EP1676980B1 - Turbocharger with variable geometry turbine - Google Patents

Turbocharger with variable geometry turbine Download PDF

Info

Publication number
EP1676980B1
EP1676980B1 EP04030888.4A EP04030888A EP1676980B1 EP 1676980 B1 EP1676980 B1 EP 1676980B1 EP 04030888 A EP04030888 A EP 04030888A EP 1676980 B1 EP1676980 B1 EP 1676980B1
Authority
EP
European Patent Office
Prior art keywords
bearing ring
disc
turbocharger
support pin
vane bearing
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.)
Active
Application number
EP04030888.4A
Other languages
German (de)
French (fr)
Other versions
EP1676980A1 (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
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
Family has litigation
Application filed by BorgWarner Inc filed Critical BorgWarner Inc
Priority to EP04030888.4A priority Critical patent/EP1676980B1/en
Publication of EP1676980A1 publication Critical patent/EP1676980A1/en
Application granted granted Critical
Publication of EP1676980B1 publication Critical patent/EP1676980B1/en
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=34928016&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1676980(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00Regulating or controlling by varying flow
    • F01D17/10Final actuators
    • F01D17/12Final actuators arranged in stator parts
    • F01D17/14Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165Final 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00Application
    • F05D2220/40Application in turbochargers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00Manufacture
    • F05D2230/30Manufacture with deposition of material
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/20Heat transfer, e.g. cooling
    • F05D2260/231Preventing heat transfer

Description

  • Die Erfindung betrifft eine Schaufellagerringanordnung für einen Turbolader mit variabler Turbinengeometrie (VTG) gemäß dem Oberbegriff des Anspruches 1.The invention relates to a blade bearing ring arrangement for a turbocharger with variable turbine geometry (VTG) according to the preamble of claim 1.
  • Die VTG-Kartusche eines derartigen aus der EP 1 236 866 A 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.The VTG cartridge of such from the EP 1 236 866 A known 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.
  • Es ist daher Aufgabe der vorliegenden Erfindung, eine Schaufellagerringanordnung für einen Turbolader der im Oberbegriff des Anspruches 1 angegebenen Art zu schaffen, bei der 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 blade bearing ring assembly for a turbocharger specified in the preamble of claim 1 species, in which it is possible to produce a welded joint that connects the disc as possible distortion with the blade bearing ring, so that a constant uniform distance as in the connection 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 der erfindungsgemäßen Schaufellagerringanordnung zum Inhalt.The dependent claims 2 to 4 have advantageous developments of the blade bearing ring assembly according to the invention to the content.
  • Um beim Verschweißen ein unerwünschtes Verziehen der Scheibe vermeiden zu können, ist eine Wärmedrossel vorgesehen, die die Ausnehmung für das zu verschweißende Tragstiftende umgibt.In order to avoid unwanted distortion of the disc during welding, a heat choke is provided which surrounds the recess for the support pin end to be welded.
  • Diese Wärmedrossel ist als eine um die Ausnehmung für das zu verschweißende Tragstiftende umlaufende Nut ausgebildet.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 the 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 design details of a turbocharger with variable turbine geometry is not required for the following description of the design principles according to the invention, are in Fig. 1 only the basic components of a turbocharger 15 according to the invention referred to, as usual, a compressor 16 in a compressor housing 17, a bearing housing 18 with the required bearings for the shaft 19 and a turbine 20 in a turbine housing 21 has. 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, in Fig. 2 only one vane bearing assembly 1 of a turbocharger according to the invention shown. 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 can be seen from a synopsis of Fig. 2 and 3 results in the end 6 in the example 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 illustration of Fig. 3 opens, the second end 7 of the support pin 5 is disposed in a recess 11 of the disc 3 and connected in a flared area 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, wie in Fig. 2 und 3 dargestellt, 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 is around, as in Fig. 2 and 3 shown, a heat choke in the form of a circumferential groove 14 is provided, which prevents the heat can penetrate directly into the massive part of the disc 3, which helps to avoid distortion of the disc 3 during welding and also reduces the required input welding energy.
  • Gemäß eines Verfahrens 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 a 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 (4)

  1. Vane bearing ring arrangement (1) for a turbocharger with variable turbine geometry,
    - having a vane bearing ring (2) and having a disc (3) which can be fixed to the vane bearing ring (2) in order to create a flow duct (4); and
    - having at least one support pin (5) which is connected by way of the first end (6) to the vane bearing ring (2) and which is welded by way of its second end (7) to the disc (3) which, for each support pin (5), has a recess (11) for the support pin end (7) to be welded, said recess being surrounded by a heat throttle (14), characterized
    - in that the heat throttle is in the form of a groove (14) which encircles the recess (11).
  2. Vane bearing ring arrangement according to Claim 1, characterized in that the first end (6) of the support pin (5) is equipped with an external thread (9).
  3. Vane bearing ring arrangement according to Claim 1 or 2, characterized in that the support pin (5) has, between the first and second ends (6 and 7), a shank section (8) of narrowed external diameter.
  4. Turbocharger with variable turbine geometry, having a vane bearing ring arrangement according to one of Claims 1-3.
EP04030888.4A 2004-12-28 2004-12-28 Turbocharger with variable geometry turbine Active EP1676980B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04030888.4A EP1676980B1 (en) 2004-12-28 2004-12-28 Turbocharger with variable geometry turbine

Applications Claiming Priority (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
KR20050124596A KR101172834B1 (en) 2004-12-28 2005-12-16 Turbocharger of variable turbine geometry
CN 200510134046 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

Publications (2)

Publication Number Publication Date
EP1676980A1 EP1676980A1 (en) 2006-07-05
EP1676980B1 true EP1676980B1 (en) 2015-10-14

Family

ID=34928016

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04030888.4A Active EP1676980B1 (en) 2004-12-28 2004-12-28 Turbocharger with variable geometry turbine

Country Status (5)

Country Link
US (1) US7507067B2 (en)
EP (1) EP1676980B1 (en)
JP (1) JP4578394B2 (en)
KR (1) KR101172834B1 (en)
CN (1) CN100478546C (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090067996A1 (en) * 2006-02-16 2009-03-12 Borg Warner 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
AT522702T (en) * 2007-12-12 2011-09-15 Honeywell Int Inc Variable nozzle for a turbocharger with radial lines positioned nozzle ring
DE102008005658A1 (en) * 2008-01-23 2009-07-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg loader
AT504446B1 (en) * 2008-01-24 2009-05-15 Avl List Gmbh Turbocharger
US8021107B2 (en) * 2008-02-25 2011-09-20 Honeywell International Inc. Variable-nozzle assembly for a turbocharger
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
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
KR101823991B1 (en) * 2010-09-27 2018-01-31 보르그워너 인코퍼레이티드 Method for manufacturing turbocharger
KR101859539B1 (en) * 2011-04-11 2018-06-27 보르그워너 인코퍼레이티드 Bearing housing of an exhaust-gas turbocharger
BR112014011825A2 (en) * 2011-11-16 2017-05-09 Mack Trucks diesel engine layout and method for varnish buildup control
KR101989455B1 (en) * 2011-11-23 2019-09-30 보르그워너 인코퍼레이티드 Exhaust-gas turbocharger
DE112013000963T5 (en) * 2012-03-15 2014-11-06 Borgwarner Inc. turbocharger
DE102019217316A1 (en) * 2019-11-08 2021-05-12 Volkswagen Aktiengesellschaft Exhaust gas turbocharger for high-performance engine concepts
CN110925242B (en) * 2019-12-13 2020-12-15 宗立君 Turbocharger

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60169604A (en) * 1984-02-15 1985-09-03 Nissan Motor Co Ltd Radial tubine variable nozzle
DE3516738C2 (en) * 1985-05-09 1989-07-27 Mtu Friedrichshafen Gmbh
DE3541508C1 (en) * 1985-11-23 1987-02-05 Kuehnle Kopp Kausch Ag Exhaust gas turbocharger
DE3941715A1 (en) * 1989-12-18 1991-06-20 Porsche Ag EXHAUST TURBOCHARGER FOR AN INTERNAL COMBUSTION ENGINE
US5207565A (en) * 1992-02-18 1993-05-04 Alliedsignal Inc. Variable geometry turbocharger with high temperature insert in turbine throat
JP3664761B2 (en) * 1994-12-22 2005-06-29 三菱重工業株式会社 Exhaust turbocharger variable capacity turbine
JPH1162603A (en) * 1997-08-25 1999-03-05 Mitsubishi Heavy Ind Ltd Variable displacement supercharger
JP3771765B2 (en) * 2000-01-24 2006-04-26 三菱重工業株式会社 Variable turbocharger
JP3735262B2 (en) * 2001-02-27 2006-01-18 三菱重工業株式会社 Variable nozzle mechanism for variable capacity turbine and manufacturing method thereof
JP2003049663A (en) * 2001-08-03 2003-02-21 Sogi Kogyo Kk Manufacturing method for variable vane in vgs(variable geometry system) type turbocharger and variable vane manufactured by same method
JP2003184563A (en) * 2001-12-14 2003-07-03 Aisin Seiki Co Ltd Variable displacement turbocharger
DE50304673D1 (en) * 2003-10-27 2006-09-28 Borgwarner Inc Turbomachine and method for producing a Leitgitters

Also Published As

Publication number Publication date
CN1796729A (en) 2006-07-05
US20060140751A1 (en) 2006-06-29
EP1676980A1 (en) 2006-07-05
CN100478546C (en) 2009-04-15
JP2006189041A (en) 2006-07-20
KR101172834B1 (en) 2012-08-10
US7507067B2 (en) 2009-03-24
JP4578394B2 (en) 2010-11-10
KR20060076206A (en) 2006-07-04

Similar Documents

Publication Publication Date Title
DE60319612T2 (en) Control device for stator blade
DE3416648C2 (en) Device for balancing a rotating body
DE3110180C2 (en)
EP2078136B1 (en) Turbocharger
EP1146266B1 (en) Brush seal
EP0906514B1 (en) Rotor for a turbomachine with blades insertable into grooves and blades for a rotor
DE3629198C2 (en)
EP0784758B1 (en) Shaft fixture
DE60307100T2 (en) SEAL ASSEMBLY FOR THE ROTOR OF A TURBOMA MACHINE
EP2018475B1 (en) Rotor blade for a wind energy installation
EP2399004B1 (en) Rotor section for a rotor of a turbo machine, rotor blade for a turbo machine and blocking element
EP1672177B1 (en) Turbocharger
DE60029424T2 (en) IMPROVED STORAGE BUSHING FOR A GAS TURBINE BUCKET
DE69819290T2 (en) AIR SEPARATOR FOR GAS TURBINES
EP1426639B1 (en) Method for mounting a two row tapered roller bearing with segmented bearing rings in a wind motor
EP2358467B1 (en) Mixer
DE3040129C2 (en)
DE602004006732T2 (en) METHOD FOR PRODUCING A STATOR COMPONENT
DE60302525T2 (en) Drum rotor for a turbomachine
EP1502008B1 (en) Device for fixing a rotor on a shaft
DE4001379C2 (en) pump impeller
EP1536103B1 (en) Turbo machine having inlet guide vanes and attachment arrangement therefor
EP2813135B1 (en) Rod belt for rod belt conveyors of agricultural machines
EP0749198A2 (en) Squirrel cage rotor for an asynchronous machine
DE102012011913A1 (en) Electric motor with sleeve, which is fixed with high accuracy on a rotary shaft

Legal Events

Date Code Title Description
AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

17P Request for examination filed

Effective date: 20050428

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

AKX Designation fees paid

Designated state(s): DE FR GB IT NL

17Q First examination report despatched

Effective date: 20080131

INTG Intention to grant announced

Effective date: 20150615

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT NL

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502004015050

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: FP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502004015050

Country of ref document: DE

26N No opposition filed

Effective date: 20160715

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

PGFP Annual fee paid to national office [announced from national office to epo]

Ref country code: IT

Payment date: 20191219

Year of fee payment: 16

PGFP Annual fee paid to national office [announced from national office to epo]

Ref country code: NL

Payment date: 20201116

Year of fee payment: 17

PGFP Annual fee paid to national office [announced from national office to epo]

Ref country code: GB

Payment date: 20201130

Year of fee payment: 17

Ref country code: FR

Payment date: 20201119

Year of fee payment: 17

Ref country code: DE

Payment date: 20201112

Year of fee payment: 17