WO2001069045A1 - Turbocompresseur a geometrie variable - Google Patents

Turbocompresseur a geometrie variable Download PDF

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Publication number
WO2001069045A1
WO2001069045A1 PCT/US2000/006512 US0006512W WO0169045A1 WO 2001069045 A1 WO2001069045 A1 WO 2001069045A1 US 0006512 W US0006512 W US 0006512W WO 0169045 A1 WO0169045 A1 WO 0169045A1
Authority
WO
WIPO (PCT)
Prior art keywords
vanes
unison ring
crank shaft
piston
port
Prior art date
Application number
PCT/US2000/006512
Other languages
English (en)
Inventor
Steven Don Arnold
Voytek Kanigowski
Kevin Slupski
Steven P. Martin
Original Assignee
Alliedsignal 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 Alliedsignal Inc. filed Critical Alliedsignal Inc.
Priority to DE1264078T priority Critical patent/DE1264078T1/de
Priority to JP2001567905A priority patent/JP4460814B2/ja
Priority to KR1020017004407A priority patent/KR100642050B1/ko
Priority to CNB008193304A priority patent/CN1313711C/zh
Priority to AT00917890T priority patent/ATE313007T1/de
Priority to DE60024879T priority patent/DE60024879T2/de
Priority to BR0006983A priority patent/BR0006983B1/pt
Priority to EP00917890A priority patent/EP1264078B1/fr
Priority to AU38796/00A priority patent/AU758433B2/en
Priority to CA002349917A priority patent/CA2349917C/fr
Priority to PCT/US2000/006512 priority patent/WO2001069045A1/fr
Publication of WO2001069045A1 publication Critical patent/WO2001069045A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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

  • This invention relates generally to the field of turbochargers having variable turbine inlet geometries. More particularly, the present invention provides a simplified structural arrangement for positioning multiple aerodynamic vanes in the inlet nozzle of the turbine housing and an integrated actuator for control of the vane position.
  • variable nozzles In a turbocharger it is often desirable to control the flow of exhaust gas into the turbine to improve the efficiency or operational range.
  • Various configurations of variable nozzles have been employed to control the exhaust gas flow.
  • Multiple pivoting vanes annularly positioned around the turbine inlet and commonly controlled to alter the throat area of the passages between the vanes is an approach which has been successfully used in prior turbochargers.
  • Various approaches to this method for implementing a variable nozzle are disclosed in US Patent numbers 4,679,984 to Swihart et al. entitled “Actuation System for Variable Nozzle Turbine” and 4,804,316 to Fleury entitled “Suspension for the Pivoting Vane Actuation Mechanism of a Variable Nozzle Turbocharger” having a common assignee with the present application.
  • a variable geometry turbocharger employing the present invention includes a turbine housing having a standard inlet for exhaust gas and an outlet to the exhaust system of the engine.
  • a volute is connected to the inlet and an integral outer nozzle wall is incorporated in the turbine housing casting adjacent the volute.
  • a center housing is attached to the turbine housing .
  • a center bore in the center housing carries a bearing assembly.
  • a compressor housing having an air inlet and a compressed air outlet is attached to the center housing.
  • a turbine wheel is carried within the turbine housing and attached to a shaft extending through the center housing, supported by the bearing assembly.
  • the shaft attached to a compressor impeller carried within the compressor housing.
  • a plurality of vanes having rotation posts extending from a first surface substantially parallel to the outer nozzle wall provide the variable nozzle.
  • the posts are received in circumferentially spaced apertures in the outer nozzle wall.
  • the vanes further have actuation tabs extending from the opposite surface of the vanes.
  • a unison ring is engaged between the center housing and the vanes and has a plurality of profiled slots equal in number to the vanes.
  • the slots are oriented obliquely to a circumference of the unison ring and receive the tabs.
  • the profiled surfaces of the slots engage the substantially flat sides of the tabs on different surfaces during the translation to provide optimum control and wear reduction.
  • Actuation of the unison ring is accomplished by a radial slot and a crank shaft having a pin engaging the radial slot.
  • the crank shaft is movable continuously from a first position to a second position, causing the pin to translate in the radial slot and impart force perpendicular to the radial slot to urge rotational motion of the unison ring.
  • the rotational motion of the unison ring causes the tabs to traverse the actuation slots from a first end of the slots to a second end of the slots.
  • the oblique orientation of the slots causes a continuously variable rotation of the vanes from a first open position to a second closed position.
  • An integral hydraulic actuator provides the actuation mechanism for the crank shaft.
  • the actuator uses a piston and piston rod attached by a rack and pinion to the crank shaft for position control of the vanes.
  • Hydraulic pressure to operate the piston is provided by a solenoid operated multiport valve with direct feedback through a cam mounted on the crank shaft adjacent the pinion gear.
  • Fig. 1 is an exploded view of an embodiment of a turbocharger employing the present invention
  • Fig. 2 is a side section elevation showing the turbine housing, center housing and compressor back plate with the turbine shaft wheel assembly and compressor impeller as supported by the bearing system
  • Fig. 3 is an end section elevation through the center housing showing an embodiment of an integral actuation valve arrangement according to the invention
  • Fig. 4 is a partial view of an alternate embodiment of the valve piston arrangment
  • Fig. 5a is a view along line G-G of Fig. 3 and with Figs. 5b-c provides section views of the crank shaft assembly extending from the actuation valve to the unison ring engaging the nozzle vanes;
  • Figs 6 a-e are end views of the unison ring and nozzle vanes demonstrating the variable vane positions and the actuation structural arrangement;
  • Fig. 7 is a reverse end view of an alternative embodiment of the unison ring showing a blind relief design for pressure compensation
  • Fig. 8 is a schematic side view of the unison ring of Fig. 7 and vanes as mounted in the turbine housing to demonstrate the pressure compensation for vane tolerance control;
  • Figs. 9a-e are schematic side views of the actuation valve porting and piston structure for control of the vane position.
  • Fig. 1 the embodiment of the invention shown in Fig. 1 includes a compressor housing 10 which is connected to a backplate 12 using two or more clamps 14 secured by bolts 16.
  • the backplate is attached to a center housing 18 with multiple bolts 20 and a seal ring 22.
  • a turbine housing 24 is connected to the center housing using multiple clamps 26 secured by bolts 28.
  • a turbine wheel and shaft assembly 30 is carried within the turbine housing.
  • Exhaust gas or other high energy gas supplying the turbocharger enters the turbine housing through inlet 32 and is distributed through the volute in the turbine housing for substantially radial entry into the turbine wheel through a circumferential nozzle entry 34.
  • vanes 36 are mounted to a nozzle wall 38 machined into the turbine housing using posts 40 extending from the vanes for rotational engagement within holes 42 in the nozzle wall.
  • Actuation tabs 44 extend from the vanes to be engaged by slots 46 in unison ring 48 which acts as the second nozzle wall. The configuration of the tabs, slots and unison ring will be explained in greater detail subsequently.
  • An actuator crank 50 terminates at a first end in a lever arm 52 carrying a pin 54 to engage elliptical slot 56 in the unison ring for rotation of the ring as will be later explained.
  • the crank extends into a boss 58 in the center housing casting through a bushing 60 and a gear 62 which is secured to the crank by a pin 64 and is received into an end bearing 66 which mates with aperture 68 in the crank boss.
  • An O-ring 70 seals the end bearing and a snap ring 72 secures the end bearing into the aperture 68.
  • a bearing system having two journal bearings 74 and a bearing spacer 76 support the shaft wheel assembly in the center housing center bore 78.
  • the shaft further extends through a thrust collar 80 which engages a thrust bearing 82 carried between the center housing and compressor back plate.
  • a piston ring 84 seals the thrust collar with the shaft bore in the back plate.
  • the stack up of the shaft wheel assembly within the turbine housing, center housing and back plate is best seen in Fig. 2.
  • the unison ring and vanes are not shown for clarity.
  • the compressor impeller 86 is attached to the shaft wheel assembly. Referring again to Fig. 1 , the integrated actuator for the turbocharger is housed in an actuator boss 82 in the casting of the center housing 18.
  • a solenoid valve 84 is mounted in an aperture at one end of the boss while the actuating components are mounted in a second aperture at the opposite end of the boss.
  • the actuating components include a piston 86 that incorporates a rod 88 having a rack gear 90 engaging the gear 62 mounted on the crank shaft 50.
  • a ring seal 92 surrounds the piston circumference sealing the piston in the bore of the actuator boss. Additional ring seals 94 and 96 seal the piston rod to a rod bore of smaller diameter than the piston bore.
  • the piston bore is sealed with a piston end 98 held in the bore with a snap ring 100.
  • a bolt 102 is inserted into a threaded hole in the piston end for use in manipulating the piston end.
  • An additional ring seal 104 seals the piston end to the bore.
  • a freeze plug 106 is employed as a replacement for the piston end.
  • the solenoid valve is secured to the boss with a bracket 108 held by a bolt 110.
  • Bore plugs 112 and 114 seal the blind ends of actuation passages in the actuator boss while steel balls 116 are employed to seal other actuation passages, described in greater detail subsequently.
  • Fig. 2 is a side sectional elevation of the turbocharger showing the assembled turbine housing, center housing and compressor back plate with the turbine shaft wheel assembly and compressor impeller supported by the bearing assembly.
  • Fig. 3 is an end sectional view through the actuator boss and assembled actuator components.
  • Fig. 4 shows the alternative freeze plug arrangement for sealing the piston bore.
  • the center housing includes a main casting portion and a turbine housing back plate 120 for attachment of the center housing to the turbine housing using bolts, as previously described.
  • Fig. 5a is a sectional view showing the crank shaft assembly with the gear 62 bushing 60 mounted in the main casting portion of the center housing with the crank shaft extending across the air gap between the main casting portion and the turbine housing back plate and into an aperture in the back plate.
  • Fig. 5b shows the details of the crank shaft sealing arrangement in the back plate aperture.
  • a first metalic ring seal 122 having a first diameter is employed to seal an inner diameter of the aperture 124, while a second metalic ring seal 126 is employed in combination with the first seal to seal a second larger diameter 128 of the aperture.
  • This arrangement allows continued sealing during uneven thermal expansion of the main casting portion and the back plate during operation.
  • Fig. 5b demonstrates the configuration during operation, with the temperature of the back plate exceed the main portion, with resulting greater expansion while Fig. 5c, shows the arrangement with nominal tolerance at a common temperature for the main casting portion and the back plate.
  • nozzle vanes36 in the turbine inlet nozzle are operated by the unison ring 48.
  • Fig. 6a shows the unison ring engaged by the end pin 54 of the crank shaft 50 in a radial slot 130. Rotation of the crank shaft causes the offset end pin to traverse the radial slot resulting in rotation of the unison ring.
  • the vanes, mounted for rotation on pins 40 which extend into receiving holes 42 in the nozzle wall of the turbine housing, have guide tabs 132 which are received in the slots 46 in the unison ring.
  • Fig. 6b shows in phantom the fully open, neutral and fully closed positions of the vanes with tab positioning in the slots.
  • Fig. 6c is an enlarged view of the unison ring slot with the tab shown in multiple positions.
  • the tab incorporates substantially flat sides 134 and 136 which provide extended engagement of the slot wall by the tab to reduce point wear on the tab.
  • the profile of the slot is predetermined to provide maximum engagement with the tab, while engaging first side 134 of the tab at the open and closed end points with maximum area and the second side 136 during the intermediate positioning of the vanes.
  • Fig. 6d shows the fully open and fully closed positions of the vanes.
  • a 22 degree rotation of the vanes is provided.
  • Table 1 shows the related leading edge, trailing edge and throat size in mm for the open, mid and closed positions of the vanes.
  • Fig. 7 shows one embodiment of the unison ring 48 that incorporates blind slots 46 while providing a blind relief 138 on the reverse side of the ring with pressure ports 140 machined into the relief.
  • Fig. 8 is a detail side section of the relieved unison ring engaging the vanes in the nozzle.
  • pressure of the exhaust gas entering the nozzle pressurizes the relieved back portion 138 of the unison ring through gap 142 provided by tolerancing of the mounting channel 144 in the back plate 120, through ports 140.
  • a feed hole 146 is provided through the back plate into the unison ring mounting channel proximate the location of the ports 144.
  • Total pressure of the exhaust gas urges the unison ring against the vanes, which are in turn urged against the nozzle surface 38 in the turbine housing.
  • Holes 42 receiving the vane pins 40 are provided with sufficient depth to allow the vanes to be maintained in close contact with the nozzle surface and unison ring for minimum vane leakage.
  • Figs. 9a through 9e show the various states of the actuation piston 86 and its piston rod 88 driving gear 62 through rack 90.
  • the solenoid valve is reacted by a spring 150 having a cap 152 engaging a cam 154 machined into the gear body.
  • Various ports, as will be described are then opened and closed, hydraulically positioning the piston which, through the mechanical closed loop of the rack and gear provides positive control on the position of the crank shaft and, therefore, the unison ring.
  • the solenoid valve is a proportional servo 4-way hydraulic actuator control valve.
  • Fig. 9a if no current is applied to the solenoid, port A is open, port B (top of the piston) is connected to drain port D.
  • Fig. 9b when oil pressure is applied from the engine on which the turbocharger is mounted, oil pressure is directed through port A into the bottom of the piston, placing the vanes in a fully open position.
  • port A is closed, port A (bottom of the piston) is connected to drain, port B opens and oil pressure is directed to the top of the piston, moving the piston to the left starting to close the vanes.
  • Fig. 9c shows the condition of the actuation systems with a balanced state low current in the solenoid.
  • Port A is closed, port B is closed and the vanes are positioned as a function of the applied current.
  • Fig. 9d shows that port B is opened directing oil pressure to the top of the piston.
  • Port A is connected to the drain and the piston moves to the left, moving the vanes in the closed direction.
  • the system stabilizes in a balanced state with high current as shown in Fig. 5e with port A closed, port B closed and the vanes positioned as a function of the applied current.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
  • Preparation Of Compounds By Using Micro-Organisms (AREA)

Abstract

L'invention concerne un turbocompresseur à géométrie variable, utilisant plusieurs ailettes (36) placées dans une entrée de turbine dotée d'un anneau de conjugaison (48), et une paroi coulée d'une seule pièce dans le logement de turbine formant des parois de buse. L'anneau de conjugaison comprend des fentes d'actionnement (46) qui reçoivent des languettes (44) disposées sur les ailettes (36), de façon à ouvrir la zone de buse lors de la rotation dudit anneau de conjugaison (48). Un actionneur électrohydraulique d'une seule pièce fait tourner l'anneau de conjugaison (48) entraîné par un arbre manivelle à crémaillère, avec rétroaction de position directe vers le solénoïde à courant variable sous charge de ressort via une came sur l'arbre manivelle.
PCT/US2000/006512 2000-03-13 2000-03-13 Turbocompresseur a geometrie variable WO2001069045A1 (fr)

Priority Applications (11)

Application Number Priority Date Filing Date Title
DE1264078T DE1264078T1 (de) 2000-03-13 2000-03-13 Turbolader mit verstellbaren leitschaufeln
JP2001567905A JP4460814B2 (ja) 2000-03-13 2000-03-13 可変形状ターボチャージャ
KR1020017004407A KR100642050B1 (ko) 2000-03-13 2000-03-13 가변 형상 터보 과급기
CNB008193304A CN1313711C (zh) 2000-03-13 2000-03-13 可变几何尺寸的涡轮增压器
AT00917890T ATE313007T1 (de) 2000-03-13 2000-03-13 Turbolader mit verstellbaren leitschaufeln
DE60024879T DE60024879T2 (de) 2000-03-13 2000-03-13 Turbolader mit verstellbaren leitschaufeln
BR0006983A BR0006983B1 (pt) 2000-03-13 2000-03-13 sistema para posicionamento de palhetas aerodinÂmicas do bocal de uma turbina.
EP00917890A EP1264078B1 (fr) 2000-03-13 2000-03-13 Turbocompresseur a geometrie variable
AU38796/00A AU758433B2 (en) 2000-03-13 2000-03-13 Variable geometry turbocharger
CA002349917A CA2349917C (fr) 2000-03-13 2000-03-13 Turbocompresseur a geometrie variable
PCT/US2000/006512 WO2001069045A1 (fr) 2000-03-13 2000-03-13 Turbocompresseur a geometrie variable

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2000/006512 WO2001069045A1 (fr) 2000-03-13 2000-03-13 Turbocompresseur a geometrie variable

Publications (1)

Publication Number Publication Date
WO2001069045A1 true WO2001069045A1 (fr) 2001-09-20

Family

ID=21741144

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2000/006512 WO2001069045A1 (fr) 2000-03-13 2000-03-13 Turbocompresseur a geometrie variable

Country Status (9)

Country Link
EP (1) EP1264078B1 (fr)
JP (1) JP4460814B2 (fr)
KR (1) KR100642050B1 (fr)
CN (1) CN1313711C (fr)
AT (1) ATE313007T1 (fr)
AU (1) AU758433B2 (fr)
CA (1) CA2349917C (fr)
DE (2) DE1264078T1 (fr)
WO (1) WO2001069045A1 (fr)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004022925A1 (fr) * 2002-08-16 2004-03-18 Borgwarner Turbo Systems Gmbh Turbocompresseur a gaz d'echappement pour moteur a combustion interne
EP1420152A2 (fr) * 2002-11-18 2004-05-19 BorgWarner Turbo Systems GmbH Turbosoufflante
WO2005088100A2 (fr) * 2004-03-08 2005-09-22 Honeywell International Inc. Commande de vannes
DE102004023214A1 (de) * 2004-05-11 2005-12-08 Volkswagen Ag Abgasturbolader für eine Brennkraftmaschine mit variabler Turbinengeometrie
EP1674668A2 (fr) 2004-12-24 2006-06-28 Toyota Jidosha Kabushiki Kaisha Turbocompresseur à géométrie variable
US7958730B2 (en) 2005-12-30 2011-06-14 Honeywell International Inc. Control of dual stage turbocharging
US8186158B2 (en) 2006-09-29 2012-05-29 Komatsu Ltd. Variable turbo supercharger and method of driving the same
US8202038B2 (en) 2006-09-29 2012-06-19 Komatsu Ltd. Variable turbo supercharger and method of driving the same
CN101529064B (zh) * 2006-10-27 2012-12-12 株式会社小松制作所 可变涡轮增压机和从液压驱动装置回油的方法
US9909456B2 (en) 2012-11-16 2018-03-06 Abb Turbo Systems Ag Nozzle ring
US10018107B2 (en) 2015-07-10 2018-07-10 Kangyue Technology Co., Ltd Balanced vanes and integrated actuation system for a variable geometry turbocharger
US10940954B2 (en) 2015-09-17 2021-03-09 Israel Aerospace Industries Ltd. Multistage turbocharging system for providing constant original critical altitude pressure input to high pressure stage turbocharger

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JP4560468B2 (ja) * 2005-10-04 2010-10-13 株式会社小松製作所 可変ターボ過給機およびこれを備えたエンジン
US8784076B2 (en) * 2006-03-14 2014-07-22 Borgwarner Inc. Disk spring for a turbocharger
US7559199B2 (en) * 2006-09-22 2009-07-14 Honeywell International Inc. Variable-nozzle cartridge for a turbocharger
JP4780666B2 (ja) * 2006-11-29 2011-09-28 株式会社小松製作所 シルティング防止制御装置および方法
JP4820765B2 (ja) * 2007-01-31 2011-11-24 株式会社小松製作所 可変ターボ過給機
JP5095458B2 (ja) 2008-03-21 2012-12-12 株式会社小松製作所 油圧サーボ駆動装置、およびこれを用いた可変ターボ過給機
JP2009299767A (ja) * 2008-06-12 2009-12-24 Komatsu Ltd 油圧サーボ駆動装置
KR20110094093A (ko) * 2008-12-11 2011-08-19 보르그워너 인코퍼레이티드 가변 노즐을 구비한 간단한 가변 기하형상 터보차저
CN101539034B (zh) * 2009-04-16 2010-12-08 上海交通大学 周向弯角可调式静叶机构
CN101634233B (zh) * 2009-08-20 2011-07-20 康跃科技股份有限公司 可变几何涡轮增压器的气动喷嘴
DE102009057664A1 (de) * 2009-12-09 2011-06-16 Ihi Charging Systems International Gmbh Verstelleinrichtung für eine Aufladeeinrichtung, insbesondere für einen Abgasturbolader
US20120023936A1 (en) * 2010-07-30 2012-02-02 Caterpillar Inc. Nozzled turbocharger turbine
GB2483995B (en) * 2010-09-22 2016-12-07 Cummins Ltd Variable geometry turbine
CN102297016B (zh) * 2011-08-15 2012-12-12 无锡凯迪增压器配件有限公司 双叶片喷嘴系统的涡轮增压器
US9429033B2 (en) * 2013-11-08 2016-08-30 Honeywell International Inc. Drive arrangement for a unison ring of a variable-vane assembly
WO2016048678A1 (fr) * 2014-09-23 2016-03-31 Borgwarner Inc. Turbocompresseur avec actionneur intégré
CN110608091A (zh) * 2018-06-14 2019-12-24 博格华纳公司 用于具有可变调节机构的压缩机的装置

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US4654941A (en) * 1984-04-20 1987-04-07 The Garrett Corporation Method of assembling a variable nozzle turbocharger
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GB731822A (en) * 1952-03-14 1955-06-15 Power Jets Res & Dev Ltd Improvements relating to turbines or compressors for operation with gaseous fluids
US4502836A (en) * 1982-07-02 1985-03-05 Swearingen Judson S Method for nozzle clamping force control
US4679984A (en) 1985-12-11 1987-07-14 The Garrett Corporation Actuation system for variable nozzle turbine
US4804316A (en) 1985-12-11 1989-02-14 Allied-Signal Inc. Suspension for the pivoting vane actuation mechanism of a variable nozzle turbocharger

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004022925A1 (fr) * 2002-08-16 2004-03-18 Borgwarner Turbo Systems Gmbh Turbocompresseur a gaz d'echappement pour moteur a combustion interne
EP1420152A2 (fr) * 2002-11-18 2004-05-19 BorgWarner Turbo Systems GmbH Turbosoufflante
EP1420152A3 (fr) * 2002-11-18 2006-07-19 BorgWarner Turbo Systems GmbH Turbosoufflante
WO2005088100A2 (fr) * 2004-03-08 2005-09-22 Honeywell International Inc. Commande de vannes
WO2005088100A3 (fr) * 2004-03-08 2005-12-01 Honeywell Int Inc Commande de vannes
US7426829B2 (en) 2004-03-08 2008-09-23 Honeywell Vane control
DE102004023214A1 (de) * 2004-05-11 2005-12-08 Volkswagen Ag Abgasturbolader für eine Brennkraftmaschine mit variabler Turbinengeometrie
EP1674668B1 (fr) 2004-12-24 2015-10-14 Toyota Jidosha Kabushiki Kaisha Turbocompresseur à géométrie variable
EP1674668A2 (fr) 2004-12-24 2006-06-28 Toyota Jidosha Kabushiki Kaisha Turbocompresseur à géométrie variable
EP1674668A3 (fr) * 2004-12-24 2012-03-07 Toyota Jidosha Kabushiki Kaisha Turbocompresseur à géométrie variable
US7958730B2 (en) 2005-12-30 2011-06-14 Honeywell International Inc. Control of dual stage turbocharging
US8202038B2 (en) 2006-09-29 2012-06-19 Komatsu Ltd. Variable turbo supercharger and method of driving the same
US8186158B2 (en) 2006-09-29 2012-05-29 Komatsu Ltd. Variable turbo supercharger and method of driving the same
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CN1451076A (zh) 2003-10-22
CA2349917A1 (fr) 2001-09-13
ATE313007T1 (de) 2005-12-15
JP2003527522A (ja) 2003-09-16
KR20020081047A (ko) 2002-10-26
EP1264078B1 (fr) 2005-12-14
EP1264078A1 (fr) 2002-12-11
AU758433B2 (en) 2003-03-20
CN1313711C (zh) 2007-05-02
KR100642050B1 (ko) 2006-11-10
DE60024879T2 (de) 2006-07-20
DE1264078T1 (de) 2003-06-26
AU3879600A (en) 2001-09-24
JP4460814B2 (ja) 2010-05-12
DE60024879D1 (de) 2006-01-19
CA2349917C (fr) 2008-12-02

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