WO2001069045A1 - Variable geometry turbocharger - Google Patents
Variable geometry turbocharger Download PDFInfo
- 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
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.
Landscapes
- 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)
Priority Applications (11)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BR0006983A BR0006983B1 (pt) | 2000-03-13 | 2000-03-13 | sistema para posicionamento de palhetas aerodinÂmicas do bocal de uma turbina. |
PCT/US2000/006512 WO2001069045A1 (en) | 2000-03-13 | 2000-03-13 | Variable geometry turbocharger |
KR1020017004407A KR100642050B1 (ko) | 2000-03-13 | 2000-03-13 | 가변 형상 터보 과급기 |
AU38796/00A AU758433B2 (en) | 2000-03-13 | 2000-03-13 | Variable geometry turbocharger |
DE1264078T DE1264078T1 (de) | 2000-03-13 | 2000-03-13 | Turbolader mit verstellbaren leitschaufeln |
CA002349917A CA2349917C (en) | 2000-03-13 | 2000-03-13 | Variable geometry turbocharger |
EP00917890A EP1264078B1 (de) | 2000-03-13 | 2000-03-13 | Turbolader mit verstellbaren leitschaufeln |
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 |
CNB008193304A CN1313711C (zh) | 2000-03-13 | 2000-03-13 | 可变几何尺寸的涡轮增压器 |
JP2001567905A JP4460814B2 (ja) | 2000-03-13 | 2000-03-13 | 可変形状ターボチャージャ |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/US2000/006512 WO2001069045A1 (en) | 2000-03-13 | 2000-03-13 | Variable geometry turbocharger |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2001069045A1 true WO2001069045A1 (en) | 2001-09-20 |
Family
ID=21741144
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2000/006512 WO2001069045A1 (en) | 2000-03-13 | 2000-03-13 | Variable geometry turbocharger |
Country Status (9)
Country | Link |
---|---|
EP (1) | EP1264078B1 (de) |
JP (1) | JP4460814B2 (de) |
KR (1) | KR100642050B1 (de) |
CN (1) | CN1313711C (de) |
AT (1) | ATE313007T1 (de) |
AU (1) | AU758433B2 (de) |
CA (1) | CA2349917C (de) |
DE (2) | DE1264078T1 (de) |
WO (1) | WO2001069045A1 (de) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2004022925A1 (de) * | 2002-08-16 | 2004-03-18 | Borgwarner Turbo Systems Gmbh | Abgasturbolader für eine brennkraftmaschine |
EP1420152A2 (de) * | 2002-11-18 | 2004-05-19 | BorgWarner Turbo Systems GmbH | Abgasturbolader |
WO2005088100A2 (en) * | 2004-03-08 | 2005-09-22 | Honeywell International Inc. | Vane control |
DE102004023214A1 (de) * | 2004-05-11 | 2005-12-08 | Volkswagen Ag | Abgasturbolader für eine Brennkraftmaschine mit variabler Turbinengeometrie |
EP1674668A2 (de) | 2004-12-24 | 2006-06-28 | Toyota Jidosha Kabushiki Kaisha | Turbolader mit variabler Geometrie |
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 |
Families Citing this family (18)
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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 |
CN101395358B (zh) * | 2006-03-14 | 2013-11-20 | 博格华纳公司 | 涡轮增压器 |
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 |
DE112009004309T5 (de) * | 2008-12-11 | 2012-05-24 | Borgwarner Inc. | Vereinfachter Turbolader mit veränderlicher Geometrie und veränderlicher Dose |
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***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 |
JP2017527739A (ja) * | 2014-09-23 | 2017-09-21 | ボーグワーナー インコーポレーテッド | 一体型アクチュエータを備えるターボチャージャ |
CN209510457U (zh) * | 2018-06-14 | 2019-10-18 | 博格华纳公司 | 用于具有可变调节机构的压缩机的装置以及增压装置 |
CN115744828B (zh) * | 2022-11-22 | 2023-08-04 | 福建德尔科技股份有限公司 | 一种电子级三氟化氯生产用的增压器 |
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US4804316A (en) | 1985-12-11 | 1989-02-14 | Allied-Signal Inc. | Suspension for the pivoting vane actuation mechanism of a variable nozzle turbocharger |
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US4274329A (en) * | 1978-11-13 | 1981-06-23 | Weyer Paul P | Rotary actuator apparatus |
US4300869A (en) * | 1980-02-11 | 1981-11-17 | Swearingen Judson S | Method and apparatus for controlling clamping forces in fluid flow control assemblies |
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US4726744A (en) * | 1985-10-24 | 1988-02-23 | Household Manufacturing, Inc. | Tubocharger with variable vane |
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2000
- 2000-03-13 CN CNB008193304A patent/CN1313711C/zh not_active Expired - Lifetime
- 2000-03-13 DE DE1264078T patent/DE1264078T1/de active Pending
- 2000-03-13 WO PCT/US2000/006512 patent/WO2001069045A1/en active IP Right Grant
- 2000-03-13 KR KR1020017004407A patent/KR100642050B1/ko active IP Right Grant
- 2000-03-13 CA CA002349917A patent/CA2349917C/en not_active Expired - Fee Related
- 2000-03-13 AU AU38796/00A patent/AU758433B2/en not_active Ceased
- 2000-03-13 DE DE60024879T patent/DE60024879T2/de not_active Expired - Lifetime
- 2000-03-13 EP EP00917890A patent/EP1264078B1/de not_active Expired - Lifetime
- 2000-03-13 AT AT00917890T patent/ATE313007T1/de not_active IP Right Cessation
- 2000-03-13 JP JP2001567905A patent/JP4460814B2/ja not_active Expired - Lifetime
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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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2004022925A1 (de) * | 2002-08-16 | 2004-03-18 | Borgwarner Turbo Systems Gmbh | Abgasturbolader für eine brennkraftmaschine |
EP1420152A2 (de) * | 2002-11-18 | 2004-05-19 | BorgWarner Turbo Systems GmbH | Abgasturbolader |
EP1420152A3 (de) * | 2002-11-18 | 2006-07-19 | BorgWarner Turbo Systems GmbH | Abgasturbolader |
WO2005088100A2 (en) * | 2004-03-08 | 2005-09-22 | Honeywell International Inc. | Vane control |
WO2005088100A3 (en) * | 2004-03-08 | 2005-12-01 | Honeywell Int Inc | Vane control |
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 (de) | 2004-12-24 | 2015-10-14 | Toyota Jidosha Kabushiki Kaisha | Turbolader mit variabler Geometrie |
EP1674668A2 (de) | 2004-12-24 | 2006-06-28 | Toyota Jidosha Kabushiki Kaisha | Turbolader mit variabler Geometrie |
EP1674668A3 (de) * | 2004-12-24 | 2012-03-07 | Toyota Jidosha Kabushiki Kaisha | Turbolader mit variabler Geometrie |
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 |
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 |
Also Published As
Publication number | Publication date |
---|---|
KR20020081047A (ko) | 2002-10-26 |
DE1264078T1 (de) | 2003-06-26 |
DE60024879T2 (de) | 2006-07-20 |
EP1264078B1 (de) | 2005-12-14 |
JP4460814B2 (ja) | 2010-05-12 |
CA2349917A1 (en) | 2001-09-13 |
CA2349917C (en) | 2008-12-02 |
ATE313007T1 (de) | 2005-12-15 |
KR100642050B1 (ko) | 2006-11-10 |
EP1264078A1 (de) | 2002-12-11 |
DE60024879D1 (de) | 2006-01-19 |
AU3879600A (en) | 2001-09-24 |
JP2003527522A (ja) | 2003-09-16 |
CN1451076A (zh) | 2003-10-22 |
AU758433B2 (en) | 2003-03-20 |
CN1313711C (zh) | 2007-05-02 |
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