WO2004063535A1 - Sealing means for a lubrication system in a turbocharger - Google Patents
Sealing means for a lubrication system in a turbocharger Download PDFInfo
- Publication number
- WO2004063535A1 WO2004063535A1 PCT/IB2003/000042 IB0300042W WO2004063535A1 WO 2004063535 A1 WO2004063535 A1 WO 2004063535A1 IB 0300042 W IB0300042 W IB 0300042W WO 2004063535 A1 WO2004063535 A1 WO 2004063535A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- turbocharger
- sealing
- sealing portion
- ring
- turbine wheel
- Prior art date
Links
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
- F01D25/186—Sealing means for sliding contact bearing
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
-
- 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
- F02B37/001—Engines characterised by provision of pumps driven at least for part of the time by exhaust using exhaust drives arranged in parallel
- F02B37/002—Engines characterised by provision of pumps driven at least for part of the time by exhaust using exhaust drives arranged in parallel the exhaust supply to one of the exhaust drives can be interrupted
-
- 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
- F02B37/007—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in parallel, e.g. at least one pump supplying alternatively
-
- 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
- F02B37/16—Control of the pumps by bypassing charging air
-
- 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
- F02B37/16—Control of the pumps by bypassing charging air
- F02B37/162—Control of the pumps by bypassing charging air by bypassing, e.g. partially, intake air from pump inlet to pump outlet
-
- 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
- F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
-
- 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
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
- F02B39/14—Lubrication of pumps; Safety measures therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/13—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/102—Shaft sealings especially adapted for elastic fluid pumps
- F04D29/104—Shaft sealings especially adapted for elastic fluid pumps the sealing fluid being other than the working fluid or being the working fluid treated
-
- 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
-
- 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
- F05D2240/00—Components
- F05D2240/40—Use of a multiplicity of similar components
-
- 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
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
-
- 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
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/602—Drainage
- F05D2260/6022—Drainage of leakage having past a seal
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Definitions
- the invention relates to a turbocharger, preferably to a turbocharger for an internal combustion engine.
- the invention further relates to a multi-turbocharger boosting system.
- the object of the invention is to provide an improved turbocharger and an improved multi-turbocharger boosting system.
- the turbocharger comprises a compressor impeller connected by a shaft being rotatably supported in a bearing with a turbine wheel and at least one sealing arrangement with a sealing portion for avoiding leakage from the bearing to the space where one of the compressor impeller and the turbine wheel are located.
- the sealing arrangement comprises at least one pressure increasing means for increasing the pressure at a low pressure side of the sealing portion.
- the low pressure side of the sealing portion is the side being communicated with and/or facing the space where one of the compressor impeller and the turbine wheel are located.
- a passage as pressure increasing means, which passage is communicated with air outside of the turbocharger or with the space where the turbine wheel is located.
- the sealing portion is a circumferential groove accommodating a sealing ring and in particular to provide the groove in the shaft with the ring being abutted under pressure against one of the side walls of the groove and a radially opposite surface of an opening where the shaft is accommodated.
- both the sealing ring and the groove have a rectangular cross section, wherein the size and cross- section of the sealing ring are such that in the sealing position of the ring a radial and axial clearance between the high pressure side of the ring and the groove can be established.
- the sealing arrangement comprises one or more additional sealing portions, wherein the pressure increasing means is provided between two adjacent sealing portions .
- the sealing arrangement comprises one or more additional sealing portions, wherein said pressure increasing means are communicated with the space where one of the compressor impeller and the turbine wheel are located, preferably adjacent to the sealing portion behind the compressor impeller or the turbine wheel, respectively.
- the passage of the pressure increasing means merges into the opening in which the shaft is rotatably accommodated.
- a multi-turbocharger boosting system comprising at least a first turbocharger and a second turbocharger, wherein at least the second turbocharger is a turbocharger according to one of the embodiments mentioned above.
- the pressure increasing means of the second turbocharger are communicated with the compressor output and/or the turbine input of the first turbocharger.
- a turbocharger with a turbine side actuating mechanism for actuating a device within the turbocharger housing from outside the turbocharger housing, said mechanism comprising a rod which is rotatably mounted in the turbocharger housing for transmitting an actuating movement from outside the turbocharger housing to the device, wherein the rod is provided with a sealing portion for avoiding gas leakage.
- the device is a variable nozzle device comprising an unison ring for actuating vanes forming nozzle passages and the actuating mechanism is a linkage mechanism comprising the rod being coupled at one end to a link arm coupled to the unison ring and the other end coupled to external adjusting means, wherein the sealing portion is formed as explained above with regard to the first aspect of the invention.
- Figure 1 shows a cross-sectional view of a first embodiment of the turbocharger according to the invention
- Figures 2 and 3 show enlarged views of the seal portion of the turbocharger in Fig. 1 at the compressor and turbine side thereof, respectively;
- Figure 4 illustrates a layout of a multi-turbocharger boosting system in which a turbocharger according to the invention is incorporated;
- Figure 5 shows a cross-sectional view of a second embodiment of the turbocharger according to the invention;
- Figures 6 and 7 show enlarged views of the seal portion of the turbocharger in Fig. 5 at the compressor and turbine side thereof, respectively;
- Figure 8 shows a cross-sectional view of a third embodiment of the turbocharger according to the invention.
- Figure 9 shows an enlarged cross-sectional view of the third embodiment of the turbocharger where a cartridge accommodating a variable nozzle device is used
- Figure 10 shows an enlarged cross-sectional view of a fourth embodiment of the turbocharger according to the invention.
- Figure 11 shows an enlarged cross-sectional view of an actuation mechanism according to the invention.
- Figure 12 shows an enlarged cross-sectional view of the sealing portion of the actuation mechanism in Fig. 11.
- the essential parts of a turbocharger according to a first embodiment of the invention are illustrated in Fig. 1 where details of the turbocharger housing and the particular construction of the turbocharger parts are not shown in detail.
- the turbocharger comprises a compressor impeller 1 and a turbine wheel 3 mounted on the opposite ends of a common shaft 5.
- the shaft 5 is freely rotatable in a bearing 7 provided with an oil supplying system 9 the arrangement of which is not particularly shown in Fig. 1.
- the bearing 7 is supported in a center housing 11.
- the seal portion 15 at the turbine wheel side is formed as an enlarged portion of the shaft 5, whereas the seal portion and the impeller side of the shaft is formed as a seal sleeve or oil slinger 13.
- Fig. 2 in the outer circumferential surface of the oil slinger 13 there are provided two circumferential grooves 17 in which seal rings 19 are accommodated for providing a leak-tight seal between the oil slinger 13 and a collar portion 21 of the center housing 11.
- the collar portion 21 there is provided at least one ventilation passage 23 which merges between the seal rings 19 into a central shaft opening formed by the collar portion 21 in order to communicate this opening with the air outside the turbocharger.
- the extended diameter portion of the shaft 5 is also provided with a twin-groove arrangement similar to the described above, where in grooves 25 there are accommodated seal rings 27.
- a turbine side collar portion 29 of the center housing 11 forms a central opening encompassing the large diameter seal portion 15 of the shaft 5 and is in abutment with the seal or piston rings 27.
- the portion of the central shaft opening extending between the seal rings 27 is communicated with the air outside the turbocharger by means of a ventilation passage 31 which extends within the turbine side collar portion 29.
- the system comprises a first turbocharger 601 and a second turbocharger 602, wherein the two turbochargers are connected generally parallel in relation to an internal combustion engine 603.
- the first turbocharger 601 comprises preferably a free floating turbine 605 at its turbine side
- the second turbocharger 602 is equipped with a variable geometry turbine 607.
- the turbines 605 and 607 and respective compressors 609 and 611 are connected in parallel. According to the layout fresh air is fed in parallel to each of the compressors by means of a first fresh air conduit 604 and second fresh air conduit 606 and the air discharged from the compressors is guided through an intercooler 612 to the intake side of the internal combustion engine 603.
- the exhaust from the engine 603 is fed through a first exhaust conduit 608 and a second exhaust conduit 610 branching from a conduit or piping 623 to the first and second turbine 605 and 607, respectively, and the exhaust discharged from the parallel turbines is guided to a catalyst 614.
- the second compressor 611 is provided with an air re-circulation system using air flow regulating means for adjusting the amount of the re-circulated air.
- the re-circulation system in this embodiment includes a by-pass conduit 613 with a butterfly valve 615 for adjusting the air mass-flow re-circulated back into the second fresh air conduit 606 connecting the inlet of the second compressor 611 with an air filter 619.
- the multi-turbocharger boosting system further comprises an additional butterfly valve 639 being arranged in the conduit 641 connecting the second compressor 611 with the intercooler 612 between the merging point of the by-pass conduit 613 downstream of the second compressor 611 and the merging point of the first compressor 609 in the conduit 641.
- a bypass passage 625 with a_corresponding waste gate valve 629 At the turbine side of the multi-turbocharger boosting system there is provided a bypass passage 625 with a_corresponding waste gate valve 629.
- a butterfly or throttle valve 633 is arranged in the second exhaust conduit 610.
- the multi-turbocharger boosting system according to Fig. 4 allows a highly efficient function of the internal combustion engine at low, medium and high rotational speeds of the internal combustion engine.
- the exhaust gas supplied through the exhaust conduit or piping 623 drives the free floating turbine 605 of the first turbocharger 601.
- the butterfly valve 633 is closed or nearly closed to reduce exhaust gas flow into turbine 607 to ensure an idling rotation of the second turbocharger 602 so as merely to avoid oil leakage from the bearing system thereof.
- the speed of the first turbocharger is controlled by means of the waste gate valve 629.
- the first turbocharger works normally to supercharge the engine 603.
- the butterfly valve 615 is open so that a re-circulation at the second compressor 611 is achieved. Due to the particular design of the layout, during the re-circulation the pressure in the second compressor 602 can be lowered so that the trust load becomes less important and the reliability is improved.
- the additional butterfly valve 639 remains closed and the first compressor 609 works normally to supercharge the engine
- the butterfly or throttle valve 633 opens progressively so as to regulate the pressure before the turbine and the exhaust gas flow drives the second turbocharger 602.
- the butterfly valve 615 is progressively closed in order to balance the power between the second compressor 611 and the second turbine, so that by operation of the butterfly valve 615 the speed of the second turbocharger 602 can be regulated.
- the butterfly valve 633 In the range of a high rotational speed of the internal combustion engine, which means at about 2500 - 4000 rpm, the butterfly valve 633 is completely or almost completely open, wherein the speed of the turbine 605 is regulated by means of the waste gate valve 629. During this operation the additional butterfly valve 639 is open and the butterfly valve 615 is totally closed.
- the butterfly valve 633 can be closed or nearly closed without causing thereby an oil leakage.
- the pressure behind the impeller 1 of turbocharger 602 becomes quite low, the pressure drop at the outer piston ring 19 is decreased by ventilating the space between the outer and inner piston rings by air at normal atmosphere pressure.
- the further seal ring 19 positioned between the ventilation passage 23 and the bearing 7 is also subject to reduced pressure drop so that an oil leakage to the impeller side of the turbocharger can be efficiently avoided even if the rotation of the second turbocharger is stopped.
- the ventilation passage 31 arranged at the turbine side as shown in Fig. 3 has almost the same function as the ventilation passage 23 at the impeller side of the turbocharger. At low rotational speed of the internal combustion engine, there is also a significant drop in pressure in the space around and behind the turbine wheel 3.
- the outer seal arrangement consisting of a seal or piston ring and a groove
- the merging point of the ventilation passage is to be arranged close to a single piston ring at the corresponding groove.
- the collar portion 121 of the center housing 111 is formed with an invertly sloped surface, wherein the merging point of the ventilation passage 123 is arranged at the radially invert almost lowest part of the sloped surface in close proximity to the seal arrangement 117, 119.
- the merging point of the ventilation passage can be also directly arranged in the center opening of the collar portion 121, so that the clearance of the fit between the shaft and the center opening in the portion between the merging point and the compressor space serves as throttling means .
- a ventilation passage 131 communicates the space behind the turbine wheel being closest to the seal arrangement 125, 127 with the air outside the turbocharger.
- a variable geometry nozzle device is designed and arranged in such a way between the center housing 111 and a turbine housing 235 that there is provided at least one gas passage 237 which communicates the exhaust gas inlet side of the turbine with the ventilation passage 231 as shown in Figs. 9 and 10 representing arrangements of the ventilation passage at the turbine side similar to the second and first embodiment, respectively.
- an actuation device 241 comprising a lever for circumferentially shifting the unison ring 245 of the variable nozzle device shown in Fig. 9.
- an actuating shaft 247 of the actuation device is rotatably supported in a bushing 249 interposed in the center housing 211.
- a seal arrangement consisting of a circumferential groove 251 and a seal ring 253.
- the seal ring 253 has elastic properties which allows each to be stocked into the bushing internal face as is the case with the seal rings described above.
- the seal ring has a substantially rectangular cross-section with two adjacent sealing surfaces abutting against the bushing 249 and the crank pin 247.
- the axial thickness of the seal ring 253 is smaller than the axial width of the groove 251, whereas the inner diameter of the seal ring 253 exceeds the diameter of the bottom portion of the groove 251, such that an L-shaped clearance 255 shown in Fig. 12 is established when the seal ring is exposed to the exhaust gas pressure from the right side in Fig. 12.
- actuation device 241 can be applied in each of the third and fourth embodiment shown in Figs. 9 and 10. Furthermore the sealing portion described above with reference to Figures 11 and 12 is also preferably applicable in each of the embodiments described above with reference to Figures 1 to 10.
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/IB2003/000042 WO2004063535A1 (en) | 2003-01-10 | 2003-01-10 | Sealing means for a lubrication system in a turbocharger |
EP07116473A EP1860299A1 (en) | 2003-01-10 | 2003-01-10 | Sealing means for a lubrication system in a turbocharger |
AU2003201061A AU2003201061A1 (en) | 2003-01-10 | 2003-01-10 | Sealing means for a lubrication system in a turbocharger |
EP03815122.1A EP1585888B1 (en) | 2003-01-10 | 2003-01-10 | Turbocharger |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/IB2003/000042 WO2004063535A1 (en) | 2003-01-10 | 2003-01-10 | Sealing means for a lubrication system in a turbocharger |
Publications (1)
Publication Number | Publication Date |
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WO2004063535A1 true WO2004063535A1 (en) | 2004-07-29 |
Family
ID=32696986
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/IB2003/000042 WO2004063535A1 (en) | 2003-01-10 | 2003-01-10 | Sealing means for a lubrication system in a turbocharger |
Country Status (3)
Country | Link |
---|---|
EP (2) | EP1585888B1 (en) |
AU (1) | AU2003201061A1 (en) |
WO (1) | WO2004063535A1 (en) |
Cited By (24)
Publication number | Priority date | Publication date | Assignee | Title |
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EP1674668A2 (en) | 2004-12-24 | 2006-06-28 | Toyota Jidosha Kabushiki Kaisha | Variable geometry turbocharger |
WO2006128616A1 (en) * | 2005-06-02 | 2006-12-07 | Borgwarner Inc. | Adjusting shaft arrangement of a turbocharger |
EP1895106A1 (en) * | 2006-08-28 | 2008-03-05 | ABB Turbo Systems AG | Sealing of variable guide vanes |
EP1972759A2 (en) * | 2007-03-22 | 2008-09-24 | Honeywell International Inc. | Stepped outer diameter semi-floating bearing |
WO2008149075A1 (en) * | 2007-06-07 | 2008-12-11 | Cummins Turbo Technologies Limited | Sealing method for a turbocharger shaft seal and corresponding turbocharger |
CN101457658A (en) * | 2007-11-28 | 2009-06-17 | 霍尼韦尔国际公司 | Turbocharger center housing and rotating assembly |
US7581394B2 (en) * | 2003-12-10 | 2009-09-01 | Honeywell International Inc. | Variable nozzle device for a turbocharger |
DE102008054265A1 (en) | 2008-10-31 | 2010-05-06 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | loader |
DE102009007364A1 (en) * | 2009-02-04 | 2010-08-05 | Continental Automotive Gmbh | Actuation shaft for actuating wastegate valve of variable turbine geometry turbocharger of internal-combustion engine, has supporting bush device that is designed such that shaft is screwable with turbocharger housing |
JP2011017326A (en) * | 2009-07-10 | 2011-01-27 | Ihi Corp | Variable displacement turbocharger |
DE102009052225A1 (en) | 2009-11-06 | 2011-05-12 | Volkswagen Ag | Gas seal for use between shaft and housing, particularly for exhaust-gas turbocharger, has two rotors, where latter rotor is connected with shaft |
WO2011149867A2 (en) * | 2010-05-27 | 2011-12-01 | Borgwarner Inc. | Control shaft seal |
CN102434225A (en) * | 2011-10-18 | 2012-05-02 | 中国南方航空工业(集团)有限公司 | Sealing structure of booster impeller shaft |
CN102828988A (en) * | 2012-09-26 | 2012-12-19 | 上海中船三井造船柴油机有限公司 | Labyrinth sealing device of ship auxiliary blower |
WO2012177507A2 (en) * | 2011-06-24 | 2012-12-27 | Caterpillar Inc. | Turbocharger with air buffer seal |
US8474433B2 (en) | 2008-08-13 | 2013-07-02 | Cummins Turbo Technologies Limited | Engine braking method and system |
US8579579B2 (en) | 2009-11-10 | 2013-11-12 | Honeywell International Inc. | Sealed shaft assembly for exhaust turbines |
JP2013234589A (en) * | 2012-05-08 | 2013-11-21 | Ihi Corp | Oil seal structure and supercharger |
US8961151B2 (en) | 2011-04-02 | 2015-02-24 | Cummins Ltd. | Turbocharger |
CN104847688A (en) * | 2014-02-19 | 2015-08-19 | 霍尼韦尔国际公司 | Sealing arrangement for fuel cell compressor |
CN106246590A (en) * | 2016-07-29 | 2016-12-21 | 中国北方发动机研究所(天津) | A kind of turbocharger air compressor end sealing arrangement structure |
US9537363B2 (en) | 2014-04-30 | 2017-01-03 | Honeywell International Inc. | Electric motor-driven compressor having an electrical terminal block assembly |
CN110296100A (en) * | 2018-03-22 | 2019-10-01 | 曼恩能源方案有限公司 | Turbo-compressor |
DE102009041741B4 (en) | 2008-10-31 | 2020-08-06 | BMTS Technology GmbH & Co. KG | Exhaust gas turbocharger for a motor vehicle |
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102006061345A1 (en) * | 2006-10-26 | 2008-04-30 | Robert Bosch Gmbh | Registeraufladeeinrichtung |
DE102010003796A1 (en) | 2010-04-09 | 2011-10-13 | Abb Turbo Systems Ag | shaft seal |
JP5776452B2 (en) * | 2011-08-31 | 2015-09-09 | 株式会社Ihi | Multiple seal structure and turbocharger |
EP2743460B1 (en) | 2012-12-14 | 2017-04-05 | ABB Turbo Systems AG | Shaft seal |
DE102015206816A1 (en) * | 2015-04-15 | 2016-10-20 | Robert Bosch Gmbh | Rotor cartridge for a turbomachine of an internal combustion engine, turbomachine of an internal combustion engine and method for assembling a turbomachine of an internal combustion engine |
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US4196910A (en) * | 1977-05-19 | 1980-04-08 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Shaft sealing device for turbocharger |
JPS5893932A (en) * | 1981-11-30 | 1983-06-03 | Nissan Motor Co Ltd | Lubricating oil leakage preventer for turbo supercharger |
US4752193A (en) * | 1983-09-01 | 1988-06-21 | Bbc Brown Boveri Ltd. | Exhaust-gas turbocharger for the two-stage supercharging of an internal-combustion engine with a device to prevent losses of lubricant |
DE3817617A1 (en) * | 1988-05-25 | 1989-07-20 | Daimler Benz Ag | Exhaust turbocharger for an internal combustion engine |
EP0357246A2 (en) * | 1988-08-03 | 1990-03-07 | Nissan Motor Co., Ltd. | Shaft seal arrangement of turbocharger |
US5890881A (en) * | 1996-11-27 | 1999-04-06 | Alliedsignal Inc. | Pressure balanced turbocharger rotating seal |
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- 2003-01-10 EP EP03815122.1A patent/EP1585888B1/en not_active Expired - Lifetime
- 2003-01-10 AU AU2003201061A patent/AU2003201061A1/en not_active Abandoned
- 2003-01-10 WO PCT/IB2003/000042 patent/WO2004063535A1/en not_active Application Discontinuation
- 2003-01-10 EP EP07116473A patent/EP1860299A1/en not_active Withdrawn
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Also Published As
Publication number | Publication date |
---|---|
AU2003201061A1 (en) | 2004-08-10 |
EP1860299A1 (en) | 2007-11-28 |
EP1585888A1 (en) | 2005-10-19 |
EP1585888B1 (en) | 2018-09-26 |
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