EP1984611A1 - Blade bearing ring assembly of a turbocharger with a variable turbine geometry - Google Patents

Blade bearing ring assembly of a turbocharger with a variable turbine geometry

Info

Publication number
EP1984611A1
EP1984611A1 EP07703476A EP07703476A EP1984611A1 EP 1984611 A1 EP1984611 A1 EP 1984611A1 EP 07703476 A EP07703476 A EP 07703476A EP 07703476 A EP07703476 A EP 07703476A EP 1984611 A1 EP1984611 A1 EP 1984611A1
Authority
EP
European Patent Office
Prior art keywords
bearing ring
blade bearing
disc
turbocharger
support pin
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP07703476A
Other languages
German (de)
French (fr)
Inventor
Timo Tries
Ralf Böning
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
Original Assignee
BorgWarner Inc
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 BorgWarner Inc filed Critical BorgWarner Inc
Publication of EP1984611A1 publication Critical patent/EP1984611A1/en
Withdrawn legal-status Critical Current

Links

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
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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
    • 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
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49236—Fluid pump or compressor making

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 known from EP-AI 236 866 turbocharger consists of a nozzle with blades and levers and turbine housing side disc.
  • 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 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.
  • FIG. 1 is a perspective view of a turbocharger according to the invention
  • Fig. 2 is a sectional view of a blade bearing assembly according to the invention for the turbocharger according to the invention.
  • Fig. 3A-C the detail X of Fig. 2 in an enlarged view for explaining the method according to the invention. 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 their 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 9 arranged in the flow channel 4 is arranged in the assembled state.
  • the blade bearing ring 2 and the disc 3 are each provided with a preferably flat fastening for producing a previously described blade bearing ring arrangement 1 according to the invention.
  • the first end 6 of the support pin 5 is first butt connected to the blade bearing ring 2, ie the substantially planar end 6 is preferably mounted with a positioning tool 8 on the preferably planar mounting portion 12 (FIG. 3A) and then connected thereto, preferably welded (Fig. 3B). Then, the spacer body 11 shown in Fig. 3B between the blade bearing ring 2 and disc 3 are inserted to adjust the defined distance between the blade bearing ring 2 and the disc 3 can. Then, the connection, preferably welding, of the second substantially planar end 7 of the support pin 5 with the associated preferably planar mounting portion 13 of the disc 3 and the removal of the spacer or body 11. It is inventively possible that first either the blade bearing ring or the disc 3 with one of the support pin ends and then the other support pin end with the other part (ie either disc or blade bearing ring) is connected.

Abstract

The invention relates to a turbocharger with a variable turbine geometry. Said turbocharger comprises a blade bearing ring assembly (1) with a blade bearing ring (2) and a disc (3), which can be fixed to the blade bearing ring (2) to create a flow channel (4) and also comprises at least one bearing pin (5), one first end (6) of which is connected to the blade bearing ring (2) and the second end (7) of which is connected to the disc (3). Both ends of the bearing pin are butt welded to the blade bearing ring (2) and the disc (3).

Description

SCHAUFELLAGERRINGANORDNUNG EINES TURBOLADERS MIT VARIABLER TURBINENGEOMETRIEBAG BEARING ARRANGEMENT OF A TURBOCHARGER WITH VARIABLE TURBINE GEOMETRY
BesehreibungBesehreibung
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 aus der EP-A-I 236 866 bekannten 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. 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.The VTG cartridge of such a known from EP-AI 236 866 turbocharger consists of a nozzle with blades and levers and turbine housing side disc. 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. To be able 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. 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 that connects as possible distortion of the disc with the blade bearing ring, so that a constant uniform spacing as in the Joining by means of screws. The solution of this object is achieved by the features of claim 1.
Im Unteranspruch 2 ist eine erfindungsgemäße Schaufellagerringanordnung definiert.In dependent claim 2 a blade bearing ring assembly according to the invention is defined.
In den Ansprüchen 3 bis 5 ist ein erfindungsgemäßes Verfahren zur Herstellung einer Schaufellagerringanordnung für den erfindungsgemäßen Turbolader angegeben.In the claims 3 to 5 an inventive method for producing a blade bearing ring assembly for the turbocharger according to the invention is given.
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: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 eine perspektivische Darstellung eines erfindungsgemäßen Turboladers,1 is a perspective view of a turbocharger according to the invention,
Fig. 2 eine Schnittdarstellung einer erfindungsgemäßen Schaufellageranordnung für den erfindungsgemäßen Turbolader, undFig. 2 is a sectional view of a blade bearing assembly according to the invention for the turbocharger according to the invention, and
Fig. 3A-C die Einzelheit X der Fig. 2 in vergrößerter Darstellung zur Erläuterung des erfindungsgemäßen Verfahrens . 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.Fig. 3A-C, the detail X of Fig. 2 in an enlarged view for explaining the method according to the invention. 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 their 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 9 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 9 arranged in the flow channel 4 is arranged in the assembled state.
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, der Schaufellagerring 2 und die Scheibe 3 jeweils mit einem vorzugsweise planen Befesti- gungsbereich 12 bzw. 13 für den bzw. die Tragstifte 5 versehen.In accordance with the method according to the invention, in addition to the usual manufacturing steps for the blade bearing ring 2, the blade shafts, levers and other conventionally provided parts, the blade bearing ring 2 and the disc 3 are each provided with a preferably flat fastening for producing a previously described blade bearing ring arrangement 1 according to the invention. tion area 12 and 13 for the or the support pins 5 provided.
Anschließend wird zur Fixierung der Scheibe 3 am Schaufellagerring 2 zunächst das erste Ende 6 des Tragstiftes 5 mit dem Schaufellagerring 2 stumpf verbunden, d. h. das im wesentlichen plane Ende 6 wird, vorzugsweise mit einem Positionierungswerkzeug 8, auf den vorzugsweise planen Befestigungsbereich 12 aufgesetzt (Fig. 3A) und dann mit diesem verbunden, vorzugsweise verschweißt (Fig. 3B). Sodann werden der bzw. die in Fig. 3B dargestellten Distanzkörper 11 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 Verbindung, vorzugsweise Verschweißung, des zweiten im wesentlichen planen Endes 7 des Tragstiftes 5 mit dem zugeordneten vorzugsweise planen Befestigungsbereich 13 der Scheibe 3 und die Entfernung des bzw. der Distanzkörper 11. Hierbei ist es erfindungsgemäß möglich, dass zuerst entweder der Schaufellagerring oder die Scheibe 3 mit einem der Tragstiftenden und dann das andere Tragstiftende mit dem jeweils anderen Teil (also entweder Scheibe oder Schaufellagerring) verbunden wird. Subsequently, to fix the disc 3 on the blade bearing ring 2, the first end 6 of the support pin 5 is first butt connected to the blade bearing ring 2, ie the substantially planar end 6 is preferably mounted with a positioning tool 8 on the preferably planar mounting portion 12 (FIG. 3A) and then connected thereto, preferably welded (Fig. 3B). Then, the spacer body 11 shown in Fig. 3B between the blade bearing ring 2 and disc 3 are inserted to adjust the defined distance between the blade bearing ring 2 and the disc 3 can. Then, the connection, preferably welding, of the second substantially planar end 7 of the support pin 5 with the associated preferably planar mounting portion 13 of the disc 3 and the removal of the spacer or body 11. It is inventively possible that first either the blade bearing ring or the disc 3 with one of the support pin ends and then the other support pin end with the other part (ie either disc or blade bearing ring) is connected.
BezugszeichenlisteLIST OF REFERENCE NUMBERS
1 Schaufellagerringanordnung1 vane ring assembly
2 Schaufellagerring2 blade bearing ring
3 Scheibe3 disc
4 Strömungskanal4 flow channel
5 Tragstift (Tragstifte)5 support pin (support pins)
6 Erstes Ende des Tragstiftes 56 First end of the support pin 5
7 Zweites zu verschweißendes Ende des Tragstiftes 57 Second end of the support pin 5 to be welded
8 Positionierungswerkzeug8 positioning tool
9 Schaftabschnitt 0 1 Distanzstück/-körper 2 planer Befestigungsbereich von 2 3 planer Befestigungsbereich von 3 4, 14' Schweißzonen 5 Turbolader 6 Verdichterrad 7 Verdichtergehäuse 8 Lagergehäuse 9 Welle 0 Turbinenrad 1 Turbinengehäuse 9 Shank section 0 1 Spacer / body 2 Plane mounting area of 2 3 Plane mounting area of 3 4, 14 'Welding zones 5 Turbocharger 6 Compressor wheel 7 Compressor housing 8 Bearing housing 9 Shaft 0 Turbine wheel 1 Turbine housing

Claims

Ansprüche claims
1. 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) verbunden ist; dadurch gekennzeichnet, dass beide Enden (6, 7) des Tragstiftes (5) stumpf mit dem Schaufellagerring (2) bzw. der Scheibe (3) verschweißt sind.A turbocharger with variable turbine geometry with a vane ring assembly (1) having a vane ring (2) and a disc (3) which is fixed to the vane ring (2) to create a flow channel (4); with at least one support pin (5) connected to a first end (6) with the blade bearing ring (2) and connected to the disc (3) with a second end (7); characterized in that both ends (6, 7) of the support pin (5) are butt welded to the blade bearing ring (2) or the disc (3).
2. Schaufellagerringanordnung (1) für einen Turbolader mit variabler Turbinengeometrie mit einem Schaufellagerring (2) und einer Scheibe (3), die am Schaufellagerring (2) zur Schaffung eines Strömungskanals (4) fixierbar ist; und 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) verbunden ist, dadurch gekennzeichnet, dass beide Enden (6, 7) des Tragstiftes (5) stumpf mit dem Schaufellagerring (2) bzw. der Scheibe (3) verschweißt sind.2. Blade bearing ring assembly (1) for a turbocharger with variable turbine geometry with a blade bearing ring (2) and a disc (3) which is fixable on the blade bearing ring (2) to provide a flow channel (4); and with at least one support pin (5) which is connected with a first end (6) to the blade bearing ring (2) and which is connected to a second end (7) with the disc (3), characterized in that both ends ( 6, 7) of the support pin (5) butt welded to the blade bearing ring (2) or the disc (3) are welded.
3. Verfahren zur Herstellung einer Schaufellagerringanordnung (1) für einen Turbolader, gekennzeichnet durch folgende3. A method for producing a vane bearing ring assembly (1) for a turbocharger, characterized by the following
Verfahrensschritte:Steps:
Befestigen des ersten Endes (6) des bzw. der Tragstifte (5) mit einem, vorzugsweise planen, Befestigungsbereich (12) eines Schaufellagerringes (2) oder einer Scheibe mittels einer stoffschlüssigen Verbindung; Anordnen von Distanzkörpern (11) zwischen dem Schaufellagerring (2) und der Scheibe (3) ;Fixing the first end (6) of the support pin (s) (5) with a, preferably planar, mounting region (12) of a blade bearing ring (2) or a disk by means of a material connection; Arranging spacer bodies (11) between the blade bearing ring (2) and the disc (3);
Befestigen des zweiten Endes (7) des Tragstiftes (5) mit einem ebenfalls vorzugsweise planen Befestigungsbereich (13) der Scheibe (3) bzw. des Schaufellagerrings (2) mittels einer stoffschlüssigen Verbindung; undAttaching the second end (7) of the support pin (5) with a likewise preferably planar mounting region (13) of the disc (3) or the blade bearing ring (2) by means of a material connection; and
Entfernen der Distanzkörper (11) nach der Befestigung der Enden (6 , 7) des Tragstiftes (5) .Removing the spacers (11) after the attachment of the ends (6, 7) of the support pin (5).
4. Verfahren nach Anspruch 3, dadurch gekennzeichnet, dass als stoffschlüssige Verbindung eine Verschweißung (14, 14') verwendet wird.4. The method according to claim 3, characterized in that as a cohesive connection a weld (14, 14 ') is used.
5. Verfahren nach Anspruch 3 oder 4, dadurch gekennzeichnet, dass nicht wärmeleitende Distanzkörper (11) verwendet werden . 5. The method according to claim 3 or 4, characterized in that non-heat-conducting spacers (11) are used.
EP07703476A 2006-02-16 2007-02-14 Blade bearing ring assembly of a turbocharger with a variable turbine geometry Withdrawn EP1984611A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006007319 2006-02-16
PCT/EP2007/001291 WO2007093406A1 (en) 2006-02-16 2007-02-14 Blade bearing ring assembly of a turbocharger with a variable turbine geometry

Publications (1)

Publication Number Publication Date
EP1984611A1 true EP1984611A1 (en) 2008-10-29

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP07703476A Withdrawn EP1984611A1 (en) 2006-02-16 2007-02-14 Blade bearing ring assembly of a turbocharger with a variable turbine geometry

Country Status (6)

Country Link
US (1) US20090067996A1 (en)
EP (1) EP1984611A1 (en)
JP (1) JP2009526938A (en)
KR (1) KR20080100198A (en)
CN (1) CN101384807A (en)
WO (1) WO2007093406A1 (en)

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CN101865032B (en) * 2009-04-20 2014-06-18 博格华纳公司 Simplified variable geometry turbocharger with sliding gate and multiple volutes
CN101598037B (en) * 2009-06-30 2011-08-31 康跃科技股份有限公司 Zero clearance floating regulating device with variable nozzle
WO2012040039A2 (en) * 2010-09-23 2012-03-29 Borgwarner Inc. Vtg cartridge of an exhaust-gas turbocharger
CN103080497B (en) * 2010-09-27 2015-05-20 博格华纳公司 Method for manufacturing a turbocharger

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US20090067996A1 (en) 2009-03-12
WO2007093406A1 (en) 2007-08-23

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