EP1528225A1 - Turbomachine et méthode de fabrication pour un anneau de guidage - Google Patents

Turbomachine et méthode de fabrication pour un anneau de guidage Download PDF

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Publication number
EP1528225A1
EP1528225A1 EP03024662A EP03024662A EP1528225A1 EP 1528225 A1 EP1528225 A1 EP 1528225A1 EP 03024662 A EP03024662 A EP 03024662A EP 03024662 A EP03024662 A EP 03024662A EP 1528225 A1 EP1528225 A1 EP 1528225A1
Authority
EP
European Patent Office
Prior art keywords
bolt
bearing ring
pin
blade bearing
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.)
Granted
Application number
EP03024662A
Other languages
German (de)
English (en)
Other versions
EP1528225B1 (fr
Inventor
Dietmar Metz
Dirk Frankestein
Ralf Böning
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
Priority to EP03024662A priority Critical patent/EP1528225B1/fr
Priority to DE50304673T priority patent/DE50304673D1/de
Priority to JP2004281195A priority patent/JP2005127321A/ja
Priority to US10/974,321 priority patent/US7303370B2/en
Publication of EP1528225A1 publication Critical patent/EP1528225A1/fr
Application granted granted Critical
Publication of EP1528225B1 publication Critical patent/EP1528225B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to a turbomachine, such as a turbine, a secondary air pump, but especially on a turbocharger.
  • a turbomachine such as a turbine, a secondary air pump, but especially on a turbocharger.
  • a turbomachine with a turbine housing with at least one supply channel for a driving fluid, such as the exhaust gas of an internal combustion engine, in which at least a turbine rotor is rotatably mounted about a rotation axis around which the fluid a grid of variable turbine geometry surrounding the turbine rotor radially on the outside can be fed.
  • the guide grid has a blade bearing ring, on each of an associated axis a plurality of adjustable about their respective axis blades is mounted in an axially limited vane space around the turbine rotor, the Exhaust gas can be supplied via the blades in an adjustable amount, which blade bearing ring which forms an axial boundary of a blade space, and with a spacer device to secure an axial distance for the free mobility of Shovels, which spacer means at least one of the blade bearing ring passing through bolt, pin or the like. having.
  • Such a turbocharger and such a blade bearing ring is for example from the EP-A-0 226 444 and US-A-5,146,752, respectively.
  • the axial dimension of the blade space by means of bolts pushed over distance-retaining Spacers secured, which of course a bolt diameter clearly must have excess outer diameter.
  • spacers approximately in stud shape integral with a Ring form these spacers are penetrated in each case by a bolt.
  • the invention proceeds in a first step from the knowledge that the efficiency a turbomachine of course, from a high implementation of the driving in Fluid available energy in revolutions of the turbine wheel depends. each Disturbance or any resistance within the flow path must therefore the efficiency undesirably decrease. Because of this realization was in in a further step, how to improve the flow in such a machine can be. It turned out that the previously connected over the or the Bolt lying spacers or spacer knobs around the turbine rotor and in particular in the connection path between the supply channel and turbine rotor one not cause insignificant vortex formation, which contributes to the reduction of the efficiency.
  • the problem thus identified is solved by the fact that the respective Bolt, pin or the like. itself is designed as a spacer device by passing between the vane bearing ring and a part provided in the turbine housing at one end used at least at other times with the aid of a molten state, but then temperature-resistant Kunststoffsmateriales on the axial Distance of the bucket bearing space is fixed. This is only the diameter of the pin or pin in the path of communication of the fluid to the turbine rotor, i. it results a much lower flow resistance than before. In short, it exists the invention in the use of the bolt or pin itself and without a thickening Sheathing as a spacer. It should be under "temperature resistant" a material be understood, which in the operation of the turbomachine, and in particular turbocharger, temperatures do not have the necessary strength loses.
  • the coatable in the molten state, but then temperature-resistant bonding material may in principle be a brazing material because there are brazing materials that themselves the temperatures of a turbocharger endure (in other turbomachines with lower operating temperatures, this is no problem anyway). However, it is preferred in general, when the determination of the distance is given by welding.
  • the part provided in the turbine housing may be a wall of the turbine housing be yourself, but it is preferable if he from a the blade bearing ring opposite mounting ring is formed, because in this way a pre-assembly the guide grid can be done outside the turbine housing and preassembled so Leitgitter only needs to be fixed in the turbine housing needs.
  • the bolt or pin of the Side of the part of the turbine housing so the housing wall or the mounting ring to insert and about the blade bearing ring with the help of the connecting material (in this case, in general, a brazing material) set.
  • the connecting material in this case, in general, a brazing material
  • the bolt, pin or the like at least over the the blade storage room traversing length at least approximately facing the axis of rotation Flow profile, e.g. such as a teardrop-shaped profile similar to one Aircraft or ship hull, owns.
  • the present invention also relates to a method of manufacturing a guide grid for a turbomachine according to the invention.
  • This method is characterized in that only between the blade bearing ring and the turbine housing (2) provided or to be provided part at least one removable spacer is used according to the desired nominal distance, that the bolt, Pen or the like. only then is fixed on the thus determined distance, whereupon the or the spacers is removed or will be.
  • a turbocharger 1 in a conventional manner a turbine housing part 2 and an associated compressor housing part 3 along an axis of rotation R are arranged.
  • the turbine housing part 2 is partially shown in section, so that a blade bearing ring 6 forming a radially outer guide grid, distributed over the circumference Guide vanes 7 about their the blade bearing ring 6 passing through pivot axes.
  • an actuating device 11 To control the movement or the position of the guide vanes 7 is an actuating device 11 provided. This can be of any nature in itself, but it is preferable if, in a conventional manner, it has a control housing 12 that controls the movement a ram member 14 attached to it controls its movement in known manner on a behind the blade bearing ring 6 (left behind in Fig. 1) the same adjusting ring 5 implement the same in a slight rotational movement.
  • This rotational movement are about the shafts 8, the vanes 7 in terms of their Rotary position relative to the turbine rotor 4 adjusted so that they are from an approximately tangential an extreme position in an approximately radially extending other extreme position adjustable are.
  • the turbine housing 2 with a flange 17 of a bearing housing connected, from which a cylindrical piece 40 projects into the turbine housing 2 and the shaft 35 of the turbine rotor 4 stores.
  • the turbine housing 2 comprises the already mentioned, the turbine rotor 4 surrounding supply channel 9 for the turbine rotor 4 driving Fluid, a rotor chamber 23 and the axial nozzle 10, through which the fluid or the Exhaust is released again.
  • This guide grid essentially has a turbine rotor 4 concentric surrounding wreath of movable, housed in a vane space 13 vanes 7, which at the fixedly connected with them adjusting shafts 8 (Fig. 1) in one the turbine rotor 4 coaxially surrounding blade bearing ring 6 are mounted.
  • the rotation or adjustment of the adjusting 8 can in a conventional manner be done via the actuator 11 to the control housing 12, the control movement the attached to it, only dash-dotted lines indicated plunger member 14th (Fig. 1), whose movement via an actuating lever 18, one connected thereto Actuating shaft 19 and for example via an opening in a behind the vane ring 6 located adjusting ring 5 engaging eccentric 20 in a slight rotational movement of this ring 5 is implemented around the axis R. Because in the adjusting ring 5 can be in a known manner, the free ends of the levers or heads be mounted, which are fixed to the adjusting shafts 8 (in Fig. 1, left of the shaft 8).
  • the guide vanes 7 are positioned above the shafts 8 their rotational position relative to the turbine rotor 4 adjusted so that it is approximately tangential extending an extreme position in an approximately radially extending other extreme position are adjustable.
  • the exhaust gas supplied via the supply channel becomes a Internal combustion engine more or less supplied to the turbine rotor 4, before it at which extends along the axis of rotation R extending axial neck 10 again. All these Arrangements are known in principle.
  • a spacer screw 16 suitably from the side of the mounting ring 29 ago to screw into a threaded bore 25 of the blade bearing ring 6.
  • the Screw 16 is preferably a stud, commonly also called worm or Grub screw is known and represents a headless screw.
  • the stud 16 has prefers a smooth surface following the screw section 26 (ie is in the Vane storage space 13 without thread) to the flow as low as possible resistance oppose.
  • the cylindrical surface of the stud 16th expedient a maximum roughness number Rz of 25, preferably of a maximum of 16, on.
  • a spacer with the desired Dimensions e.g. a piece of wood of the appropriate thickness or another body, inserted, so that so that the desired width of the blade chamber 13 is determined. Then it will this distance by soldering or (preferably) welding the screw 16 with the help a weld 30 secured, at the same time also a rotation for the screw 16 results and unintentional unscrewing from the threaded hole 25 is effectively avoided as a result of shock or vibration.
  • the out Wood or other material existing spacer can then after pre-assembly the guide grid with the vanes 7 are easily removed. Just when the guide grid is pre-assembled before it pushes it into the turbine housing 2, let easy for the attachment of the softened connection material soldering or Use welding machines, so that the inventive method cost can be carried out.
  • An additional measure to improve the flow conditions of the supply channel 9 to the rotor chamber 23 may be located in that the bolt, pin or the like. At least 16 over the the blade storage room 13 traversing length at least approximately has against the rotation axis R facing flow profile, as on hand Fig. 3 is illustrated. It is then to the circular threaded portion 26 of the screw 16 is provided an approximately drop-shaped flow profile 31, which down (relative to Figs. 2 and 3) in the direction of the axis of rotation R has. This training also facilitates the partial introduction of the weld 30 (Fig. 2) between the end portion of the bolt 16 and the inner surfaces of the receiving it Bore of the mounting ring 29. The flow profile can thereby in each case desired way to be optimized, as it is from shipbuilding or aircraft is known, for example by also the upwardly facing side of the bolt 16 more or less sharpened.
  • a stud 16 has been shown as a spacer pin, wherein the Screw slot 33 at the opposite end of the threaded portion 26 of the Screw 16 is provided.
  • the screw slot 33 are also provided at the same end.
  • one Stud 16 could also be used with a capscrew, but with it the attachment the weld 30 may be more difficult or inefficient.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
EP03024662A 2003-10-27 2003-10-27 Turbomachine et méthode de fabrication pour un anneau de guidage Expired - Fee Related EP1528225B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP03024662A EP1528225B1 (fr) 2003-10-27 2003-10-27 Turbomachine et méthode de fabrication pour un anneau de guidage
DE50304673T DE50304673D1 (de) 2003-10-27 2003-10-27 Strömungsmaschine und Verfahren zum Herstellen eines Leitgitters
JP2004281195A JP2005127321A (ja) 2003-10-27 2004-09-28 流体流れエンジン及び案内格子を製造する方法
US10/974,321 US7303370B2 (en) 2003-10-27 2004-10-27 Fluid flow engine and method of producing a guiding grid

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03024662A EP1528225B1 (fr) 2003-10-27 2003-10-27 Turbomachine et méthode de fabrication pour un anneau de guidage

Publications (2)

Publication Number Publication Date
EP1528225A1 true EP1528225A1 (fr) 2005-05-04
EP1528225B1 EP1528225B1 (fr) 2006-08-16

Family

ID=34400473

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03024662A Expired - Fee Related EP1528225B1 (fr) 2003-10-27 2003-10-27 Turbomachine et méthode de fabrication pour un anneau de guidage

Country Status (4)

Country Link
US (1) US7303370B2 (fr)
EP (1) EP1528225B1 (fr)
JP (1) JP2005127321A (fr)
DE (1) DE50304673D1 (fr)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005001864B3 (de) * 2004-12-10 2006-01-12 Dr.Ing.H.C. F. Porsche Ag Turbinengehäuse eines Abgasturboladers mit verstellbarer Turbinengeometrie
EP1676980A1 (fr) * 2004-12-28 2006-07-05 BorgWarner Inc. Turbocompresseur à géométrie variable et procédé de fabrication
EP1707755A1 (fr) * 2005-03-08 2006-10-04 Dr.Ing. h.c.F. Porsche Aktiengesellschaft Carter de turbine d'un turbocompresseur avec une turbine à géométrie variable
EP1734231A1 (fr) * 2005-06-16 2006-12-20 BorgWarner Inc. Turbocompresseur et anneau statorique pour celui-ci
WO2007093406A1 (fr) * 2006-02-16 2007-08-23 Borgwarner Inc. Ensemble bague de support d'aubes d'un turbocompresseur à géométrie de turbine variable
WO2009000436A3 (fr) * 2007-06-23 2009-02-12 Ihi Charging Systems Internat Turbocompresseur a suralimentation de gaz d'échappement pour moteur à combustion interne
WO2010040643A1 (fr) * 2008-10-09 2010-04-15 Continental Automotive Gmbh Turbocompresseur comprenant des éléments de fixation destinés à la fixation de bagues de palier d'aubes d'une turbine à géométrie variable vtg
DE102009007663A1 (de) * 2009-02-05 2010-08-12 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
CN101598037B (zh) * 2009-06-30 2011-08-31 康跃科技股份有限公司 可变喷嘴零间隙浮动调节装置
DE102012211417A1 (de) 2012-07-02 2014-01-02 Bosch Mahle Turbo Systems Gmbh & Co. Kg Leitschaufel-Anordnung für einen Abgasturbolader
DE102009009129B4 (de) 2009-02-17 2022-11-03 BMTS Technology GmbH & Co. KG Turbolader mit variabler Turbinengeometrie
EP4239164A3 (fr) * 2022-03-01 2023-09-13 Garrett Transportation I Inc. Procédé de construction d'une couronne d'aubes fixes pour une tuyère d'une turbine de turbocompresseur

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE50205914D1 (de) * 2002-08-26 2006-04-27 Borgwarner Inc Verstellbares Leitgitter für eine Turbineneinheit
DE102004038748A1 (de) * 2004-08-10 2006-02-23 Daimlerchrysler Ag Abgasturbolader für eine Brennkraftmaschine
JP4545068B2 (ja) * 2005-08-25 2010-09-15 三菱重工業株式会社 可変容量型排気ターボ過給機及び可変ノズル機構構成部材の製造方法
US7918023B2 (en) 2007-02-08 2011-04-05 Honeywell International Inc. Method for manufacturing a variable-vane mechanism for a turbocharger
US8021107B2 (en) * 2008-02-25 2011-09-20 Honeywell International Inc. Variable-nozzle assembly for a turbocharger
JP5201333B2 (ja) * 2008-03-11 2013-06-05 株式会社Ｉｈｉ 可変ノズルのベーン形状及び可変容量過給機
US8267647B2 (en) * 2008-07-09 2012-09-18 Borgwarner Inc. Variable geometry turbocharger lower vane ring retaining system
DE102008053169A1 (de) * 2008-10-24 2010-04-29 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
DE102009007390B4 (de) * 2009-02-05 2021-03-25 BMTS Technology GmbH & Co. KG Ladeeinrichtung mit einer variablen Turbinengeometrie
JP5101546B2 (ja) * 2009-02-26 2012-12-19 三菱重工業株式会社 可変容量型排気ターボ過給機
EP2510205B1 (fr) * 2009-12-07 2015-05-06 Volvo Lastvagnar AB Vis de réglage de la course d'une aube
JP5527306B2 (ja) * 2011-11-04 2014-06-18 トヨタ自動車株式会社 可変容量型ターボチャージャ
EP3234310B1 (fr) 2014-12-19 2020-08-26 Volvo Truck Corporation Turbocompresseur, et procédé pour fabriquer un turbocompresseur
DE102017207540A1 (de) * 2017-05-04 2018-11-08 Man Diesel & Turbo Se Turbolader

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3645645A (en) * 1970-10-19 1972-02-29 Garrett Corp Variable-area nozzle seal
JPS60169604A (ja) * 1984-02-15 1985-09-03 Nissan Motor Co Ltd ラジアルタ−ビン可変ノズル
US4659295A (en) * 1984-04-20 1987-04-21 The Garrett Corporation Gas seal vanes of variable nozzle turbine
EP0226444A2 (fr) * 1985-12-11 1987-06-24 AlliedSignal Inc. Turbosoufflante avec des aubes statoriques variables
US4702672A (en) * 1985-05-09 1987-10-27 Mtu Friedrichschafen Gmbh Fluid flow machine
US5207565A (en) * 1992-02-18 1993-05-04 Alliedsignal Inc. Variable geometry turbocharger with high temperature insert in turbine throat
EP1099838A1 (fr) * 1999-05-20 2001-05-16 Hitachi, Ltd. Compresseur turbine deplacement variable
EP1120546A2 (fr) * 2000-01-24 2001-08-01 Mitsubishi Heavy Industries, Ltd. Turbine avec capacité variable
US6312217B1 (en) * 1999-03-11 2001-11-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Variable capacity supercharger

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS63183207A (ja) * 1987-01-23 1988-07-28 Honda Motor Co Ltd 可変容量式タ−ビン
US5749670A (en) * 1996-04-04 1998-05-12 Dresser-Rand Company Method for fastening parts together and resulting structure
JPH10103070A (ja) * 1996-09-27 1998-04-21 Toyota Motor Corp 可変容量ターボチャージャ
JP3771765B2 (ja) * 2000-01-24 2006-04-26 三菱重工業株式会社 可変ターボチャージャ
JP2002038967A (ja) * 2000-07-27 2002-02-06 Toyota Motor Corp 可変ノズル式ターボチャージャ
DE50207509D1 (de) * 2002-09-10 2006-08-24 Borgwarner Inc Leitgitter variabler Geometrie und Turbolader mit einem solchen Leitgitter

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3645645A (en) * 1970-10-19 1972-02-29 Garrett Corp Variable-area nozzle seal
JPS60169604A (ja) * 1984-02-15 1985-09-03 Nissan Motor Co Ltd ラジアルタ−ビン可変ノズル
US4659295A (en) * 1984-04-20 1987-04-21 The Garrett Corporation Gas seal vanes of variable nozzle turbine
US4702672A (en) * 1985-05-09 1987-10-27 Mtu Friedrichschafen Gmbh Fluid flow machine
EP0226444A2 (fr) * 1985-12-11 1987-06-24 AlliedSignal Inc. Turbosoufflante avec des aubes statoriques variables
US5207565A (en) * 1992-02-18 1993-05-04 Alliedsignal Inc. Variable geometry turbocharger with high temperature insert in turbine throat
US6312217B1 (en) * 1999-03-11 2001-11-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Variable capacity supercharger
EP1099838A1 (fr) * 1999-05-20 2001-05-16 Hitachi, Ltd. Compresseur turbine deplacement variable
EP1120546A2 (fr) * 2000-01-24 2001-08-01 Mitsubishi Heavy Industries, Ltd. Turbine avec capacité variable

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 010, no. 006 (M - 445) 11 January 1986 (1986-01-11) *

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005001864B3 (de) * 2004-12-10 2006-01-12 Dr.Ing.H.C. F. Porsche Ag Turbinengehäuse eines Abgasturboladers mit verstellbarer Turbinengeometrie
EP1676980A1 (fr) * 2004-12-28 2006-07-05 BorgWarner Inc. Turbocompresseur à géométrie variable et procédé de fabrication
US7507067B2 (en) 2004-12-28 2009-03-24 Borgwarner Inc. Turbocharger of variable turbine geometry
EP1707755A1 (fr) * 2005-03-08 2006-10-04 Dr.Ing. h.c.F. Porsche Aktiengesellschaft Carter de turbine d'un turbocompresseur avec une turbine à géométrie variable
US7431560B2 (en) 2005-03-08 2008-10-07 Dr. Ing. H.C.F. Porsche Aktiengesellschaft Turbine housing of an exhaust gas turbocharger with adjustable turbine geometry
EP1734231A1 (fr) * 2005-06-16 2006-12-20 BorgWarner Inc. Turbocompresseur et anneau statorique pour celui-ci
WO2007093406A1 (fr) * 2006-02-16 2007-08-23 Borgwarner Inc. Ensemble bague de support d'aubes d'un turbocompresseur à géométrie de turbine variable
US8418460B2 (en) 2007-06-23 2013-04-16 Ihi Charging Systems International Gmbh Exhaust gas turbocharger for an internal combustion engine
WO2009000436A3 (fr) * 2007-06-23 2009-02-12 Ihi Charging Systems Internat Turbocompresseur a suralimentation de gaz d'échappement pour moteur à combustion interne
WO2010040643A1 (fr) * 2008-10-09 2010-04-15 Continental Automotive Gmbh Turbocompresseur comprenant des éléments de fixation destinés à la fixation de bagues de palier d'aubes d'une turbine à géométrie variable vtg
US8764389B2 (en) 2008-10-09 2014-07-01 Continental Automotive Gmbh Turbocharger having fastening elements for fastening vane bearing rings of a variable turbine geometry VTG
DE102009007663A1 (de) * 2009-02-05 2010-08-12 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
DE102009009129B4 (de) 2009-02-17 2022-11-03 BMTS Technology GmbH & Co. KG Turbolader mit variabler Turbinengeometrie
CN101598037B (zh) * 2009-06-30 2011-08-31 康跃科技股份有限公司 可变喷嘴零间隙浮动调节装置
DE102012211417A1 (de) 2012-07-02 2014-01-02 Bosch Mahle Turbo Systems Gmbh & Co. Kg Leitschaufel-Anordnung für einen Abgasturbolader
EP4239164A3 (fr) * 2022-03-01 2023-09-13 Garrett Transportation I Inc. Procédé de construction d'une couronne d'aubes fixes pour une tuyère d'une turbine de turbocompresseur

Also Published As

Publication number Publication date
US20050169748A1 (en) 2005-08-04
EP1528225B1 (fr) 2006-08-16
US7303370B2 (en) 2007-12-04
DE50304673D1 (de) 2006-09-28
JP2005127321A (ja) 2005-05-19

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