EP1887189A2 - Schaufelanordnung und Verfahren zur Montage einer Schaufelanordnung für einen Turbolader mit variabler Düse - Google Patents

Schaufelanordnung und Verfahren zur Montage einer Schaufelanordnung für einen Turbolader mit variabler Düse Download PDF

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Publication number
EP1887189A2
EP1887189A2 EP07113861A EP07113861A EP1887189A2 EP 1887189 A2 EP1887189 A2 EP 1887189A2 EP 07113861 A EP07113861 A EP 07113861A EP 07113861 A EP07113861 A EP 07113861A EP 1887189 A2 EP1887189 A2 EP 1887189A2
Authority
EP
European Patent Office
Prior art keywords
vane
nozzle
ring
axle
variable
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Withdrawn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
EP07113861A
Other languages
English (en)
French (fr)
Inventor
Lorrain Sausse
Emmanuel Severin
Manual Dufin
Gary Agnew
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.)
Honeywell International Inc
Original Assignee
Honeywell International 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 Honeywell International Inc filed Critical Honeywell International Inc
Publication of EP1887189A2 publication Critical patent/EP1887189A2/de
Withdrawn legal-status Critical Current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 present invention relates to turbochargers having a variable-nozzle turbine in which movable vanes are disposed in the nozzle of the turbine for regulating exhaust gas flow into the turbine.
  • An exhaust gas-driven turbocharger is a device used in conjunction with an internal combustion engine for increasing the power output of the engine by compressing the air that is delivered to the air intake of the engine to be mixed with and burned in the engine.
  • a turbocharger comprises a compressor wheel mounted on one end of a shaft in a compressor housing and a turbine wheel mounted on the other end of the shaft in a turbine housing.
  • the turbine housing is formed separately from the compressor housing, and there is yet another center housing connected between the turbine and compressor housings for containing bearings for the shaft.
  • the turbine housing defines a generally annular chamber that surrounds the turbine wheel and that receives exhaust gas from an engine.
  • the turbine assembly includes a nozzle that leads from the chamber into the turbine wheel.
  • the exhaust gas flows from the chamber through the nozzle to the turbine wheel and the turbine wheel is driven by the exhaust gas.
  • the turbine thus extracts power from the exhaust gas and drives the compressor.
  • the compressor receives ambient air through an inlet of the compressor housing and the air is compressed by the compressor wheel and is then discharged from the housing to the engine air intake.
  • variable-geometry turbocharger which includes an array of variable vanes in the turbine nozzle. The vanes are pivotally mounted in the nozzle and are connected to a mechanism that enables the setting angles of the vanes to be varied.
  • Changing the setting angles of the vanes has the effect of changing the effective flow area in the turbine nozzle, and thus the flow of exhaust gas to the turbine wheel can be regulated by controlling the vane positions. In this manner, the power output of the turbine can be regulated, which allows engine power output to be controlled to a greater extent than is generally possible with a fixed-geometry turbocharger.
  • variable vane mechanisms tend to be made up of a relatively large number of separate parts and thus are complicated and present a challenge in terms of manufacture and assembly. It would be desirable to improve upon the ease of manufacture and assembly of a variable vane mechanism.
  • a variable vane assembly for a variable-nozzle turbine having a reduced parts count and therefore reduced complexity of manufacture and assembly relative to some existing variable vane assemblies.
  • a variable vane assembly includes a fixed nozzle ring defining a plurality of circumferentially spaced apertures, and a ring of circumferentially spaced vanes each comprising an airfoil portion that extends axially from a first end proximate the nozzle ring to an opposite second end.
  • Each vane has an axle immovably connected with the first end of the airfoil portion and extending axially therefrom in a direction away from the second end, the axle defining a rotation axis of the vane.
  • the axles of the vanes are inserted in the apertures of the nozzle ring such that the axles are rotatable in the apertures.
  • An actuator ring is disposed adjacent to and concentric with the nozzle ring, the actuator ring being rotatable about an axis relative to the nozzle ring.
  • the actuator ring can concentrically surround a portion of the nozzle ring such that the actuator ring and the portion of the nozzle ring occupy the same plane.
  • the actuator ring defines a plurality of circumferentially spaced first connecting elements.
  • Each vane further includes an arm having a proximal end immovably connected with the vane proximate the first end of the airfoil portion. A distal end of the is offset from the rotation axis of the vane and defines a second connecting element configured to connect with one of the first connecting elements of the actuator ring. Insertion of the axle of each vane into one of the apertures in the nozzle ring is also effective to connect the second connecting element of the vane with one of the first connecting elements of the actuator ring, thereby connecting the arm of the vane to the actuator ring.
  • rotation of the actuator ring moves the arms and thereby causes the vanes to rotate about the rotation axes thereof for adjusting a rotational orientation of the vanes.
  • each vane and its associated axle and arm comprise an integral one-piece structure.
  • the structure can be formed by casting, by machining a single piece of starting material, by metal injection molding (MIM), or any other suitable technique.
  • MIM metal injection molding
  • variable vane mechanism has a relatively simple construction.
  • all, of the vanes are identical to one another, and therefore the entire assembly encompasses only three part configurations: (1) the nozzle ring, (2) the actuator ring, and (3) the vanes.
  • the parts count is also significantly reduced in comparison with prior vane assemblies in which the vanes and the arms are separate until the time of assembly.
  • the process of assembly is considerably simplified because there is no need to weld or otherwise attach the arms to the vanes during assembly.
  • a method for assembling a vane assembly comprises the steps of: (1) providing a nozzle ring encircling an axis, the nozzle ring having an annular surface generally perpendicular to the axis and defining a plurality of circumferentially spaced apertures extending through the annular surface; (2) assembling an actuator ring with the nozzle ring such that the actuator ring is adjacent to and concentric with the nozzle ring, the actuator ring defining a plurality of circumferentially spaced first connecting elements and being rotatable relative to the nozzle ring; (3) providing a plurality of vanes each having an airfoil portion that extends axially from a first end to an opposite second end, and an axle immovably connected with the first end of the airfoil portion and extending axially therefrom in a direction away from the second the axle defining a rotation axis of the vane, each vane further comprising an having a proximal immovably connected with
  • FIG. 1 is a perspective view of a partial assembly of a turbocharger including a variable vane assembly in accordance with an embodiment of the invention
  • FIG. 2 is an exploded view of the partial assembly of FIG. 1;
  • FIG. 3 is a perspective view of a vane with integral arm in accordance with an embodiment of the invention.
  • FIG. 4 is another perspective view of the vane
  • FIG. 5 is a perspective view of the variable vane assembly in accordance with an embodiment of the invention.
  • FIG. 6 is a perspective view of the partial assembly of FIG. 1, partly in section.
  • a partial assembly 10 of a turbocharger in accordance with an embodiment of the invention is shown in perspective view in FIG. 1, in exploded view in FIG. 2, and in a partially sectioned perspective view in FIG. 6.
  • the partial assembly includes a turbine wheel 12 mounted on one end of a shaft 14 .
  • the turbine wheel is part of a turbine that includes a turbine housing assembly surrounding the turbine wheel.
  • the turbine housing assembly includes a turbine housing 15 and an insert 16 having a generally tubular portion 18 that is inserted into a generally cylindrical bore in the turbine housing and forms a part of a flow path for exhaust gas through the turbine wheel.
  • the tubular portion 18 of the insert 16 is joined to a generally annular portion 20 that extends radially outwardly from the end of the tubular portion.
  • the annular portion 20 forms one wall of a nozzle that directs exhaust gas from a generally annular chamber defined in the turbine housing 15 radially inwardly into the turbine wheel 12 .
  • the opposite wall of the nozzle is formed in part by a generally annular cover or plate 22 that is affixed to a center housing 24 of the partial assembly 10.
  • the cover 22 has a generally cylindrical flange at its outer diameter that engages the radially outer surface of a generally cylindrical flange on the center housing.
  • the center housing houses a bearing 25 for the shaft 14 passing through the center housing.
  • the end of the shaft 14 opposite from the turbine wheel 12 is connected to a compressor wheel (not shown) driven by the turbine wheel 12.
  • the opposite wall of the nozzle from the annular portion 20 of the insert 16 is also formed in part by a nozzle ring 26.
  • the nozzle ring 26 is connected to the annular portion 20 by a plurality of spacers 28 that are spaced apart about the circumference of the nozzle ring.
  • the spacers 28 keep the nozzle ring 26 and the annular portion 20 a substantially constant axial distance apart from each other.
  • the nozzle ring 26 also engages a shroud 30 and a locator ring 31 affixed to the center housing 24 for ensuring that the nozzle ring is substantially coaxial with respect to the center housing.
  • the shroud 31 also serves as a heat shield for shielding the center housing from the hot exhaust gas passing through the turbine.
  • the nozzle ring 26 supports a plurality of adjustable vanes 32 that are disposed in the nozzle between the wall formed by the nozzle ring 26 and plate 22 and the opposite wall formed by the annular portion 20 of the insert 16.
  • the vanes 32 are circumferentially spaced apart about the circumference of the nozzle ring.
  • each vane 32 includes an airfoil portion 34 that is wetted by the exhaust gas flowing through the nozzle into the turbine wheel and acts in cooperation with adjacent vanes to determine or influence the flow direction of the exhaust gas flowing through the passages between the vanes.
  • an axle 36 is immovably connected with the airfoil portion to form an airfoil/axle assembly.
  • the nozzle ring defines a plurality of apertures 38 circumferentially spaced apart about its circumference. Each aperture 38 receives the axle 36 of one of the vanes.
  • the axles 36 are rotatable in the apertures 38 about the axes of the axles for adjusting the setting angles of the airfoil portions 34.
  • the apertures 38 extend through a generally annular surface 40 of the nozzle ring that is generally perpendicular to the central axis of the nozzle ring and that faces the annular portion 20 of the insert 16.
  • the airfoil portion 34 of each vane 32 extends axially from the proximal end of the airfoil portion adjacent the annular surface 40 to an opposite distal end.
  • the distal end of the airfoil portion 34 can be a free end as shown, or alternatively the distal end can include an axle engaging an aperture in the annular portion 20 of the insert 16 .
  • the proximal ends of the airfoil portions 34 advantageously are closely adjacent the annular surface 40 of the nozzle ring 26 and the distal ends of the airfoil portions 34 advantageously are closely adjacent the annular portion 20 so the exhaust gas flowing through the nozzle is substantially prevented from leaking between the ends of the airfoil portions and the adjacent walls of the nozzle.
  • Each vane 32 further includes an arm 42 immovably connected with the airfoil/axle assembly.
  • the arm 42 is connected at a location intermediate the distal end of the airfoil portion 34 and the distal end of the axle 36, contrary to prior-art vanes in which the arm is connected to the distal end of the axle.
  • the arm advantageously is connected proximate the proximal end of the airfoil portion 34.
  • the arm 42 extends perpendicular to the axis of the axle 36 and terminates in a distal end 44.
  • the distal end includes a projection 46 that extends axially away from the proximal end of the airfoil portion 34, in the same direction as the axle 36.
  • the vane 32 with its associated axle 36 and arm 42 is a one-piece integral structure.
  • the structure can be formed by manufacturing the airfoil portion 34 and axle 36 together as a single part (e.g., by casting or machining), manufacturing the arm 42 as a separate part, and then joining the two parts together by welding or the like.
  • the entire vane structure can be formed as a single part by casting, by machining, by metal injection molding (MIM), or by any other suitable technique.
  • variable vane assembly is illustrated in isolation, forming a portion of the partial assembly 10 depicted in FIGS. I and 2.
  • the variable vane assembly includes the nozzle ring 26, the vanes 32, and an actuator ring 48.
  • the actuator ring surrounds the portion of the nozzle ring 26 having the apertures 38 for the vane axles. More particularly, the nozzle ring 26 is of a stepped configuration having a larger-diameter portion joined to a smaller-diameter portion.
  • the actuator ring surrounds the smaller-diameter portion, and the iarger-diarneter portion is disposed axially adjacent the actuator ring.
  • the actuator ring is rotatable about the axis of the nozzle ring.
  • the actuator ring engages the arms 42 of the vanes 32 such that rotation of the actuator ring causes the vanes to be rotated about the axes of the axles 36.
  • the actuator ring 48 and the vane arms 42 are on the front or "flow" side of the nozzle ring 26 .
  • each vane arm 42 defines a connecting element that connects with a cooperative connecting element defined by the actuator ring 48 .
  • the connecting of the actuator ring 48 comprise receptacles 50 defined in the actuator ring
  • the connecting elements of the vane arms comprise the projections 46 that are received in the receptacles 50 .
  • the actuator ring could define projections received in receptacles defined in the vane arms, or the connection between the vane arms and actuator ring could be accomplished in another way.
  • variable vane assembly is configured to ease the assembly of the parts.
  • the actuator ring 48 is assembled to the nozzle ring 26 and is rotatably positioned with respect to the nozzle ring so that a receptacle 50 is generally aligned with each aperture 38 in the nozzle ring.
  • the axles 36 of the vanes are inserted into the apertures 38 in the nozzle ring in such an orientation that the projections 46 on the vane arms 42 are received in the receptacles 50.
  • Each aperture 38 in the nozzle ring has a relatively small-diameter portion that receives one of the axles 36 and forms a bearing surface therefor, and a relatively larger-diameter countersunk portion surrounding the small-diameter portion at the annular surface 40 of the nozzle ring.
  • a lengthwise portion of the arm 42 of each vane adjacent the proximal end of the arm is accommodated in the countersunk portion of the respective aperture.
  • the one-piece vanes and the arrangement for connecting the vane arms with the actuator ring in accordance with the invention avoid the need for welding of vane parts during assembly. This is in contrast to some prior variable vane assemblies in which each vane is formed in two separate parts that must be welded together during the assembly process.
  • the actuator ring defines a recess or slot 52 (FIG. 5) for receiving a tab 54 on a crank arm 56 disposed on one side of the center housing 24, on the opposite side of the nozzle ring 26 from the actuator ring 48 .
  • the crank arm 56 is immovably connected with a shaft 58 of another crank arm 60 disposed on the opposite side of the center housing 24.
  • the shaft 58 extends through a bushing 62 that passes through the center housing 24, and the end of the shaft 58 is immovably connected with the crank arm 56.
  • the crank arm 60 is rotated by an actuator (not shown), which causes the crank arm 56 to be rotated such that the tab 54 rotates the actuator ring 48. In this manner, the setting angles of the vanes 32 can be adjusted to any desired angle for regulating the exhaust gas flow into the turbine wheel 12.
  • the actuator ring 48 has receptacles 50 for the vane arms 42 that are formed by recesses in the radially inner surface of the actuator ring.
  • the receptacles it is possible for the receptacles to be formed by recesses in the radially outer surface of the actuator ring.
  • the cover 22 also defines recesses 23 (FIG. 1) to accommodate the vane arms 42.
  • the recesses 23 are circumferentially elongated to accommodate the extent of the circumferential movement of the vane arms 42.
  • the apertures 38 in the nozzle ring that form bearing surfaces for the vane axles 36 can be either blind holes or can extend entirely through the nozzle ring to its back side.
  • Blind holes offer the advantage that exhaust gas cannot leak through the holes to the back side of the nozzle ring, but the length of the bearing surfaces cannot be as great with blind holes as it can be with through holes unless the axial thickness of the nozzle ring is increased.
  • the vane arms 42 are connected to the axles 36 adjacent the proximal ends of the airfoil portions 34, and hence the arms 42 do not project into the stream of exhaust gas flowing through the nozzle, or at least the extent of their projection into the stream is minimal.
  • the arms 42 could attach to the airfoil portions 34 , although this is not preferred because the arms would be in the exhaust gas stream and thus would cause aerodynamic losses that would impair the efficiency of the turbine.
  • a vane assembly includes vanes each having an axle and an arm immovably connected with the vane prior to assembling the vane assembly.
  • the vane, axle, and arm can be an integral one-piece structure formed by casting, machining, or metal injection molding.
  • the axles engage apertures in a nozzle ring and are rotatable in the apertures about axes of the vanes.
  • An actuator ring is assembled with the nozzle ring and is rotatable relative thereto.
  • the actuator ring defines connecting elements that connect with cooperative connecting elements on the vane arms. Rotation of the actuator ring causes the vanes to rotate for adjusting the angles of the vanes. During assembly, the motion of inserting the axles into the apertures is also effective for placing the arms in position for connection with the actuator ring.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)
EP07113861A 2006-08-07 2007-08-06 Schaufelanordnung und Verfahren zur Montage einer Schaufelanordnung für einen Turbolader mit variabler Düse Withdrawn EP1887189A2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/462,785 US20080031728A1 (en) 2006-08-07 2006-08-07 Vane assembly and method of assembling a vane assembly for a variable-nozzle turbocharger

Publications (1)

Publication Number Publication Date
EP1887189A2 true EP1887189A2 (de) 2008-02-13

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EP07113861A Withdrawn EP1887189A2 (de) 2006-08-07 2007-08-06 Schaufelanordnung und Verfahren zur Montage einer Schaufelanordnung für einen Turbolader mit variabler Düse

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US (1) US20080031728A1 (de)
EP (1) EP1887189A2 (de)
CN (1) CN101173614A (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008058509A1 (de) 2008-11-21 2010-05-27 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
DE102008060850A1 (de) 2008-12-06 2010-06-10 Bosch Mahle Turbo Systems Gmbh & Co. Kg Variable Turbinengeometrie, Schaufellagerscheibe und Ladeeinrichtung
WO2013010817A1 (de) * 2011-07-21 2013-01-24 Bosch Mahle Turbo Systems Gmbh & Co. Kg Variable turbinengeometrie
EP2180159A4 (de) * 2007-12-14 2015-06-03 Mitsubishi Heavy Ind Ltd Mechanismus für verstellbare düse

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EP1816317B1 (de) * 2006-02-02 2013-06-12 IHI Corporation Turbolader mit variabler Geometrie
EP1984601B1 (de) * 2006-02-16 2015-11-18 BorgWarner, Inc. Turbolader mit verstellbaren leitschaufeln, schaufelhebel und verstellring dafür
US7918023B2 (en) * 2007-02-08 2011-04-05 Honeywell International Inc. Method for manufacturing a variable-vane mechanism for a turbocharger
US7980816B2 (en) * 2007-08-27 2011-07-19 Honeywell International Inc. Retainer for a turbocharger
DE102008007670B4 (de) * 2008-02-06 2021-01-07 BMTS Technology GmbH & Co. KG Steuerring für VTG
KR101021658B1 (ko) * 2008-08-12 2011-03-17 (주)계양정밀 가변노즐장치를 구비한 터보차져
GB0822474D0 (en) * 2008-12-10 2009-01-14 Cummins Turbo Tech Ltd Variable geometry turbine nozzle ring
JP4759062B2 (ja) * 2009-01-15 2011-08-31 トヨタ自動車株式会社 ターボチャージャおよびターボチャージャの製造方法
US8231326B2 (en) * 2009-03-31 2012-07-31 Nuovo Pignone S.P.A. Nozzle adjusting mechanism and method
IT1401665B1 (it) * 2010-08-31 2013-08-02 Nuova Pignone S R L Sistema di azionamento per turbomacchina e metodo.
GB2483995B (en) * 2010-09-22 2016-12-07 Cummins Ltd Variable geometry turbine
CN102003271A (zh) * 2010-12-08 2011-04-06 无锡明珠增压器制造有限公司 可变截面的涡轮增压器
US9506371B2 (en) * 2011-08-08 2016-11-29 Borgwarner Inc. Turbocharger
CN102297016B (zh) 2011-08-15 2012-12-12 无锡凯迪增压器配件有限公司 双叶片喷嘴***的涡轮增压器
US8967956B2 (en) * 2011-09-26 2015-03-03 Honeywell International Inc. Turbocharger variable-nozzle assembly with vane sealing arrangement
US8985943B2 (en) * 2011-09-30 2015-03-24 Honeywell International Inc. Turbocharger variable-nozzle assembly with vane sealing arrangement
CN102383872A (zh) * 2011-10-18 2012-03-21 湖南天雁机械有限责任公司 带限位销的涡轮增压器可变喷嘴
WO2013163015A1 (en) * 2012-04-27 2013-10-31 Borgwarner Inc. Exhaust-gas turbocharger
EP2861834B1 (de) 2012-06-19 2021-04-14 Volvo Lastvagnar AB Vorrichtung zur steuerung eines gasflusses, abgasnachbehandlungssystem und system zum antreiben eines fahrzeugs
CN103147846B (zh) * 2013-03-12 2015-10-21 汉美综合科技（常州）有限公司 用于涡轮增压器的可调式喷嘴
US10018107B2 (en) * 2015-07-10 2018-07-10 Kangyue Technology Co., Ltd Balanced vanes and integrated actuation system for a variable geometry turbocharger
US20190063254A1 (en) * 2017-08-31 2019-02-28 GM Global Technology Operations LLC Turbocharger utilizing variable-camber turbine guide vane system
US10619508B2 (en) 2017-11-03 2020-04-14 Borgwarner, Inc. Variable turbine geometry vane lever
CN108167031A (zh) * 2018-03-06 2018-06-15 哈尔滨广瀚燃气轮机有限公司 一种燃气轮机用可转导叶执行机构
CN108506051A (zh) * 2018-04-19 2018-09-07 萍乡德博科技股份有限公司 可变截面增压器喷嘴环

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EP1234950B1 (de) * 2001-02-26 2006-01-18 Mitsubishi Heavy Industries, Ltd. Leitschaufelverstellmechanismus für eine Turbine und Herstellungsverfahren dafür
DE10209484B4 (de) * 2002-03-05 2004-06-24 Borgwarner Turbo Systems Gmbh Turbolader für Fahrzeuge mit verbesserter Aufhängung für den Betätigungsmechanismus der variablen Düsen
US6709232B1 (en) * 2002-09-05 2004-03-23 Honeywell International Inc. Cambered vane for use in turbochargers
US7137778B2 (en) * 2004-04-12 2006-11-21 Borgwarner Inc. Variable turbine geometry turbocharger

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2180159A4 (de) * 2007-12-14 2015-06-03 Mitsubishi Heavy Ind Ltd Mechanismus für verstellbare düse
DE102008058509A1 (de) 2008-11-21 2010-05-27 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
DE102008060850A1 (de) 2008-12-06 2010-06-10 Bosch Mahle Turbo Systems Gmbh & Co. Kg Variable Turbinengeometrie, Schaufellagerscheibe und Ladeeinrichtung
WO2013010817A1 (de) * 2011-07-21 2013-01-24 Bosch Mahle Turbo Systems Gmbh & Co. Kg Variable turbinengeometrie

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US20080031728A1 (en) 2008-02-07
CN101173614A (zh) 2008-05-07

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