rückseite 12 der Nabe des Turbinenrades ist eine wärmeübertragende Gehäusewand 23 angeordnet. Im Betrieb der Turbine wird der Nabe des Turbinenrades die Wärme erfindungsgemäss durch die Rückwand 12 der Nabe des Turbinenrades und durch die wärmeübertragende Gehäusewand 23 entzogen und über ein Kühlmedium, beispielsweise Kühlwasser oder Öl, zu einem Wärmetauscher abgeführt.A heat-transmitting housing wall 23 is arranged between the cooling duct 50 and the rear 12 of the hub of the turbine wheel. During operation of the turbine, the heat from the hub of the turbine wheel is extracted according to the invention through the rear wall 12 of the hub of the turbine wheel and through the heat-transferring housing wall 23 and dissipated to a heat exchanger via a cooling medium, for example cooling water or oil.
Zur Verbesserung der Wärmeübertragung von der Nabe des Turbinenrades auf die Kühlflüssigkeit können verschiedene Massnahmen getroffen werden. Einerseits kann die wärmeübertragende Gehäusewand ein Material enthalten, welches eine verbesserte Wärmeleitfähigkeit aufweist. Hierfür kann in die entsprechende Gehäusewand mit einem nachträglich aufgebrachten Material behandelt werden oder als eigenständiges Gehäuseteil vollständig aus einem anderen Material gefertigt und form- oder kraftschlüssig mit dem restlichen Turbinengehäuse verbunden sein.Various measures can be taken to improve the heat transfer from the hub of the turbine wheel to the coolant. On the one hand, the heat-transmitting housing wall can contain a material that has an improved thermal conductivity. For this purpose, it can be treated with a subsequently applied material in the corresponding housing wall or made entirely of another material as an independent housing part and connected to the rest of the turbine housing in a positive or non-positive manner.
Eine weitere Massnahme ist in Fig. 2 dargestellt. Um den Wärmetransport im Innern des Kühlkanals zu verbessern, ist die entsprechende Innenseite der wärmeübertrageriden Gehäusewand 24 mit einer oberflächenvergrössemden Struktur versehen. In der .. dargestellten Version sind mehrere Finnen vorgesehen, welche von dem Kühlmedium umspült werden. Weitere oberflächenvergrössernde Strukturen währen ebenfalls möglich, beispielsweise poröses, vom Kühlmedium durchflossenes Material, oder mehrere kleine Kühlkanäle in der Gehäusewand.Another measure is shown in FIG. 2. In order to improve the heat transport in the interior of the cooling channel, the corresponding inside of the heat transferring housing wall 24 is provided with a surface-enlarging structure. In the version shown .. several fins are provided, which are washed by the cooling medium. Other surface-enlarging structures would also be possible, for example porous material through which the cooling medium flows, or several small cooling channels in the housing wall.
Um Wärmeabfluss aus der Nabe des Turbinenrades zu verbessern kann gemäss Fig. 3 auch die Oberfläche Rückwand 13 der Nabe des Turbinenrades sowie die gegenüberliegende wärmeübertragende Gehäusewand 25 mit einer oberflächenvergrösserten Struktur versehen sein. Über die vergrösserte Oberfläche lässt sich mehr Wärme transportieren, wodurch der gesamte, mit den kleinen Pfeilen angedeutete Wärmefluss verbessert wird. Bezugszeichenliste 11 Nabe des TurbinenradesIn order to improve heat flow from the hub of the turbine wheel, the surface rear wall 13 of the hub of the turbine wheel and the opposite heat-transmitting housing wall 25 can also be provided with a surface-enlarged structure according to FIG. 3. More heat can be transported via the enlarged surface, which improves the overall heat flow, indicated by the small arrows. Reference numeral list 11 hub of the turbine wheel
12, 13 Rückseite der Nabe12, 13 rear of the hub
15 Laufschaufeln des Turbinenrades15 blades of the turbine wheel
16 Gaseintrittskante der Laufschaufeln16 gas inlet edge of the moving blades
21 Turbinengehäuse, gasaustrittsseitig21 turbine housing, gas outlet side
22 Turbinengehäuse, gaseintrittsseitig 23, 24, 25 wärmeübertragende Gehäusewand 30 Welle22 turbine housing, gas inlet side 23, 24, 25 heat-transmitting housing wall 30 shaft
40 Strömungskanal40 flow channel
50 Kühlkanal50 cooling channel
51 Kühlkanalgehäuseeinschub 51 Cooling channel housing insert

Claims

PATE NTA N S P R Ü C H E PATE NTA NSPRÜ CHE
1. Abgasturbine, umfassend ein Turbinengehäuse (21 , 22) und ein im Turbinengehäuse angeordnetes Turbinenrad, wobei das Turbinenrad auf einer Welle (30) drehbar gelagert ist, das Turbinenrad eine Nabe (11) aufweist, welche zusammen mit dem Turbinengehäuse einen Strömungskanal (40) begrenzt, in dessen Bereich auf einer Vorderseite der Nabe Laufschaufeln (15) angeordnet sind, und im Turbinengehäuse ein Kühlkanal (50) mit einem Kühlmedium vorgesehen ist, dadurch gekennzeichnet, dass der Kühlkanal zur Kühlung der Nabe des Turbinenrades im Turbinengehäuse gegenüber einer dem Strömungskanal abgewandten Rückseite (12, 13) der Nabe des Turbinenrades angeordnet ist.Exhaust turbine, comprising a turbine housing (21, 22) and a turbine wheel arranged in the turbine housing, the turbine wheel being rotatably mounted on a shaft (30), the turbine wheel having a hub (11) which together with the turbine housing has a flow channel (40 ), in whose area rotor blades (15) are arranged on a front side of the hub, and a cooling duct (50) with a cooling medium is provided in the turbine housing, characterized in that the cooling duct for cooling the hub of the turbine wheel in the turbine housing relative to one of the flow duct facing back (12, 13) of the hub of the turbine wheel is arranged.
2. Abgasturbine nach Anspruch 1 , dadurch gekennzeichnet, dass der Kühlkanal zumindest teilweise durch eine wärmeübertragende Gehäusewand (23, 24, 25) begrenzt ist, und dass die wärmeübertragende Gehäusewand zwischen der Rückseite der Nabe des Turbinenrades (12, 13) und dem Kühlkanal (50) angeordnet ist..2. Exhaust gas turbine according to claim 1, characterized in that the cooling duct is at least partially delimited by a heat-transmitting housing wall (23, 24, 25), and that the heat-transmitting housing wall between the rear of the hub of the turbine wheel (12, 13) and the cooling duct ( 50) is arranged ..
3. Abgasturbine nach Anspruch 2, dadurch gekennzeichnet, dass die wärmeübertragende Gehäusewand (23, 24, 25) ein Material enthält, welches gegenüber dem Material des restlichen Turbinengehäuses (21 , 22) eine grössere Wärmeleitfähigkeit aufweist. 3. Exhaust gas turbine according to claim 2, characterized in that the heat-transmitting housing wall (23, 24, 25) contains a material which has a greater thermal conductivity than the material of the remaining turbine housing (21, 22).
4. Abgasturbine nach einem der Ansprüche 2 oder 3, dadurch gekennzeichnet, dass der Kühlkanal von einem ringförmigen Gehäuseeinschub (51) umgeben ist, welcher schlüssig mit dem Turbinengehäuse (22) verbunden ist.4. Exhaust gas turbine according to one of claims 2 or 3, characterized in that the cooling channel is surrounded by an annular housing insert (51) which is positively connected to the turbine housing (22).
5. Abgasturbine nach einem der Ansprüche 2 oder 3, dadurch gekennzeichnet, dass die wärmeübertragende Gehäusewand (24, 25) und/ oder die Rückseite der Nabe des Turbinenrades (13) zum dazwischenliegenden Spalt hin und/ oder die wärmeübertragende Gehäusewand (24, 25) zur Innenseite des Kühlkanals (50) hin eine oberflächenvergrössernde Struktur aufweisen.5. Exhaust gas turbine according to one of claims 2 or 3, characterized in that the heat-transmitting housing wall (24, 25) and / or the rear of the hub of the turbine wheel (13) towards the gap therebetween and / or the heat-transmitting housing wall (24, 25) have a surface-enlarging structure towards the inside of the cooling channel (50).
6. Abgasturbine nach Anspruch 1 , dadurch gekennzeichnet, dass die Laufschaufeln Gaseintrittskanten (16) aufweisen, welche im Strömungskanal (40) im wesentlichen senkrecht zur Strömungsrichtung verlaufen, und dass sich die Rückseite der Nabe des Turbinenrades (12, 13) radial bis zu den Gaseintrittskanten der Laufschaufeln erstreckt.6. Exhaust gas turbine according to claim 1, characterized in that the blades have gas inlet edges (16) which run in the flow channel (40) substantially perpendicular to the direction of flow, and that the back of the hub of the Turbine wheel (12, 13) extends radially up to the gas inlet edges of the rotor blades.
7. Abgasturbolader, umfassend einen Verdichter und eine den Verdichter antreibende Turbine gemäss einem der Ansprüche 1 bis 6. 7. Exhaust gas turbocharger, comprising a compressor and a turbine driving the compressor according to one of claims 1 to 6.
PCT/CH2004/000341 2004-06-04 2004-06-04 Turbine hub cooling system for exhaust-gas turbines WO2005119030A1 (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011116658A1 (en) * 2011-10-21 2013-04-25 Daimler Ag Supercharger for internal combustion engine of vehicle, has heat exchanger arranged in exhaust gas housing and formed as helically rotating lubricant channel, where lubricant flow through heat exchanger
WO2014198453A1 (en) * 2013-06-13 2014-12-18 Continental Automotive Gmbh Turbocharger with a radial/axial turbine wheel
US11002154B2 (en) 2017-03-30 2021-05-11 Vitesco Technologies GmbH Turbocharger for an internal combustion engine, and turbine housing

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB645258A (en) * 1946-05-10 1950-10-25 Alfred Buechi Improvements in or relating to turbines
US4107927A (en) * 1976-11-29 1978-08-22 Caterpillar Tractor Co. Ebullient cooled turbocharger bearing housing
DE3322436A1 (en) * 1983-06-22 1985-01-03 Volkswagenwerk Ag, 3180 Wolfsburg Exhaust turbocharger with partition wall, having a disc-shaped air gap, between charge-air compressor and exhaust turbine
US6739845B2 (en) * 2002-05-30 2004-05-25 William E. Woollenweber Compact turbocharger

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB645258A (en) * 1946-05-10 1950-10-25 Alfred Buechi Improvements in or relating to turbines
US4107927A (en) * 1976-11-29 1978-08-22 Caterpillar Tractor Co. Ebullient cooled turbocharger bearing housing
DE3322436A1 (en) * 1983-06-22 1985-01-03 Volkswagenwerk Ag, 3180 Wolfsburg Exhaust turbocharger with partition wall, having a disc-shaped air gap, between charge-air compressor and exhaust turbine
US6739845B2 (en) * 2002-05-30 2004-05-25 William E. Woollenweber Compact turbocharger

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011116658A1 (en) * 2011-10-21 2013-04-25 Daimler Ag Supercharger for internal combustion engine of vehicle, has heat exchanger arranged in exhaust gas housing and formed as helically rotating lubricant channel, where lubricant flow through heat exchanger
WO2014198453A1 (en) * 2013-06-13 2014-12-18 Continental Automotive Gmbh Turbocharger with a radial/axial turbine wheel
KR101823744B1 (en) * 2013-06-13 2018-01-30 콘티넨탈 오토모티브 게엠베하 Turbocharger with a radial/axial turbine wheel
US10190415B2 (en) 2013-06-13 2019-01-29 Continental Automotive Gmbh Turbocharger with a radial-axial turbine wheel
US11002154B2 (en) 2017-03-30 2021-05-11 Vitesco Technologies GmbH Turbocharger for an internal combustion engine, and turbine housing

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