EP2366870B1 - Turbocharger rotor - Google Patents

Turbocharger rotor Download PDF

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Publication number
EP2366870B1
EP2366870B1 EP11157850.6A EP11157850A EP2366870B1 EP 2366870 B1 EP2366870 B1 EP 2366870B1 EP 11157850 A EP11157850 A EP 11157850A EP 2366870 B1 EP2366870 B1 EP 2366870B1
Authority
EP
European Patent Office
Prior art keywords
shaft
turbine wheel
intermediate piece
rotor
turbine
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.)
Not-in-force
Application number
EP11157850.6A
Other languages
German (de)
French (fr)
Other versions
EP2366870A2 (en
EP2366870A3 (en
Inventor
Klaus Czerwinski
Martin Schlegl
Thomas Berger
Oliver Gamm
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BMTS Technology GmbH and Co KG
Original Assignee
Bosch Mahle Turbo Systems GmbH and Co KG
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 Bosch Mahle Turbo Systems GmbH and Co KG filed Critical Bosch Mahle Turbo Systems GmbH and Co KG
Publication of EP2366870A2 publication Critical patent/EP2366870A2/en
Publication of EP2366870A3 publication Critical patent/EP2366870A3/en
Application granted granted Critical
Publication of EP2366870B1 publication Critical patent/EP2366870B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/063—Welded 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
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • F01D5/284—Selection of ceramic materials
    • 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
    • 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
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics

Definitions

  • the present invention relates to a rotor for a charging device, in particular for an exhaust gas turbocharger, having a shaft carrying a turbine wheel and a compressor wheel according to the preamble of claim 1.
  • the invention also relates to a charging device equipped with such a rotor.
  • the invention additionally relates to a rotor for a charging device, according to the preamble of claims 8 and 10.
  • rotors are, for example, from the WO 2006/105891 A1 as well as from the US 4,557,704 known.
  • turbine / compressor wheels with an associated shaft are usually connected via thermal joining methods, for example electron beam or friction welding or soldering.
  • the parts to be joined are solid and the parts are joined in a separate production step from the actual parts production.
  • a local, often abrupt change in the material / structural properties and, consequently, a component weakening occur.
  • fusion joining method beam welding / soldering
  • the present invention therefore deals with the problem of providing a rotor of the generic type, an improved or at least one alternative embodiment, which does not have the disadvantages mentioned in the prior art in particular.
  • the present invention is based on the general idea to provide at least one porous, metallic or ceramic intermediate piece for connection, in particular, of a turbine wheel to a shaft of a rotor between the shaft and the turbine wheel, which is connected to the turbine wheel and / or the shaft via an infiltration process.
  • the said turbine wheel is Of course, by way of example also for a compressor wheel which can be connected in a similar manner to the shaft.
  • the porous intermediate piece can be sintered beforehand either by infiltration, for example during a casting process of the turbine wheel or by a casting process to the shaft or in a sintering process to the shaft or the turbine wheel and then connected to the second component by infiltration.
  • the invention offers the following advantages: It is possible to join a shaft and a turbine wheel which have completely different physical properties, such as a coefficient of thermal expansion, whereby mechanically unstable phases can form in the interface, especially in the case of conventional material joining.
  • the intermediate piece usually has a lower density than the turbine wheel or as the shaft, so that a center of gravity of the rotor is advantageously displaced in the direction of the compressor.
  • a heat wear resistance in the range of radial shaft seals can be increased due to a suitable material engineering design. It is particularly advantageous, however, that materials which have hitherto not been combinable can now be joined together reliably, that is to say they can be fastened to one another, wherein in the joining region no abrupt change in the material microstructural properties is to be feared, which could lead to undesired component weakening in this region.
  • the intermediate piece is formed as a metallic intermediate piece and materially connected to the shaft or the turbine wheel. This would be the optional option open, one of the two infiltration processes, that is to replace either the connection of the intermediate piece with the shaft or with the turbine wheel by a conventional cohesive connection.
  • a cohesive connection be selected on one of the two components.
  • the turbine wheel 2 can of course also be analogous to a compressor wheel not designated in detail.
  • at least between this and the shaft 3 at least one porous, metallic or ceramic intermediate piece 4 is provided for connecting the turbine wheel 2 to the shaft 3, which is connected to the turbine wheel 2 and / or to the shaft 3 via an infiltration process.
  • the intermediate piece 4 according to the invention can have an annular shape, as shown in FIGS Fig. 1 a and 1 b is shown, or a disc-like shape, as for example in Fig. 1c is drawn.
  • the intermediate piece 4 can be connected, for example, during the casting process of the turbine wheel 2 in / on this by means of infiltration and later via a casting process to the shaft 3.
  • the intermediate piece 4 sintered to the turbine wheel 2 or to the shaft 3 is.
  • the intermediate piece 4 is connected to the turbine wheel 2 by means of a sintering process, while the connection to the shaft 3 is produced in an adjoining infiltration process.
  • the intermediate piece 4 is formed as a metallic intermediate piece 4 and is first materially connected in a first connecting step with the shaft 3 or with the turbine wheel 2.
  • a Such material connection can be done, for example, by welding or soldering.
  • the intermediate piece 4 with the second component that is, for example. Connected to the turbine wheel 2 or the shaft 3 by means of infiltration process.
  • the intermediate piece 4 integrated in a back of the turbine wheel 2, for example, is embedded.
  • the rotor 1 produced according to the invention it is also possible, in particular, to reliably connect a turbine wheel 2 and a shaft 3 with completely different physical properties, for example thermal expansion coefficients. Due to the fact that the intermediate piece 4 usually has a lower density than the turbine wheel 2 or the shaft 3, moreover, a center of gravity of the rotor 1 is advantageously displaced in the direction of the compressor. Also, in the rotor 1 according to the invention, a material engineering embodiment of an optimal heat wear resistance of the rotor 1 in the region of radial shaft sealing rings can take place.
  • connection of the shaft 3 to the composite of turbine wheel 2 and spacer 4 can be represented in the following manner: casting (infiltrating a shaft material in a suitable device) or by local melting of the shaft material blank under axial pressure at the Stirnseitefugestelle.
  • the illustrated joining process can also be carried out in reverse order, so that first of all a sprue or an infiltration of the intermediate piece 4 takes place on the shaft 3 and then this compound formed from intermediate piece 4 and shaft 3 used as an insert in the casting process of the turbine wheel 2 and from Material of the turbine wheel 2 is infiltrated.
  • Fig. 1 shown embodiment and not belonging to the subject invention, can be arranged to connect the turbine wheel 2 to the shaft 3 on the shaft 3 radially outwardly projecting webs 6 and / or on a receiving opening 5 of the turbine wheel 2 radially inwardly projecting webs 6 'at a sliding of the turbine wheel 2 on the shaft 3 are plastically deformed, as for example.
  • FIG. 2 In the right sectional view in Fig. 2 is shown. The two sectional views are aligned with respect to a viewing plane orthogonal to the sectional image of the rotor 1.
  • the webs 6 ' are formed as longitudinal webs, wherein, of course, circumferential webs are conceivable.
  • the webs 6 'in this case have a small projection ü, so that an outer diameter of the shaft 3 is greater than an inner diameter of the receiving opening 5.
  • caulking of the turbine wheel 2 with the shaft 3 leads to a plastic deformation of the webs 6,6', whereby a positive and very stable connection can be achieved.
  • the reference I a not yet caulked area, while denoted by the reference numeral II already caulked area.
  • Fig. 2 are the webs 6 'arranged as radially inwardly projecting webs 6' on the turbine wheel 2, wherein according to the Fig. 3 the webs 6 may alternatively or additionally also be provided on the shaft 3 as radially outwardly projecting webs 6. Also in Fig. 3 is denoted by the reference numeral II already caulked and the reference numeral I not yet caulked area.
  • a further alternative not belonging to the invention embodiment for connecting a turbine wheel 2 is shown with a shaft 3, wherein the shaft 3 in this case has a conically tapering portion 7 with a arranged at the free end of the shaft 3 external thread 8.
  • a conical receiving opening 9 designed to be complementary to the conical region 7 is provided, with an adjoining internal thread 10, whereby an exact radial alignment of the turbine wheel 2 can be achieved by the conical design of the conical region 7 or the conical receiving opening 9
  • the term turbine wheel 2 is of course analogous to the connection of the invention to a compressor wheel.
  • the external thread 8 is located outside of the turbine wheel 2, in which case then a nut is screwed onto the external thread 8, which is covered to improve the aerodynamic properties with a corresponding, not shown cap.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)

Description

Die vorliegende Erfindung betrifft einen Rotor für eine Ladeeinrichtung, insbesondere für einen Abgasturbolader, mit einer ein Turbinenrad und ein Verdichterrad tragenden Welle gemäß dem Oberbegriff des Anspruchs 1. Die Erfindung betrifft außerdem eine mit einem derartigen Rotor ausgestattete Ladeeinrichtung. Die Erfindung betrifft zusätzlich einen Rotor für eine Ladeeinrichtung, gemäß dem Oberbegriff des Anspruchs 8 und10.The present invention relates to a rotor for a charging device, in particular for an exhaust gas turbocharger, having a shaft carrying a turbine wheel and a compressor wheel according to the preamble of claim 1. The invention also relates to a charging device equipped with such a rotor. The invention additionally relates to a rotor for a charging device, according to the preamble of claims 8 and 10.

Aus der DE 10 2004 025 049 A1 ist ein gattungsgemäßer Rotor bekannt, wobei die Welle zwischen einem Turbinenrad und einer Lagerung wenigstens eine Wärmeisolierung aufweist, deren Wärmedurchlässigkeit geringer ist als die der an die Wärmeisolierung angrenzenden Bereiche der Welle und die den Wärmedurchgang durch die Welle behindert. Hierdurch soll insbesondere ein verbessertes Wärmemanagement erreicht werden.From the DE 10 2004 025 049 A1 a generic rotor is known, wherein the shaft between a turbine wheel and a bearing has at least one heat insulation whose heat permeability is lower than that of the heat insulation adjacent areas of the shaft and which hinders the heat transfer through the shaft. As a result, in particular an improved thermal management is to be achieved.

Aus der EP 1 002 935 A1 ist ein weiterer Rotor bekannt, bei welchem ein Turbinenrad über ein Zwischenstück aus einer Nickel- oder Kobald-Basislegierung besteht. Um dabei einen unerwünschten Wärmefluss vom Turbinenrad zu einem den Stahlkörper der Lagerwelle führenden, temperaturempfindlichen Lager reduzieren zu können, ist das Zwischenstück aus mindestens zwei starr miteinander verbundenen Zylinderabschnitten aufgebaut, von denen einer aus der Nickel- oder Kobald-Basislegierung und ein anderer von einem Stahl gebildet ist mit einer gegenüber dem Werkstoff des Stahlkörpers geringeren Wärmeleitfähigkeit.From the EP 1 002 935 A1 Another rotor is known in which a turbine wheel via an intermediate piece of a nickel or cobalt-based alloy. In order to be able to reduce unwanted heat flow from the turbine to a steel body of the bearing shaft leading, temperature-sensitive bearings, the intermediate piece of at least two rigidly interconnected cylinder sections is constructed, one of the nickel or cobalt base alloy and another of a steel is formed with a relation to the material of the steel body lower thermal conductivity.

Weitere Rotoren sind bspw. aus der WO 2006/105891 A1 sowie aus der US 4,557,704 bekannt.Other rotors are, for example, from the WO 2006/105891 A1 as well as from the US 4,557,704 known.

Schließlich ist aus der DE 10 2007 028 346 A1 ein Rotor bekannt, bei welchem ein Turbinenrad mit einer Welle über ein Gewinde verschraubt ist.Finally, out of the DE 10 2007 028 346 A1 a rotor is known in which a turbine wheel is screwed to a shaft via a thread.

Generell werden Turbinen-/Verdichterräder mit einer zugehörigen Welle üblicherweise über thermische Fügeverfahren, bspw. einem Elektronenstrahl-oder Reibschweißen bzw. einem Löten, verbunden. Dabei sind die zu fügenden Teile massiv und die Teile werden in einem, von der eigentlichen Teileherstellung separaten Fertigungsschritt gefügt. An der Fügestelle des Turbinen-/Verdichterrads mit der Welle treten dabei jedoch eine lokale, oftmals sprunghafte Änderung der Werkstoff-/Gefügeeigenschaften und einhergehend damit eine Bauteilschwächung auf. Darüber hinaus lassen sich nicht alle in Frage kommenden Werkstoffe für ein Turbinen-/Verdichterrad, insbesondere nicht mit intermetallischen Phasen, durch Schmelzfügeverfahren (Strahlschweißen/Löten) miteinander verbinden.In general, turbine / compressor wheels with an associated shaft are usually connected via thermal joining methods, for example electron beam or friction welding or soldering. The parts to be joined are solid and the parts are joined in a separate production step from the actual parts production. At the joint of the turbine / compressor wheel with the shaft, however, a local, often abrupt change in the material / structural properties and, consequently, a component weakening occur. In addition, not all candidate materials for a turbine / compressor wheel, in particular not with intermetallic phases, by fusion joining method (beam welding / soldering) connect to each other.

Die vorliegende Erfindung beschäftigt sich daher mit dem Problem, für einen Rotor der gattungsgemäßen Art, eine verbesserte oder zumindest eine alternative Ausführungsform anzugeben, die insbesondere die im Stand der Technik genannten Nachteile nicht aufweist.The present invention therefore deals with the problem of providing a rotor of the generic type, an improved or at least one alternative embodiment, which does not have the disadvantages mentioned in the prior art in particular.

Dieses Problem wird erfindungsgemäß durch den Gegenständs der unabhängigen Ansprüchs gelöst. Vorteilhafte Ausführungsformen sind Gegenstand der abhängigen Ansprüche.This problem is solved according to the invention by the subject matter of the independent claims. Advantageous embodiments are the subject of the dependent claims.

Die vorliegende Erfindung beruht auf dem allgemeinen Gedanken, zur Anbindung insbesondere eines Turbinenrads an eine Welle eines Rotors zwischen der Welle und dem Turbinenrad wenigstens ein poröses, metallisches oder keramisches Zwischenstück vorzusehen, das über einen Infiltrationsprozess mit dem Turbinenrad und/oder der Welle verbunden ist. Das genannte Turbinenrad steht dabei selbstverständlich exemplarisch auch für ein in ähnlicher Weise mit der Welle verbindbares Verdichterrad. Das poröse Zwischenstück kann entweder über Infiltration, bspw. während eines Abgussprozesses des Turbinenrads oder durch einen Angussprozess an die Welle oder aber in einem Sinterprozess an die Welle bzw. das Turbinenrad vorab angesintert und anschließend an die jeweils zweite Komponente durch Infiltration angebunden werden. Denkbar ist insbesondere im Falle eines metallischen Zwischenstücks auch ein Anbinden des Zwischenstücks an das Turbinenrad oder an die Welle durch ein stoffliches Fügen, bspw. ein Schweißen oder ein Löten, wobei anschließend durch Infiltration eine Anbindung an die zweite Komponente vorgenommen wird. Generell bietet dabei die Erfindung folgende Vorteile: Es ist ein Fügen einer Welle und eines Turbinenrads möglich, die völlig unterschiedliche physikalische Eigenschaften, wie bspw. einen thermischen Ausdehnungskoeffizienten, aufweisen, wobei sich insbesondere bei konventioneller stofflicher Fügung mechanisch nicht stabile Phasen im Interface ausbilden können. Das Zwischenstück weist dabei üblicherweise eine geringere Dichte als das Turbinenrad bzw. als die Welle auf, so dass ein Schwerpunkt des Rotors vorteilhaft in Richtung des Verdichters verlagert wird. Auch lässt sich eine Warmverschleißbeständigkeit im Bereich von Radialwellendichtringen aufgrund einer geeigneten werkstofftechnischen Ausgestaltung erhöhen. Von besonderem Vorteil ist jedoch, dass auch bisher nicht miteinander kombinierbare Werkstoffe nun prozesssicher miteinander gefügt, dass heißt aneinander befestigt werden können, wobei im Fügebereich keine sprunghafte Änderung der Werkstoff-Gefügeeigenschaften zu befürchten sind, die zu einer unerwünschten Bauteilschwächung in diesem Bereich führen könnten.The present invention is based on the general idea to provide at least one porous, metallic or ceramic intermediate piece for connection, in particular, of a turbine wheel to a shaft of a rotor between the shaft and the turbine wheel, which is connected to the turbine wheel and / or the shaft via an infiltration process. The said turbine wheel is Of course, by way of example also for a compressor wheel which can be connected in a similar manner to the shaft. The porous intermediate piece can be sintered beforehand either by infiltration, for example during a casting process of the turbine wheel or by a casting process to the shaft or in a sintering process to the shaft or the turbine wheel and then connected to the second component by infiltration. It is conceivable in particular in the case of a metallic intermediate piece and a tethering of the intermediate piece to the turbine wheel or to the shaft by a material joining, for example. Welding or soldering, wherein then a connection to the second component is made by infiltration. In general, the invention offers the following advantages: It is possible to join a shaft and a turbine wheel which have completely different physical properties, such as a coefficient of thermal expansion, whereby mechanically unstable phases can form in the interface, especially in the case of conventional material joining. The intermediate piece usually has a lower density than the turbine wheel or as the shaft, so that a center of gravity of the rotor is advantageously displaced in the direction of the compressor. Also, a heat wear resistance in the range of radial shaft seals can be increased due to a suitable material engineering design. It is particularly advantageous, however, that materials which have hitherto not been combinable can now be joined together reliably, that is to say they can be fastened to one another, wherein in the joining region no abrupt change in the material microstructural properties is to be feared, which could lead to undesired component weakening in this region.

Bei einer vorteilhaften Weiterbildung der erfindungsgemäßen Lösung, ist das Zwischenstück als metallisches Zwischenstück ausgebildet und stofflich mit der Welle oder dem Turbinenrad verbunden. Dies würde die optionale Möglichkeit eröffnen, einen der beiden Infiltrationsprozesse, das heißt entweder die Verbindung des Zwischenstücks mit der Welle oder mit dem Turbinenrad durch eine herkömmliche stoffschlüssige Verbindung zu ersetzen. Selbstverständlich kann alternativ zur stoffschlüssigen Verbindung auch ein Ansintern an eines der beiden Bauteile gewählt werden.In an advantageous development of the solution according to the invention, the intermediate piece is formed as a metallic intermediate piece and materially connected to the shaft or the turbine wheel. This would be the optional option open, one of the two infiltration processes, that is to replace either the connection of the intermediate piece with the shaft or with the turbine wheel by a conventional cohesive connection. Of course, as an alternative to the cohesive connection and a Ansintern be selected on one of the two components.

Weitere wichtige Merkmale und Vorteile der Erfindung ergeben sich aus den Unteransprüchen, aus den Zeichnungen und aus der zugehörigen Figurenbeschreibung anhand der Zeichnungen.Other important features and advantages of the invention will become apparent from the dependent claims, from the drawings and from the associated figure description with reference to the drawings.

Es versteht sich, dass die vorstehend genannten und die nachstehend noch zu erläuternden Merkmale nicht nur in der jeweils angegebenen Kombination, sondern auch in anderen Kombinationen oder in Alleinstellung verwendbar sind, ohne den Rahmen der vorliegenden Erfindung zu verlassen.It is understood that the features mentioned above and those yet to be explained below can be used not only in the particular combination given, but also in other combinations or in isolation, without departing from the scope of the present invention.

Bevorzugte Ausführungsbeispiele der Erfindung sind in den Zeichnungen dargestellt und werden in der nachfolgenden Beschreibung näher erläutert, wobei sich gleiche Bezugszeichen auf gleiche oder ähnliche oder funktional gleiche Bauteile beziehen.Preferred embodiments of the invention are illustrated in the drawings and will be described in more detail in the following description, wherein like reference numerals refer to the same or similar or functionally identical components.

Es zeigen, jeweils schematisch,

  • Fig. 1 einen erfindungsgemäßen Rotor mit einem zwischen einer Welle und einem Turbinen-/Verdichterrad angeordneten Zwischenstück,
  • Fig. 2 ein mit einer Welle verstemmtes Turbinenrad,
  • Fig. 3 eine Darstellung wie in Fig. 2, jedoch bei einer anderen Ausführungsform,
  • Fig. 4 ein Rotor mit einer konischen Welle zur verbesserten Radialausrichtung eines Turbinen-/Verdichterrads.
Show, in each case schematically,
  • Fig. 1 a rotor according to the invention with an intermediate piece arranged between a shaft and a turbine / compressor wheel,
  • Fig. 2 a turbine wheel caulked with a shaft,
  • Fig. 3 a representation like in Fig. 2 but in another embodiment,
  • Fig. 4 a rotor with a conical shaft for improved radial alignment of a turbine / compressor wheel.

Entsprechend der Fig. 1, weist ein erfindungsgemäßer Rotor 1 für eine nicht gezeigte Ladeeinrichtung, insbesondere für einen Abgasturbolader, eine ein Turbinenrad 2 tragende Welle 3 auf. Das Turbinenrad 2 kann dabei selbstverständlich analog auch für ein nicht näher bezeichnetes Verdichterrad stehen. Erfindungsgemäß ist nun zur Anbindung des Turbinenrads 2 an die Welle 3 zumindest zwischen diesem und der Welle 3 wenigstens ein poröses, metallisches oder keramisches Zwischenstück 4 vorgesehen, das über einen Infiltrationsprozess mit dem Turbinenrad 2 und/oder mit der Welle 3 verbunden ist. Das erfindungsgemäße Zwischenstück 4 kann dabei eine ringförmige Gestalt aufweisen, wie dies gemäß den Fig. 1 a und 1 b dargestellt ist, oder aber eine scheibenartige Gestalt, wie dies bspw. in Fig. 1c gezeichnet ist. Im Vergleich zu herkömmlichen Verbindungen von Turbinenrädern mit zugehörigen Wellen kann bei dem erfindungsgemäßen Rotor 1 ein Übergang zwischen dem Turbinenrad 2 und der Welle 3 erreicht werden ohne sprunghafte Änderung von Werkstoff-/Gefügeeigenschaften und damit ohne bisher dort auftretende Schwachpunkte. Das Zwischenstück 4 kann dabei bspw. während des Abgussprozesses des Turbinenrads 2 in/an dieses mittels Infiltration angebunden werden und später über einen Angussprozess an die Welle 3. Alternativ ist auch denkbar, dass das Zwischenstück 4 an das Turbinenrad 2 oder an die Welle 3 angesintert ist. In diesem Fall ist bspw. das Zwischenstück 4 mit dem Turbinenrad 2 mittels eines Sinterprozesses verbunden, während die Verbindung zur Welle 3 in einem sich daran anschließenden Infiltrationsprozess hergestellt wird.According to the Fig. 1 , A rotor 1 according to the invention for a charging device, not shown, in particular for an exhaust gas turbocharger, a shaft 3 carrying a turbine wheel 2. The turbine wheel 2 can of course also be analogous to a compressor wheel not designated in detail. According to the invention, at least between this and the shaft 3 at least one porous, metallic or ceramic intermediate piece 4 is provided for connecting the turbine wheel 2 to the shaft 3, which is connected to the turbine wheel 2 and / or to the shaft 3 via an infiltration process. The intermediate piece 4 according to the invention can have an annular shape, as shown in FIGS Fig. 1 a and 1 b is shown, or a disc-like shape, as for example in Fig. 1c is drawn. Compared to conventional compounds of turbine wheels with associated shafts, a transition between the turbine wheel 2 and the shaft 3 can be achieved in the rotor 1 according to the invention without sudden change of material / structural properties and thus without previously occurring weak points. The intermediate piece 4 can be connected, for example, during the casting process of the turbine wheel 2 in / on this by means of infiltration and later via a casting process to the shaft 3. Alternatively, it is also conceivable that the intermediate piece 4 sintered to the turbine wheel 2 or to the shaft 3 is. In this case, for example, the intermediate piece 4 is connected to the turbine wheel 2 by means of a sintering process, while the connection to the shaft 3 is produced in an adjoining infiltration process.

Generell ist auch denkbar, dass das Zwischenstück 4 als metallisches Zwischenstück 4 ausgebildet ist und zunächst in einem ersten Verbindungsschritt stofflich mit der Welle 3 oder mit dem Turbinenrad 2 verbunden wird. Eine derartige stoffliche Verbindung kann bspw. mittels Schweißen oder Löten erfolgen. In einem sich daran anschließenden Fertigungsschritt wird das Zwischenstück 4 mit der zweiten Komponente, das heißt bspw. mit dem Turbinenrad 2 oder der Welle 3 mittels Infiltrationsprozess verbunden.In general, it is also conceivable that the intermediate piece 4 is formed as a metallic intermediate piece 4 and is first materially connected in a first connecting step with the shaft 3 or with the turbine wheel 2. A Such material connection can be done, for example, by welding or soldering. In an adjoining production step, the intermediate piece 4 with the second component, that is, for example. Connected to the turbine wheel 2 or the shaft 3 by means of infiltration process.

Betrachtet man Fig. 1b, so kann man erkennen, dass das Zwischenstück 4 in einem Rücken des Turbinenrads 2 integriert, bspw. eingebettet ist. Mit dem erfindungsgemäß hergestellten Rotor 1 ist es insbesondere auch möglich, ein Turbinenrad 2 und eine Welle 3 mit völlig unterschiedlichen physikalischen Eigenschaften, bspw. thermischen Ausdehnungskoeffizienten, prozesssicher miteinander zu verbinden. Aufgrund der Tatsache, dass das Zwischenstück 4 üblicherweise eine geringere Dichte aufweist als das Turbinenrad 2 bzw. die Welle 3 wird darüber hinaus ein Schwerpunkt des Rotors 1 vorteilhaft in Richtung des Verdichters verlagert. Auch kann im erfindungsgemäßen Rotor 1 eine werkstofftechnische Ausgestaltung einer optimalen Warmverschleißbeständigkeit des Rotors 1 im Bereich von Radialwellendichtringen erfolgen. Durch die poröse Struktur des Zwischenstücks 4 wird dieses beim Verbindungsprozess mit der Welle 3 bzw. mit dem Turbinenrad 2 von einem flüssigen Werkstoff der-/desselben infiltriert, wodurch eine besonders feste Verbindung erreicht werden kann. Die Anbindung der Welle 3 an den Verbund aus Turbinenrad 2 und Zwischenstück 4 kann dabei auf folgende Weise dargestellt werden: Angießen (Infiltrieren eines Wellenmaterials in einer geeigneten Vorrichtung) oder durch lokales Aufschmelzen des Wellenmaterial-Rohlings unter axialem Druck an der Stirnseitefügestelle. Selbstverständlich kann dabei der dargestellte Fügeprozess auch in umgekehrter Reihenfolge erfolgen, so dass zunächst ein Anguss bzw. eine Infiltration des Zwischenstücks 4 an die Welle 3 erfolgt und anschließend dieser aus Zwischenstück 4 und Welle 3 gebildete Verbund als Einlegeteil im Gießprozess des Turbinenrads 2 verwendet und vom Material des Turbinenrads 2 infiltriert wird.If you look at Fig. 1b , it can be seen that the intermediate piece 4 integrated in a back of the turbine wheel 2, for example, is embedded. With the rotor 1 produced according to the invention, it is also possible, in particular, to reliably connect a turbine wheel 2 and a shaft 3 with completely different physical properties, for example thermal expansion coefficients. Due to the fact that the intermediate piece 4 usually has a lower density than the turbine wheel 2 or the shaft 3, moreover, a center of gravity of the rotor 1 is advantageously displaced in the direction of the compressor. Also, in the rotor 1 according to the invention, a material engineering embodiment of an optimal heat wear resistance of the rotor 1 in the region of radial shaft sealing rings can take place. Due to the porous structure of the intermediate piece 4, it is infiltrated by a liquid material of the same in the connection process with the shaft 3 or with the turbine wheel 2, whereby a particularly firm connection can be achieved. The connection of the shaft 3 to the composite of turbine wheel 2 and spacer 4 can be represented in the following manner: casting (infiltrating a shaft material in a suitable device) or by local melting of the shaft material blank under axial pressure at the Stirnseitefugestelle. Of course, the illustrated joining process can also be carried out in reverse order, so that first of all a sprue or an infiltration of the intermediate piece 4 takes place on the shaft 3 and then this compound formed from intermediate piece 4 and shaft 3 used as an insert in the casting process of the turbine wheel 2 and from Material of the turbine wheel 2 is infiltrated.

Alternativ zu der gemäß der Fig. 1 gezeigten Ausführungsform und nicht zum Erfindungsgegenstand gehörend, können zur Anbindung des Turbinenrads 2 an die Welle 3 an der Welle 3 nach radial außen abstehende Stege 6 und/oder an einer Aufnahmeöffnung 5 des Turbinenrads 2 nach radial innen abstehende Stege 6' angeordnet sein, die bei einem Aufschieben des Turbinenrads 2 auf die Welle 3 plastisch deformiert werden, wie dies bspw. in der rechten Schnittdarstellung in Fig. 2 gezeigt ist. Die beiden Schnittdarstellungen sind dabei hinsichtlich einer Betrachtungsebene orthogonal zum Schnittbild des Rotors 1 ausgerichtet. In der linken Schnittdarstellung kann man erkennen, dass die Stege 6' als Längsstege ausgebildet sind, wobei selbstverständlich auch umlaufende Stege denkbar sind. Die Stege 6' weisen dabei einen geringen Überstand ü auf, so dass ein Außendurchmesser der Welle 3 größer ist als ein Innendurchmesser der Aufnahmeöffnung 5. Dabei führt ein Verstemmen des Turbinenrads 2 mit der Welle 3 zu einer plastischen Verformung der Stege 6,6', wodurch eine formschlüssige und besonders stabile Verbindung erreicht werden kann. In der oberen Schnittdarstellung in Fig. 2 ist mit dem Bezugszeichen I ein noch nicht verstemmter Bereich bezeichnet, während mit dem Bezugszeichen II der bereits verstemmte Bereich dargestellt ist.Alternatively to that according to the Fig. 1 shown embodiment and not belonging to the subject invention, can be arranged to connect the turbine wheel 2 to the shaft 3 on the shaft 3 radially outwardly projecting webs 6 and / or on a receiving opening 5 of the turbine wheel 2 radially inwardly projecting webs 6 'at a sliding of the turbine wheel 2 on the shaft 3 are plastically deformed, as for example. In the right sectional view in Fig. 2 is shown. The two sectional views are aligned with respect to a viewing plane orthogonal to the sectional image of the rotor 1. In the left sectional view, it can be seen that the webs 6 'are formed as longitudinal webs, wherein, of course, circumferential webs are conceivable. The webs 6 'in this case have a small projection ü, so that an outer diameter of the shaft 3 is greater than an inner diameter of the receiving opening 5. Here, caulking of the turbine wheel 2 with the shaft 3 leads to a plastic deformation of the webs 6,6', whereby a positive and very stable connection can be achieved. In the upper section in Fig. 2 is denoted by the reference I a not yet caulked area, while denoted by the reference numeral II already caulked area.

Gemäß der Fig. 2 sind dabei die Stege 6' als radial nach innen abstehende Stege 6' am Turbinenrad 2 angeordnet, wobei gemäß der Fig. 3 die Stege 6 alternativ oder zusätzlich auch an der Welle 3 als nach radial außen abstehende Stege 6 vorgesehen sein können. Auch in Fig. 3 ist dabei mit dem Bezugszeichen II der bereits verstemmte und mit dem Bezugszeichen I der noch nicht verstemmte Bereich bezeichnet.According to the Fig. 2 are the webs 6 'arranged as radially inwardly projecting webs 6' on the turbine wheel 2, wherein according to the Fig. 3 the webs 6 may alternatively or additionally also be provided on the shaft 3 as radially outwardly projecting webs 6. Also in Fig. 3 is denoted by the reference numeral II already caulked and the reference numeral I not yet caulked area.

Betrachtet man nochmals die Fig. 2 und 3, so ist klar, dass die Umformvorgänge der Stege 6, 6' beim Verstemmen des Turbinenrads 2 mit der Welle 3 abhängig von der Härte der beiden Materialien sind. Axial benachbart zu den Bereichen mit den Stegen 6, 6' ist zumindest einenends ein Bereich 11 vorgesehen, der keine Stege 6 aufweist und dadurch eine koaxiale Ausrichtung des Turbinen-/Verdichterrads 2 auf der Welle 3 ermöglicht. Ein großer Vorteil dieser Verbindungsart ist, dass zum Verbinden kein zusätzlicher Arbeitsgang, wie bspw. Schrauben oder Schweißen, erforderlich ist. Die Stege 6,6' können dabei nahezu beliebige Ausgestaltungen, insbesondere Riffelungen, Schraubenlinien, etc. aufweisen.Looking again at the Fig. 2 and 3 , it is clear that the forming operations of the webs 6, 6 'when caulking the turbine wheel 2 with the shaft 3 are dependent on the hardness of the two materials. Axially adjacent to the areas with the webs 6, 6 ', at least one end of a region 11 is provided, which has no webs 6 and thereby enables a coaxial alignment of the turbine / compressor wheel 2 on the shaft 3. A great advantage of this type of connection is that no additional operation, such as screws or welding, is required for the connection. The webs 6,6 'can have almost any desired configurations, in particular corrugations, helices, etc.

In Fig. 4 ist eine weitere alternative nicht zur Erfindung gehörende Ausführungsform zur Verbindung eines Turbinenrads 2 mit einer Welle 3 gezeigt, wobei die Welle 3 in diesem Fall einen sich konisch verjüngenden Bereich 7 mit einem am freien Ende der Welle 3 angeordneten Außengewinde 8 aufweist. Am Turbinenrad 2 ist dazu eine komplementär zum konischen Bereich 7 ausgebildete konische Aufnahmeöffnung 9 vorgesehen, mit einem sich daran anschließenden Innengewinde 10, wobei durch die konische Ausbildung des konischen Bereichs 7 bzw. der konischen Aufnahmeöffnung 9 eine exakte radiale Ausrichtung des Turbinenrads 2 erreicht werden kann. Auch in diesem Fall steht der Begriff Turbinenrad 2 selbstverständlich analog für die Anbindung der Erfindung auf ein Verdichterrad. Denkbar ist selbstverständlich auch, dass das Außengewinde 8 außerhalb des Turbinenrads 2 liegt, wobei in diesem Fall dann auf das Außengewinde 8 eine Mutter aufgeschraubt wird, welche zur Verbesserung der aerodynamischen Eigenschaften mit einer entsprechenden, nicht gezeichneten Kappe abgedeckt wird.In Fig. 4 a further alternative not belonging to the invention embodiment for connecting a turbine wheel 2 is shown with a shaft 3, wherein the shaft 3 in this case has a conically tapering portion 7 with a arranged at the free end of the shaft 3 external thread 8. On the turbine wheel 2, a conical receiving opening 9 designed to be complementary to the conical region 7 is provided, with an adjoining internal thread 10, whereby an exact radial alignment of the turbine wheel 2 can be achieved by the conical design of the conical region 7 or the conical receiving opening 9 , Also in this case, the term turbine wheel 2 is of course analogous to the connection of the invention to a compressor wheel. It is of course also conceivable that the external thread 8 is located outside of the turbine wheel 2, in which case then a nut is screwed onto the external thread 8, which is covered to improve the aerodynamic properties with a corresponding, not shown cap.

Claims (5)

  1. A rotor (1) for a supercharging device, in particular for an exhaust gas turbocharger, having a shaft (3) carrying a turbine wheel (2) and a compressor wheel, wherein for connecting in particular the turbine wheel (2) to the shaft (3) at least between the same and the shaft (3) at least one porous metallic or ceramic intermediate piece (4) is provided, which is connected to the turbine wheel (2) and/or the shaft (3) via an infiltration process, characterized in that the intermediate piece (4) is sintered onto the turbine wheel (2) or onto the shaft (3) and integrated in a back of the turbine wheel (2).
  2. The rotor according to Claim 1, characterized in that the intermediate piece (4) is designed as a metallic intermediate piece (4) and materially connected to the shaft (3) or the turbine wheel (2).
  3. The rotor according to Claim 2, characterized in that the intermediate piece (4) is welded or soldered to the shaft (3) or to the turbine wheel (2).
  4. The rotor according to any one of the Claims 1 to 3, characterized in that the intermediate piece (4) has an annular or a disc-like shape.
  5. A supercharging device, in particular an exhaust gas turbocharger, having a rotor (1) according to any one of the preceding claims.
EP11157850.6A 2010-03-16 2011-03-11 Turbocharger rotor Not-in-force EP2366870B1 (en)

Applications Claiming Priority (1)

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DE102010011486A DE102010011486A1 (en) 2010-03-16 2010-03-16 Rotor for a charging device

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EP2366870A2 EP2366870A2 (en) 2011-09-21
EP2366870A3 EP2366870A3 (en) 2012-11-14
EP2366870B1 true EP2366870B1 (en) 2015-02-25

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EP2366870A2 (en) 2011-09-21
DE102010011486A1 (en) 2011-09-22
US20110229325A1 (en) 2011-09-22
EP2366870A3 (en) 2012-11-14

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