EP1676980A1 - Turbocharger with variable geometry turbine and manufacturing method - Google Patents

Turbocharger with variable geometry turbine and manufacturing method Download PDF

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Publication number
EP1676980A1
EP1676980A1 EP04030888A EP04030888A EP1676980A1 EP 1676980 A1 EP1676980 A1 EP 1676980A1 EP 04030888 A EP04030888 A EP 04030888A EP 04030888 A EP04030888 A EP 04030888A EP 1676980 A1 EP1676980 A1 EP 1676980A1
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EP
European Patent Office
Prior art keywords
bearing ring
disc
support pin
blade bearing
turbocharger
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.)
Granted
Application number
EP04030888A
Other languages
German (de)
French (fr)
Other versions
EP1676980B1 (en
Inventor
Ralf Böning
Dietmar Metz
Dirk Frankenstein
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.)
BorgWarner Inc
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BorgWarner Inc
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Publication date
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Application filed by BorgWarner Inc filed Critical BorgWarner Inc
Priority to EP04030888.4A priority Critical patent/EP1676980B1/en
Priority to JP2005348934A priority patent/JP4578394B2/en
Priority to KR1020050124596A priority patent/KR101172834B1/en
Priority to CNB2005101340463A priority patent/CN100478546C/en
Priority to US11/321,300 priority patent/US7507067B2/en
Publication of EP1676980A1 publication Critical patent/EP1676980A1/en
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Publication of EP1676980B1 publication Critical patent/EP1676980B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/04—Arrangement of sensing elements responsive to load
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2260/231—Preventing heat transfer

Definitions

  • the invention relates to a turbocharger with variable turbine geometry (VTG) according to the preamble of claim 1.
  • VFG variable turbine geometry
  • the VTG cartridge of such a turbocharger consists of a nozzle with vanes and levers and turbine-side disk.
  • the attachment of the disc to a vane bearing ring of a vane bearing assembly takes place in generic turbochargers by means of screws or welding.
  • spacer sleeves are required, which can be removed in the case of a welded joint after welding again.
  • the blade bearing assembly is defined as an independently tradable object.
  • a heat choke is provided, which surrounds the recess for the support pin end to be welded.
  • this heat choke is designed as a circumferential groove around the recess for the support pin end to be welded.
  • the first end of the support pins can be screwed, riveted or otherwise fixed to the disc.
  • the support pins preferably have a very small diameter of a few millimeters, so that the resulting flow cross-section reduction and the associated Strömungsverwirbelonne remain minimal.
  • a turbocharger 15 in a compressor housing 17, a bearing housing 18 having the required bearings for the shaft 19 and a turbine 20 in a turbine housing 21.
  • the remaining parts are not necessary for the explanation of the present invention to fully explain its principles, of course provided.
  • the blade bearing arrangement 1 has a blade bearing ring 2, on which a disc 3 is arranged at a defined distance.
  • the disc 3 is preferably formed of the same material as the blade bearing ring 2 and serves, as stated, to set an exact axial gap in order to define a flow channel 4 can.
  • a support pin 5 For attachment of the disc 3 on the blade bearing ring 2 is at least one, but usually provided a plurality of support pins, of which in Fig. 2, a support pin 5 is visible.
  • the support pin 5 has a first and a second end 6 and 7, respectively. Between the ends 6 and 7, a shaft region 8 arranged in the flow channel 4 is arranged in the assembled state.
  • the second end 7 of the support pin 5 is arranged in a recess 11 of the disc 3 and connected in a conically widened region 12 of the recess 11 with the disc 3 via a weld 13.
  • the end 7 is roof-like tapered at its end face in order to achieve a perfecting of the weld 13 can.
  • a heat choke in the form of a circumferential groove 14 is provided in the particularly preferred embodiment shown in Figs. 2 and 3, which prevents the heat can penetrate directly into the massive part of the disc 3, which contributes to the prevention of distortion of the disc 3 during welding and also reduces the required input welding energy.
  • the disc 3 is provided with one recess 11 per support pin 5, wherein each of these recesses 11, the above-described heat choke in the form of the circumferential groove 14 is attached.
  • the first end 6 of the support pin 5 is screwed to the blade bearing ring 2 for fixing the disc 3 on the blade bearing ring 2.
  • spacers between the blade bearing ring 2 and disc 3 are inserted to the defined distance to be able to adjust between the blade bearing ring 2 and the disc 3.
  • the welding of the second end 7 and the removal of the spacers takes place.

Abstract

The turbocharger has a vane bearing ring assembly (1) with a vane bearing ring and a disk (3) fixed to the vane bearing ring for creating a flow channel (4). A support pin is connected with an end of the vane bearing ring which is welded with an end of the disk. The disk includes a recess per support pin for a support pin end that is to be welded with the bearing ring, where the recess is surrounded by a heat throttle. An independent claim is also included for a method for producing a vane bearing ring assembly.

Description

Die Erfindung betrifft einen Turbolader mit variabler Turbinengeometrie (VTG) gemäß dem Oberbegriff des Anspruches 1.The invention relates to a turbocharger with variable turbine geometry (VTG) according to the preamble of claim 1.

Die VTG-Kartusche eines derartigen Turboladers besteht aus einem Leitapparat mit Schaufeln und Hebeln und turbinengehäuseseitiger Scheibe. Die Befestigung der Scheibe an einem Schaufellagerring einer Schaufellageranordnung erfolgt bei gattungsgemäßen Turboladern mittels Schrauben oder Schweißen. Um für den Strömungskanal, der sich zwischen Schaufellagerring und Scheibe ausbildet und in dem sich die Schaufeln der VTG befinden, eine definierte Breite einstellen zu können, sind Distanz-Hülsen erforderlich, die im Falle einer Schweißverbindung nach dem Schweißen wieder entfernt werden können. Durch das Schweißen kann jedoch ein Verzug der Scheibe infolge starker Wärmeeinleitung entstehen. Ein Verzug der Scheibe kann durch die dadurch bedingte lokale Spaltreduktion zwischen Schaufeln und Scheibe zu einem Klemmen der Schaufeln führen.The VTG cartridge of such a turbocharger consists of a nozzle with vanes and levers and turbine-side disk. The attachment of the disc to a vane bearing ring of a vane bearing assembly takes place in generic turbochargers by means of screws or welding. In order to set a defined width for the flow channel, which forms between the blade bearing ring and disc and in which the blades of the VTG are located, spacer sleeves are required, which can be removed in the case of a welded joint after welding again. By welding, however, a distortion of the disc caused by strong heat input. A distortion of the disc can lead to a clamping of the blades due to the consequent local gap reduction between blades and disc.

Es ist daher Aufgabe der vorliegenden Erfindung, einen Turbolader der im Oberbegriff des Anspruches 1 angegebenen Art zu schaffen, bei dem es möglich ist, eine Schweißverbindung herzustellen, die möglichst verzugsfrei die Scheibe mit dem Schaufellagerring verbindet, so dass ein konstant gleichmäßiger Abstand wie bei dem Verbinden mittels Schrauben entsteht. Die Lösung dieser Aufgabe erfolgt durch die Merkmale des Anspruches 1.It is therefore an object of the present invention to provide a turbocharger specified in the preamble of claim 1 species, in which it is possible to produce a welded joint, which connects the disc as possible with the blade bearing ring without distortion, so that a constant uniform distance as in the Joining by means of screws. The solution of this object is achieved by the features of claim 1.

Die Unteransprüche 2 bis 4 haben vorteilhafte Weiterbildungen des erfindungsgemäßen Turboladers zum Inhalt.The dependent claims 2 to 4 have advantageous developments of the turbocharger invention to the content.

In den Ansprüche 6 bis 8 ist ein erfindungsgemäßes Verfahren zur Herstellung einer Schaufellageranordnung für den erfindungsgemäßen Turbolader angegeben.In the claims 6 to 8 an inventive method for producing a vane bearing assembly for the turbocharger according to the invention is given.

In Anspruch 5 ist die Schaufellageranordnung als selbständig handelbares Objekt definiert. Um beim Verschweißen ein unerwünschtes Verziehen der Scheibe vermeiden zu können, ist bei einer besonders bevorzugten Ausführungsform eine Wärmedrossel vorgesehen, die die Ausnehmung für das zu verschweißende Tragstiftende umgibt.In claim 5, the blade bearing assembly is defined as an independently tradable object. In order to avoid unwanted distortion of the disc during welding, in a particularly preferred embodiment, a heat choke is provided, which surrounds the recess for the support pin end to be welded.

In einer besonders bevorzugten Ausführungsform ist diese Wärmedrossel als eine um die Ausnehmung für das zu verschweißende Tragstiftende umlaufende Nut ausgebildet.In a particularly preferred embodiment, this heat choke is designed as a circumferential groove around the recess for the support pin end to be welded.

Durch das Vorsehen einer derartigen Wärmedrossel wird erreicht, dass der Energieeintrag in die Scheibe so gering wie möglich gehalten werden kann. Ein weiterer Vorteil dieser Wärmedrossel ist darin zu sehen, dass dadurch, dass weniger Energie in das die Schweißstelle umgebende Material der Scheibe abgeführt wird, d.h., die Energie an der Schweißstelle "gefangen" bleibt, insgesamt weniger Schweißenergie nötig ist, um das Scheibenmaterial zu schweißen.By providing such a heat choke is achieved that the energy input into the disc can be kept as low as possible. Another advantage of this heat choke is the fact that less energy is dissipated into the material surrounding the weld the disc, ie, the energy at the weld "trapped", total less welding energy is needed to weld the disc material ,

Das erste Ende der Tragstifte kann mit der Scheibe entweder verschraubt, vernietet oder auf andere Art und Weise fixiert werden.The first end of the support pins can be screwed, riveted or otherwise fixed to the disc.

Die Tragstifte haben vorzugsweise einen sehr geringen Durchmesser von einigen wenigen Millimetern, damit die dadurch bedingte Strömungsquerschnittsreduktion sowie die damit verbundenen Strömungsverwirbelungen minimal bleiben.The support pins preferably have a very small diameter of a few millimeters, so that the resulting flow cross-section reduction and the associated Strömungsverwirbelungen remain minimal.

Weitere Einzelheiten, Vorteile und Merkmale der vorliegenden Erfindung ergeben sich aus nachfolgender Beschreibung von Ausführungsbeispielen anhand der beigefügten Zeichnung. Es zeigt:

Fig. 1
eine perspektivische Darstellung eines erfindungsgemäßen Turboladers,
Fig. 2
eine Schnittdarstellung einer erfindungsgemäßen Schaufellageranordnung für den erfindungsgemäßen Turbolader, und
Fig. 3
die Einzelheit X der Fig. 2 in vergrößerter Darstellung.
Further details, advantages and features of the present invention will become apparent from the following description of embodiments with reference to the accompanying drawings. It shows:
Fig. 1
a perspective view of a turbocharger according to the invention,
Fig. 2
a sectional view of a blade bearing assembly according to the invention for the turbocharger according to the invention, and
Fig. 3
the detail X of FIG. 2 in an enlarged view.

Da für die nachfolgende Beschreibung der erfindungsgemäßen Konstruktionsprinzipien eine komplette Erläuterung aller Konstruktionsdetails eines Turboladers mit variabler Turbinengeometrie nicht erforderlich ist, sind in Fig. 1 nur die grundlegenden Bauteile eines erfindungsgemäßen Turboladers 15 bezeichnet, der wie üblich ein Verdichterrad 16 in einem Verdichtergehäuse 17, ein Lagergehäuse 18 mit den erforderlichen Lagern für die Welle 19 und ein Turbinenrad 20 in einem Turbinengehäuse 21 aufweist. Die übrigen Teile sind für die Erläuterung vorliegender Erfindung nicht erforderlich, um deren Prinzipien vollständig zu erläutern, natürlich jedoch vorgesehen.Since a complete explanation of all construction details of a turbocharger with variable turbine geometry is not required for the following description of the design principles according to the invention, only the basic components of a turbocharger 15 according to the invention are designated in Fig. 1, as usual, a compressor 16 in a compressor housing 17, a bearing housing 18 having the required bearings for the shaft 19 and a turbine 20 in a turbine housing 21. The remaining parts are not necessary for the explanation of the present invention to fully explain its principles, of course provided.

Dementsprechend ist in Fig. 2 nur eine Schaufellageranordnung 1 eines erfindungsgemäßen Turboladers dargestellt. Die Schaufellageranordnung 1 weist einen Schaufellagerring 2 auf, an dem in einem definierten Abstand eine Scheibe 3 angeordnet ist. Die Scheibe 3 ist vorzugsweise aus dem gleichen Material wie der Schaufellagerring 2 ausgebildet und dient, wie gesagt, zur Einstellung eines exakten axialen Spaltes, um einen Strömungskanal 4 definieren zu können.Accordingly, only one vane bearing assembly 1 of a turbocharger according to the invention is shown in FIG. The blade bearing arrangement 1 has a blade bearing ring 2, on which a disc 3 is arranged at a defined distance. The disc 3 is preferably formed of the same material as the blade bearing ring 2 and serves, as stated, to set an exact axial gap in order to define a flow channel 4 can.

Zur Befestigung der Scheibe 3 am Schaufellagerring 2 ist mindestens ein, jedoch in der Regel eine Mehrzahl von Tragstiften vorgesehen, von denen in Fig. 2 ein Tragstift 5 sichtbar ist. Der Tragstift 5 weist ein erstes und ein zweites Ende 6 bzw. 7 auf. Zwischen den Enden 6 und 7 ist im Montagezustand ein im Strömungskanal 4 angeordneter Schaftbereich 8 angeordnet.For attachment of the disc 3 on the blade bearing ring 2 is at least one, but usually provided a plurality of support pins, of which in Fig. 2, a support pin 5 is visible. The support pin 5 has a first and a second end 6 and 7, respectively. Between the ends 6 and 7, a shaft region 8 arranged in the flow channel 4 is arranged in the assembled state.

Wie sich aus einer Zusammenschau der Fig. 2 und 3 ergibt, weist das Ende 6 im Beispielsfalle ein Außengewinde 9 auf, das mit einem entsprechenden Innengewinde 10 des Schaufellagerrings 2 zur Fixierung dieses ersten Endes 6 am Schaufellagerring 2 zusammenwirkt.As is apparent from a synopsis of FIGS. 2 and 3, the end 6 in the exemplary case, an external thread 9, which cooperates with a corresponding internal thread 10 of the blade bearing ring 2 for fixing this first end 6 on the blade bearing ring 2.

Wie sich insbesondere aus der vergrößerten Darstellung der Fig. 3 erschließt, ist das zweite Ende 7 des Tragstiftes 5 in einer Ausnehmung 11 der Scheibe 3 angeordnet und in einem konisch erweiterten Bereich 12 der Ausnehmung 11 mit der Scheibe 3 über eine Verschweißung 13 verbunden. Hierzu ist das Ende 7 an seiner Stirnfläche dachartig verjüngt, um eine Perfektionierung der Schweißnaht 13 erreichen zu können.As can be seen in particular from the enlarged view of FIG. 3, the second end 7 of the support pin 5 is arranged in a recess 11 of the disc 3 and connected in a conically widened region 12 of the recess 11 with the disc 3 via a weld 13. For this purpose, the end 7 is roof-like tapered at its end face in order to achieve a perfecting of the weld 13 can.

Um die Ausnehmung 11 der Scheibe 3 herum ist in der in den Fig. 2 und 3 dargestellten besonders bevorzugten Ausführungsform eine Wärmedrossel in Form einer umlaufenden Nut 14 vorgesehen, die verhindert, dass die Wärme direkt in den massiven Teil der Scheibe 3 eindringen kann, was zur Vermeidung von Verzug der Scheibe 3 beim Verschweißen beiträgt und überdies die erforderliche einzutragende Schweißenergie vermindert.Around the recess 11 of the disc 3, a heat choke in the form of a circumferential groove 14 is provided in the particularly preferred embodiment shown in Figs. 2 and 3, which prevents the heat can penetrate directly into the massive part of the disc 3, which contributes to the prevention of distortion of the disc 3 during welding and also reduces the required input welding energy.

Gemäß dem erfindungsgemäßen Verfahren wird zur Herstellung einer zuvor beschriebenen erfindungsgemäßen Schaufellagerringanordnung 1 neben den üblichen Herstellungsschritten für den Schaufellagerring 2, die Schaufelwellen, Hebel und sonstigen üblicherweise vorgesehenen Teile, die Scheibe 3 mit jeweils einer Ausnehmung 11 pro Tragstift 5 versehen, wobei um jede dieser Ausnehmungen 11 die zuvor beschriebene Wärmedrossel in Form der umlaufenden Nut 14 angebracht wird.According to the inventive method for producing a previously described blade bearing ring assembly 1 according to the invention in addition to the usual manufacturing steps for the blade bearing ring 2, the blade shafts, levers and other commonly provided parts, the disc 3 is provided with one recess 11 per support pin 5, wherein each of these recesses 11, the above-described heat choke in the form of the circumferential groove 14 is attached.

Anschließend wird zur Fixierung der Scheibe 3 am Schaufellagerring 2 zunächst das erste Ende 6 des Tragstiftes 5 mit dem Schaufellagerring 2 verschraubt. Sodann werden in der Zeichnung nicht näher dargestellte Distanzkörper zwischen Schaufellagerring 2 und Scheibe 3 eingelegt, um die definierte Distanz zwischen dem Schaufellagerring 2 und der Scheibe 3 einstellen zu können. Dann erfolgt die Verschweißung des zweiten Endes 7 und die Entfernung der Distanzkörper.Subsequently, first the first end 6 of the support pin 5 is screwed to the blade bearing ring 2 for fixing the disc 3 on the blade bearing ring 2. Then in the drawing not shown spacers between the blade bearing ring 2 and disc 3 are inserted to the defined distance to be able to adjust between the blade bearing ring 2 and the disc 3. Then, the welding of the second end 7 and the removal of the spacers takes place.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
SchaufellagerringanordnungBlade bearing ring arrangement
22
SchaufellagerringNozzle ring
33
Scheibedisc
44
Strömungskanalflow channel
55
Tragstift (Tragstifte)Support pin (support pins)
66
Erstes Ende des Tragstiftes 5First end of the support pin 5
77
Zweites zu verschweißendes Ende des Tragstiftes 5Second end of the support pin 5 to be welded
88th
Schaftabschnittshank portion
99
Außengewindeexternal thread
1010
Innengewinde des Schaufellagerrings 2Internal thread of the blade bearing ring 2
1111
Ausnehmungrecess
1212
Konisch erweiterter BereichConically extended area
1313
Verschweißungwelding
1414
Wärmedrossel (Nut)Heat choke (groove)
1515
Turboladerturbocharger
1616
Verdichterradcompressor
1717
Verdichtergehäusecompressor housing
1818
Lagergehäusebearing housing
1919
Wellewave
2020
Turbinenradturbine
2121
Turbinengehäuseturbine housing

Claims (8)

Turbolader mit variabler Turbinengeometrie - mit einer Schaufellagerringanordnung (1), die einen Schaufellagerring (2) und eine Scheibe (3) aufweist, die am Schaufellagerring (2) zur Schaffung eines Strömungskanals (4) fixierbar ist; - mit zumindest einem Tragstift (5), der mit einem ersten Ende (6) mit dem Schaufellagerring (2) verbunden ist und der mit einem zweiten Ende (7) mit der Scheibe (3) verschweißt ist; gekennzeichnet dadurch, - dass die Scheibe (3) pro Tragstift (5) eine Ausnehmung (11) für das zu verschweißende Tragstiftende (7) aufweist, die von einer Wärmedrossel (14) umgeben ist. Turbocharger with variable turbine geometry - With a blade bearing ring assembly (1) having a blade bearing ring (2) and a disc (3) which is fixed to the blade bearing ring (2) to provide a flow channel (4); - With at least one support pin (5) which is connected to a first end (6) with the blade bearing ring (2) and which is welded to a second end (7) with the disc (3); characterized by - That the disc (3) per support pin (5) has a recess (11) for the support pin end (7) to be welded, which is surrounded by a heat throttle (14). Turbolader nach Anspruch 1, dadurch gekennzeichnet, dass die Wärmedrossel als um die Ausnehmung (11) umlaufende Nut (14) ausgebildet ist.Turbocharger according to claim 1, characterized in that the heat choke is formed as around the recess (11) circumferential groove (14). Turbolader nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass das erste Ende (6) des Tragstiftes (5) mit einem Außengewinde (9) versehen ist.Turbocharger according to one of claims 1 to 2, characterized in that the first end (6) of the support pin (5) is provided with an external thread (9). Turbolader nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass der Tragstift (5) einen Schaftabschnitt (8) zwischen dem ersten und zweiten Ende (6 bzw. 7) aufweist, der im Außendurchmesser verjüngt ist.Turbocharger according to one of claims 1 to 3, characterized in that the support pin (5) has a shank portion (8) between the first and second ends (6 and 7, respectively), which is tapered in outer diameter. Schaufellagerringanordnung (1) gemäß dem Oberbegriff des Anspruches 1 für einen Turbolader mit variabler Turbinengeometrie gekennzeichnet durch wenigstens eines der Merkmale der Ansprüche 1 bis 4.Blade bearing ring assembly (1) according to the preamble of claim 1 for a turbocharger with variable turbine geometry characterized by at least one of the features of claims 1 to 4. Verfahren zur Herstellung einer Schaufellagerringanordnung (1) gemäß nach einem der Ansprüche 1 bis 5, gekennzeichnet durch folgende Verfahrensschritte: - Befestigen des ersten Endes (6) des bzw. der Tragstifte (5) am Schaufellagerring (2); - Anordnen von Distanzkörpern zwischen dem Schaufellagerring (2) und der Scheibe (3); - Verschweißen des zweiten Endes (7) des Tragstiftes (5) in einer Ausnehmung (11) der Scheibe (3); und - Entfernen der Distanzkörper nach der Verschweißung. Method for producing a blade bearing ring arrangement (1) according to one of claims 1 to 5, characterized by the following method steps: - Fixing the first end (6) of the or the support pins (5) on the vane bearing ring (2); - Arranging spacers between the blade bearing ring (2) and the disc (3); - Welding of the second end (7) of the support pin (5) in a recess (11) of the disc (3); and - Remove the spacers after welding. Verfahren nach Anspruch 6, dadurch gekennzeichnet, dass das erste Ende (6) des Tragstiftes (5) mit dem Schaufellagerring (2) verschraubt wird.A method according to claim 6, characterized in that the first end (6) of the support pin (5) with the blade bearing ring (2) is screwed. Verfahren nach Anspruch 6 oder 7, dadurch gekennzeichnet, dass in der Scheibe (3) eine Wärmedrossel in Form einer um die Ausnehmung (11) umlaufenden Nut (14) angebracht wird.A method according to claim 6 or 7, characterized in that in the disc (3) a heat choke in the form of a circumferential groove (14) around the recess (11) is mounted.
EP04030888.4A 2004-12-28 2004-12-28 Turbocharger with variable geometry turbine Active EP1676980B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP04030888.4A EP1676980B1 (en) 2004-12-28 2004-12-28 Turbocharger with variable geometry turbine
JP2005348934A JP4578394B2 (en) 2004-12-28 2005-12-02 Variable turbo turbine turbocharger
KR1020050124596A KR101172834B1 (en) 2004-12-28 2005-12-16 Turbocharger of variable turbine geometry
CNB2005101340463A CN100478546C (en) 2004-12-28 2005-12-27 Turbocharger of variable turbine geometry
US11/321,300 US7507067B2 (en) 2004-12-28 2005-12-28 Turbocharger of variable turbine geometry

Applications Claiming Priority (1)

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WO2007093406A1 (en) * 2006-02-16 2007-08-23 Borgwarner Inc. Blade bearing ring assembly of a turbocharger with a variable turbine geometry
WO2009092635A2 (en) * 2008-01-23 2009-07-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg Supercharger device
DE102008039093A1 (en) * 2008-08-21 2010-02-25 Bosch Mahle Turbo Systems Gmbh & Co. Kg Turbo-supercharger for internal combustion engine of motor vehicle, has turbine wheel and compressor wheel, which are mounted in bearing housing by common shaft
US7918023B2 (en) 2007-02-08 2011-04-05 Honeywell International Inc. Method for manufacturing a variable-vane mechanism for a turbocharger
EP2093379A3 (en) * 2008-02-25 2012-06-20 Honeywell International Inc. Variable-nozzle assembly for a turbocharger
DE102019217316A1 (en) * 2019-11-08 2021-05-12 Volkswagen Aktiengesellschaft Exhaust gas turbocharger for high-performance engine concepts

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WO2009076062A2 (en) * 2007-12-12 2009-06-18 Honeywell International Inc. Variable nozzle for a turbocharger, having nozzle ring located by radial members
AT504757B1 (en) * 2008-04-03 2009-08-15 Avl List Gmbh ABGASTURBOLADER WITH AN ABGASTURBINE
AT504758B1 (en) * 2008-04-03 2009-06-15 Avl List Gmbh ABGASTURBOLADER WITH AN ABGASTURBINE
AT504446B1 (en) * 2008-01-24 2009-05-15 Avl List Gmbh TURBOCHARGER
CN103080497B (en) * 2010-09-27 2015-05-20 博格华纳公司 Method for manufacturing a turbocharger
US9638060B2 (en) * 2011-04-11 2017-05-02 Borgwarner Inc. Bearing housing of an exhaust-gas turbocharger
JP2015502483A (en) * 2011-11-16 2015-01-22 マック トラックス インコーポレイテッド Diesel engine apparatus and method for varnish deposition control
US9850810B2 (en) * 2011-11-23 2017-12-26 Borgwarner Inc. Exhaust-gas turbocharger
KR101983756B1 (en) * 2012-03-15 2019-09-03 보르그워너 인코퍼레이티드 Exhaust-gas turbocharger
US11085320B2 (en) * 2018-09-25 2021-08-10 Garrett Transportation I Inc Variable vane mechanism of turbocharger having predetermined vane clearance
CN110925242B (en) * 2019-12-13 2020-12-15 宗立君 Turbocharger

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007093406A1 (en) * 2006-02-16 2007-08-23 Borgwarner Inc. Blade bearing ring assembly of a turbocharger with a variable turbine geometry
US7918023B2 (en) 2007-02-08 2011-04-05 Honeywell International Inc. Method for manufacturing a variable-vane mechanism for a turbocharger
WO2009092635A2 (en) * 2008-01-23 2009-07-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg Supercharger device
WO2009092635A3 (en) * 2008-01-23 2010-04-22 Bosch Mahle Turbo Systems Gmbh & Co. Kg Supercharger device
US8747059B2 (en) 2008-01-23 2014-06-10 Bosch Mahle Turbo Systems Gmbh & Co. Kg Supercharger device
EP2093379A3 (en) * 2008-02-25 2012-06-20 Honeywell International Inc. Variable-nozzle assembly for a turbocharger
DE102008039093A1 (en) * 2008-08-21 2010-02-25 Bosch Mahle Turbo Systems Gmbh & Co. Kg Turbo-supercharger for internal combustion engine of motor vehicle, has turbine wheel and compressor wheel, which are mounted in bearing housing by common shaft
DE102019217316A1 (en) * 2019-11-08 2021-05-12 Volkswagen Aktiengesellschaft Exhaust gas turbocharger for high-performance engine concepts

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CN100478546C (en) 2009-04-15
KR20060076206A (en) 2006-07-04
US20060140751A1 (en) 2006-06-29
JP2006189041A (en) 2006-07-20
CN1796729A (en) 2006-07-05
JP4578394B2 (en) 2010-11-10
EP1676980B1 (en) 2015-10-14
KR101172834B1 (en) 2012-08-10
US7507067B2 (en) 2009-03-24

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