US20080038110A1 - Sector-Divided Turbine Assembly With Axial Piston Variable-Geometry Mechanism - Google Patents

Sector-Divided Turbine Assembly With Axial Piston Variable-Geometry Mechanism Download PDF

Info

Publication number
US20080038110A1
US20080038110A1 US10/576,663 US57666303A US2008038110A1 US 20080038110 A1 US20080038110 A1 US 20080038110A1 US 57666303 A US57666303 A US 57666303A US 2008038110 A1 US2008038110 A1 US 2008038110A1
Authority
US
United States
Prior art keywords
vanes
piston
dividing
chamber
turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US10/576,663
Other languages
English (en)
Inventor
Quentin Roberts
Luciano Bernardini
Alain Lombard
Dominique Petitjean
Jeff Lotterman
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
Assigned to HONEYWELL INTERNATIONAL, INC. reassignment HONEYWELL INTERNATIONAL, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: PETITJEAN, DOMINIQUE, BERNARDINI, LUCIANO, LOMBARD, ALAIN, ROBERTS, QUENTIN, LOTTERMAN, JEFF
Publication of US20080038110A1 publication Critical patent/US20080038110A1/en
Abandoned legal-status Critical Current

Links

Images

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • 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
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • 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
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to turbochargers in which a turbine of the turbocharger is driven by exhaust gas from a reciprocating engine.
  • the invention relates more particularly to turbine housings that are divided into a plurality of substantially separate sections each fed by a separate exhaust system, and to turbochargers having a variable-geometry turbine for controlling the flow into the turbine.
  • the present invention relates instead to sector-divided turbine housings.
  • a sector-divided turbine housing the generally annular chamber is divided into angular sectors each of which occupies only a part of the circumference such that the passages succeed each other in the circumferential direction, such as shown in FIG. 2 of U.S. Pat. No. 6,260,358. That figure also shows guide vanes 12 that are positioned just radially inwardly of the chamber and guide the flow into the turbine wheel.
  • turbocharger To optimize the performance of a turbocharger over a range of different engine operating conditions, it is also desirable to control the flow through the turbine by using a variable-geometry mechanism so that the turbocharger can operate at a more-advantageous operating point as the reciprocating engine speed and other variables change.
  • the problem addressed by the invention is the integration of both sector division and variable geometry in a turbocharger. In known prior turbochargers having sector division and variable geometry, the full benefits of sector division generally have not been achieved; in fact, the benefits of sector division and variable geometry each have been compromised when such integration has been attempted.
  • FIG. 1 is an axial cross-sectional view of a turbocharger in accordance with one embodiment of the invention
  • FIG. 2 is a sectioned view of a turbine assembly in accordance with one embodiment of the invention.
  • FIG. 3 is a sectioned view of a turbine housing of the turbine assembly
  • FIG. 4A is an exploded perspective view of a vane and piston assembly of the turbine assembly
  • FIG. 4B is a cross-sectional view through the piston along line 4 B- 4 B in FIG. 4A ;
  • FIG. 4C is a perspective view of the vane and piston assembly, with the piston in a relatively open position with respect to the vanes;
  • FIG. 4D is a view similar to FIG. 4C , showing the piston in a relatively closed position
  • FIG. 5 is a view similar to FIG. 4D , showing an alternative embodiment in accordance with the invention.
  • FIG. 6 is an axial cross-sectional view of a turbine assembly in accordance with yet another embodiment of the invention.
  • FIG. 7 is a perspective view of the piston included in the turbine assembly of FIG. 6 .
  • FIG. 1 illustrates a turbocharger 10 in accordance with one embodiment of the invention.
  • the turbocharger 10 is similar in many respects to that described in U.S. Pat. No. 5,441,383, which is incorporated herein by reference.
  • the major components or modules of the turbocharger include a compressor assembly 20 , a center housing and bearing assembly 30 , and a turbine assembly 40 .
  • the compressor assembly 20 comprises a compressor housing 21 that defines an axially extending air inlet 22 through which air to be compressed is received into the compressor assembly.
  • Mounted within the compressor housing is a compressor wheel 23 that is rotatable about a central longitudinal axis of the turbocharger.
  • the compressor wheel 23 is mounted on one end of a rotatable shaft 26 that extends longitudinally through the center housing and bearing assembly 30 and connects to the turbine as described below.
  • the compressor wheel supports a plurality of compressor blades 24 .
  • the housing 21 and the wheel 23 define a flow path therebetween, and the blades 24 occupy the flow path.
  • the flow path is oriented generally axially at an upstream side of the compressor wheel, and then turns radially outwardly so that it extends generally radially outwardly at a downstream side of the wheel adjacent the trailing edges of the blades 24 .
  • Air is ingested through the inlet 22 into the row of blades 24 and is compressed as it travels along the flow path through the compressor; the compressed air is discharged radially outwardly into a generally annular volute 25 defined by the compressor housing. From the volute 25 , the compressed air is supplied via a discharge pipe (not shown) to an engine with which the turbocharger is associated. Compressing the intake air allows a greater amount of power to be produced by the engine.
  • the compressor illustrated in FIG. 1 is generally referred to as an axial-radial compressor, or a centrifugal compressor; however, the invention is not limited to any particular type of compressor, and other types may be used, such as axial-flow compressors.
  • the center housing and bearing assembly 30 includes a center housing 31 having a central bore therethrough, coaxially arranged with respect to the rotational axis of the compressor wheel.
  • a bearing 32 is mounted within the bore of the center housing.
  • the bearing 32 defines a central bore therethrough, and the shaft 26 extends through the bore in the bearing.
  • There is a radial clearance between the shaft and the bearing bore so that the shaft can rotate with respect to the bearing; oil or other lubricant is supplied into the bearing assembly via a supply port 33 defined in the center housing, and from the port 33 to the bearing via passages 34 , 35 , 36 .
  • the oil that has lubricated and cooled the bearing assembly is drained from the center housing via a drain 37 .
  • an oil-lubricated bearing system is shown, the invention is not limited to any particular type of bearing system.
  • the turbine assembly 40 includes a turbine housing 41 that defines a central cylindrical bore 42 therethrough.
  • the turbine housing also defines a generally annular volute or chamber 43 that surrounds the central bore 42 and opens into the bore at a radially inner side of the chamber.
  • Mounted on the opposite end of the shaft 26 from the compressor wheel 23 is a turbine wheel 44 that supports a plurality of turbine blades 45 .
  • hot exhaust gas from the engine (not shown) is supplied via a suitable exhaust duct system (not shown) into the chamber 43 .
  • the exhaust gas flows generally radially inwardly (although it can also have an axial component) from the chamber into the row of turbine blades 45 , which are appropriately shaped so that the turbine wheel 44 is rotatably driven by the exhaust gas.
  • the exhaust gas is expanded to a lower pressure as it passes through the turbine, and is then discharged from the turbine housing 41 .
  • Mechanical power generated by the turbine is used to drive the compressor via the shaft 26 .
  • pulse separation wherein the cylinders of the engine are divided into a plurality of subgroups, and the pulses from each subgroup of cylinders are isolated from those of the other subgroups by having independent exhaust passages for each subgroup.
  • pulse separation it is desired to minimize the communication or cross talk between the separate exhaust passages. Accordingly, in the case of a turbocharged engine, it is advantageous to maintain separate exhaust passages all the way into the turbine of the turbocharger.
  • the turbine housing 41 of the turbocharger advantageously comprises a sector-divided turbine housing, wherein the generally annular chamber 43 is divided into a plurality of angular sectors that are separate from one another and are fed with exhaust gas via separate inlet ducts.
  • Various numbers of sectors can be employed in accordance with the invention.
  • FIGS. 2 and 3 depict one embodiment of a turbine assembly and housing wherein the generally annular chamber 43 is divided into two angular sectors 43 a and 43 b each occupying approximately 180 degrees of the circumference of the chamber.
  • the chamber 43 is divided into the sectors by a pair of dividing “tongues” or walls 46 that extend generally radially inwardly (but typically also with a substantial circumferential or tangential directional component) from a radially outer wall of the chamber.
  • the sector 43 a is supplied with exhaust gas via an inlet duct 47 a
  • the sector 43 b is supplied with exhaust gas via a separate inlet duct 47 b.
  • variable-geometry turbine nozzle is provided by a hollow cylindrical or tubular piston 48 that is arranged to slide axially within the bore 42 of the turbine housing 41 between a relatively open position (shown in phantom lines in FIG. 1 ) and a relatively closed position (shown in solid lines in FIG. 1 ).
  • the piston In the relatively open position, the piston uncovers a relatively large proportion of the total axial length of the chamber sectors 43 a,b so that a relatively large flow area is available for the exhaust gas to flow through as it flows inwardly to the turbine wheel.
  • the piston 48 covers a substantial portion of the axial length of the sectors so that a relatively small proportion of the axial length is available for the exhaust gas to flow through.
  • the piston is moved between the open and closed positions by a suitable actuator and control system (not shown); advantageously, the actuator and control system are also operable to position the piston in any axial position between the fully open and fully closed positions, so that an infinitely variable adjustment of the variable-geometry turbine nozzle can be achieved.
  • the turbine assembly 40 also can include a vane arrangement 50 for guiding the flow into the turbine wheel.
  • the vane arrangement, the variable-geometry turbine nozzle, and the sector division of the turbine housing are combined in a unique and particularly advantageous way.
  • the vane arrangement includes a generally ring-shaped member 51 that abuts the turbocharger center housing 31 and includes a flange retained between the center housing 31 and the turbine housing 41 .
  • a plurality of vanes are mounted on the member 51 and project from one side thereof; the vanes are radially located just inward of the turbine housing chamber 43 , as best seen in FIG. 1 .
  • the vanes include dividing vanes 52 that are arranged to abut or join with, in a substantially sealed manner, the radially inner ends of the dividing walls 46 of the sector-divided turbine housing.
  • the dividing vanes 52 thus serve as extensions of the dividing walls so that the sector-division of the turbine housing is extended all the way to the trailing edges of the dividing vanes, and hence essentially to the turbine wheel 44 .
  • the vane arrangement also optionally includes one or more additional vanes 53 arranged between the dividing vanes 52 . In the embodiment of FIGS. 1-4 , there are three additional vanes 53 per sector 43 a,b , and the additional vanes have a smaller axial extent than the dividing vanes. However, it is within the scope of the invention to eliminate the additional vanes altogether so that the only vanes present in the turbine are the dividing vanes.
  • the dividing vanes can extend across the full axial length of the turbine housing sectors 43 a,b as seen in FIG. 1 , so that the sector-division of turbine housing is preserved when the piston 48 is in the fully open position.
  • the additional vanes 53 can extend across less than the full axial length of the sectors 43 a,b .
  • the vanes 53 are sized so that when the piston 48 is in its most closed position as shown in FIG. 1 , the vanes 53 extend across the remaining open portion of the sectors 43 a,b ; in this closed position of the piston, the vanes 53 can abut the end of the piston.
  • the piston has a slot 49 for receiving each dividing vane 52 .
  • the slots 49 advantageously fit closely about the dividing vanes 52 so that flow is substantially prevented from passing between the dividing vanes and the slots from one sector of the turbine housing chamber to an adjacent sector. In this manner, the sector-division of the turbine housing can be preserved all the way to the trailing edges of the dividing vanes for all positions of the piston.
  • the slots 49 for the vanes 52 extend generally radially inwardly into the piston from the radially outer side of the piston, but it is preferred (although not essential) for the slots not to go all the way through to the radially inner side of the piston; that is, the slots preferably extend through less than the full radial thickness of the piston.
  • FIG. 5 shows an alternative embodiment of a vane assembly 50 ′ and piston 48 ′ wherein the dividing vanes 52 ′ and additional vanes 53 ′ are all the same length and are sized to extend across the full axial length of the turbine housing sectors.
  • the piston includes slots 49 ′ for the dividing vanes and also includes slots 49 ′′ for the additional vanes 53 ′. With this arrangement, the vanes provide a guiding function at all positions of the piston.
  • FIGS. 6 and 7 depict such an embodiment.
  • FIG. 6 shows a turbine assembly 140 generally similar to the turbine assembly 40 of FIG. 1 , including a sector-divided turbine housing 141 , a turbine wheel 144 , and an axially sliding piston 148 .
  • Dividing vanes 152 and additional vanes 153 are affixed to the end of the piston 148 and project axially therefrom.
  • the dividing vanes are longer than the additional vanes, and are long enough so that when the piston is in its most open position (as shown in phantom lines in FIG. 6 ), the dividing vanes extend across the full axial length of the turbine housing sectors 143 .
  • the turbine assembly includes a heat shroud 160 that is retained between the center housing 31 and the turbine housing 141 and forms one wall of the turbine nozzle passage through which the exhaust gas flows into the turbine wheel.
  • the heat shroud includes slots 161 through which the dividing vanes extend when the piston is moved toward its closed position as shown in FIG. 6 .
  • the additional vanes 153 are described and shown as being shorter than the dividing vanes 152 , it is within the scope of the invention to make the additional vanes the same length as the dividing vanes, in which case the heat shroud 160 would include slots for the additional vanes as well as the dividing vanes.
  • the dividing vanes either can be mounted on the piston and be received through slots in a fixed structure of the turbine assembly, or can be mounted on a fixed structure of the turbine assembly and be received through slots in the piston. It is also possible for the dividing vanes to be formed integrally with (i.e., of one piece with) the dividing walls; for example, the turbine housing can be cast, and the dividing walls and dividing vanes can form integral parts of the casting. Any additional vanes included in the vane arrangement can also be mounted either on fixed structure or on the piston; additionally, it is possible to mount the dividing vanes on fixed structure and mount the additional vanes on the piston, or to mount the dividing vanes on the piston and mount the additional vanes on fixed structure.
  • Turbine assemblies in accordance with the invention can also include an integrated bypass (not illustrated) arranged in the variable-geometry piston such that when the piston is in a particular position (e.g., its fully open position), the bypass allows the exhaust gas in the turbine housing chamber to bypass the turbine wheel and thereby achieve an augmented flow rate.
  • the pistons in the illustrated embodiments are shown as not extending radially inwardly beyond the trailing edges of the vanes, it is within the scope of the invention to have the piston extend radially inwardly of the vane trailing edges.
  • the disclosed embodiments have turbine wheels in which the inlet and exit diameters of the wheel are the same.
  • the invention is not limited to such configurations, and it is within the scope of the invention to employ turbine wheels of other configurations.
  • the turbine wheel can have an exit diameter smaller than its inlet diameter.
  • the invention is not limited to radial-flow turbines as illustrated, but also applies to mixed-flow and axial-flow turbines.
  • a mixed-flow turbine the exhaust gas enters the turbine wheel along a direction having both radially inward and axial components. Accordingly, the gas flows from the generally annular chamber in a generally radially inward direction and can then be turned somewhat toward axial by suitable guide vane extensions just upstream of the turbine wheel.
  • the concepts of the present invention still apply to mixed-flow arrangements.
  • the invention also applies to axial-flow turbines, wherein the flow leaving the generally annular chamber is turned just upstream of the turbine wheel by suitable guide vanes so that the flow enters the wheel generally axially.
  • the invention provides a unique and particularly advantageous uniting of sector-division and variable-geometry turbine nozzle features in a turbine assembly for a turbocharger or other device.
  • the sector-division of the exhaust streams from an engine can be kept separate and essentially isolated from one another all the way to the inlet of the turbine wheel.
  • the full benefits of variable geometry are attainable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
US10/576,663 2003-10-24 2003-10-24 Sector-Divided Turbine Assembly With Axial Piston Variable-Geometry Mechanism Abandoned US20080038110A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IB2003/005142 WO2005040560A1 (fr) 2003-10-24 2003-10-24 Ensemble turbine divise en secteurs, equipe d'un mecanisme a geometrie variable et a piston axial

Publications (1)

Publication Number Publication Date
US20080038110A1 true US20080038110A1 (en) 2008-02-14

Family

ID=34509324

Family Applications (1)

Application Number Title Priority Date Filing Date
US10/576,663 Abandoned US20080038110A1 (en) 2003-10-24 2003-10-24 Sector-Divided Turbine Assembly With Axial Piston Variable-Geometry Mechanism

Country Status (4)

Country Link
US (1) US20080038110A1 (fr)
EP (1) EP1725742A1 (fr)
AU (1) AU2003278524A1 (fr)
WO (1) WO2005040560A1 (fr)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090164037A1 (en) * 2007-12-24 2009-06-25 Snecma Services Method of selecting an arrangement of sectors for a turbomachine nozzle
US20100172750A1 (en) * 2007-01-16 2010-07-08 Genius Air conditioning apparatus equipped with a compressor and a vortex
US20100196145A1 (en) * 2009-02-03 2010-08-05 Alain Lombard Turbine assembly for an exhaust gas-driven turbocharger having a variable nozzle
US20110067397A1 (en) * 2008-08-21 2011-03-24 Torsten Hirth Internal combustion engine with an exhaust gas turbocharger
US20110103938A1 (en) * 2009-10-06 2011-05-05 Holroyd Robert L Turbomachine
US20120031092A1 (en) * 2009-04-23 2012-02-09 Siegfried Sumser Internal combustion engine and method for operating an internal combustion engine
CN102770624A (zh) * 2009-10-06 2012-11-07 康明斯有限公司 涡轮机
DE102011121330A1 (de) * 2011-12-16 2013-06-20 Ihi Charging Systems International Gmbh Turbine für einen Abgasturbolader
US20140086725A1 (en) * 2011-08-15 2014-03-27 Wuxi Kaidi Supercharger Accessories Co., Ltd. Turbocharger with a double-vane nozzle system
US9593690B2 (en) 2013-06-26 2017-03-14 Honeywell International Inc. Turbocharger with an annular rotary bypass valve
US20170234212A1 (en) * 2016-02-17 2017-08-17 Honeywell International Inc. Turbocharger with rotary bypass valve operable to selectively configure the turbine volute as single-scroll or twin-scroll
WO2018158849A1 (fr) * 2017-02-28 2018-09-07 三菱重工エンジン＆ターボチャージャ株式会社 Turbocompresseur d'échappement
WO2021192565A1 (fr) * 2020-03-24 2021-09-30 株式会社豊田自動織機 Turbocompresseur
US20220316349A1 (en) * 2019-07-09 2022-10-06 Cummins Ltd. Turbine assembly
IL287648B2 (en) * 2021-10-28 2023-06-01 Gregory KATS rotary engine

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0227473D0 (en) * 2002-11-25 2002-12-31 Leavesley Malcolm G Variable turbocharger apparatus with bypass apertures
AT501234B1 (de) * 2006-03-30 2008-02-15 Avl List Gmbh Abgasturbine für eine brennkraftmaschine
WO2007058647A1 (fr) * 2005-11-16 2007-05-24 Honeywell International Inc. Cartouche a piston coulissant et turbocompresseur dote d'une telle cartouche
EP2035673B1 (fr) 2006-06-19 2014-06-11 Turbo Energy Limited Mécanisme à aubes de stator à calage variable pour turbocompresseurs
US8123470B2 (en) * 2007-08-10 2012-02-28 Honeywell International Inc. Turbine assembly with semi-divided nozzle and half-collar piston
AT505407B1 (de) * 2007-08-16 2009-01-15 Ghm Engineering Abgasturbolader für eine brennkraftmaschine
US8070425B2 (en) * 2008-03-28 2011-12-06 Honeywell International Inc. Turbocharger with sliding piston, and having vanes and leakage dams
DE102009004890A1 (de) * 2009-01-16 2010-07-22 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
FR2968717B1 (fr) * 2010-12-14 2014-06-13 Faurecia Sys Echappement Carter de turbine pour turbocompresseur, turbine et turbocompresseur correspondants.
WO2014175765A1 (fr) * 2013-04-25 2014-10-30 Siemens Aktiengesellschaft Ensemble de buses de canal pour turbodétendeur centripète
DE112014003991B4 (de) 2013-10-10 2023-06-29 Ihi Charging Systems International Gmbh Hitzeschild für einen Abgasturbolader und Abgasturbolader sowie ein Verfahren zur Herstellung eines Hitzeschilds
SE539442C2 (sv) * 2014-09-12 2017-09-26 Scania Cv Ab Turbinarrangemang innefattande två inloppsledningar med var sina bypassledningar vars flödesareor är varierbara medelst en gemensam ventilkropp

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5231831A (en) * 1992-07-28 1993-08-03 Leavesley Malcolm G Turbocharger apparatus
US6165780A (en) * 1996-09-26 2000-12-26 National Institute Of Agrobiological Resources, Ministry Of Agriculture, Forestry And Fisheries Shuttle vector comprising a T-DNA Region and RI and RK2 origins of replication
US20030003585A1 (en) * 1996-09-26 2003-01-02 Shinji Kawasaki New high capacity binary shuttle vector

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2861774A (en) * 1950-02-16 1958-11-25 Alfred J Buchi Inlet control for radial flow turbines
CH668455A5 (en) * 1984-06-29 1988-12-30 Bbc Brown Boveri & Cie Exhaust turbocharger with adjustable inlet - has blade ring on sleeve sliding on cylindrical surface
DE69308377T2 (de) * 1992-05-21 1997-06-19 Alliedsignal Ltd Regelbarer Turbolader
DE4242494C1 (en) * 1992-12-16 1993-09-09 Mercedes-Benz Aktiengesellschaft, 70327 Stuttgart, De Adjustable flow-guide for engine exhaust turbocharger - has axially-adjustable annular insert in sectors forming different kinds of guide grilles supplied simultaneously by spiral passages
DE10212675B4 (de) * 2002-03-22 2006-05-18 Daimlerchrysler Ag Abgasturbolader in einer Brennkraftmaschine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5231831A (en) * 1992-07-28 1993-08-03 Leavesley Malcolm G Turbocharger apparatus
US6165780A (en) * 1996-09-26 2000-12-26 National Institute Of Agrobiological Resources, Ministry Of Agriculture, Forestry And Fisheries Shuttle vector comprising a T-DNA Region and RI and RK2 origins of replication
US20030003585A1 (en) * 1996-09-26 2003-01-02 Shinji Kawasaki New high capacity binary shuttle vector
US6794190B2 (en) * 1996-09-26 2004-09-21 National Institute Of Agrobological Sciences Method for producing a transformed plant with a high capacity binary shuttle vector
US6521408B1 (en) * 1997-09-25 2003-02-18 National Institute Of Agrobiological Sciences Method for assessing a function of a gene

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100172750A1 (en) * 2007-01-16 2010-07-08 Genius Air conditioning apparatus equipped with a compressor and a vortex
US20090164037A1 (en) * 2007-12-24 2009-06-25 Snecma Services Method of selecting an arrangement of sectors for a turbomachine nozzle
US8140308B2 (en) * 2007-12-24 2012-03-20 Snecma Services Method of selecting an arrangement of sectors for a turbomachine nozzle
US9447723B2 (en) * 2008-08-21 2016-09-20 Daimler Ag Multiple inlet exhaust gas turbocharged engine with an axially moveable and rotatable adjustment ring
US20110067397A1 (en) * 2008-08-21 2011-03-24 Torsten Hirth Internal combustion engine with an exhaust gas turbocharger
US8113770B2 (en) * 2009-02-03 2012-02-14 Honeywell International Inc. Turbine assembly for an exhaust gas-driven turbocharger having a variable nozzle
US20100196145A1 (en) * 2009-02-03 2010-08-05 Alain Lombard Turbine assembly for an exhaust gas-driven turbocharger having a variable nozzle
US20120031092A1 (en) * 2009-04-23 2012-02-09 Siegfried Sumser Internal combustion engine and method for operating an internal combustion engine
CN102071977A (zh) * 2009-10-06 2011-05-25 康明斯有限公司 涡轮机
US20110103938A1 (en) * 2009-10-06 2011-05-05 Holroyd Robert L Turbomachine
CN102770624A (zh) * 2009-10-06 2012-11-07 康明斯有限公司 涡轮机
US8747057B2 (en) * 2009-10-06 2014-06-10 Cummins Ltd. Turbomachine
US20140086725A1 (en) * 2011-08-15 2014-03-27 Wuxi Kaidi Supercharger Accessories Co., Ltd. Turbocharger with a double-vane nozzle system
DE102011121330A1 (de) * 2011-12-16 2013-06-20 Ihi Charging Systems International Gmbh Turbine für einen Abgasturbolader
CN103998724A (zh) * 2011-12-16 2014-08-20 Ihi供应系统国际有限责任公司 用于废气涡轮增压器的涡轮机
US9593690B2 (en) 2013-06-26 2017-03-14 Honeywell International Inc. Turbocharger with an annular rotary bypass valve
US9932886B2 (en) * 2016-02-17 2018-04-03 Honeywell International Inc. Turbocharger with rotary bypass valve operable to selectively configure the turbine volute as single-scroll or twin-scroll
CN107091146A (zh) * 2016-02-17 2017-08-25 霍尼韦尔国际公司 带有可操作来将涡轮机蜗壳选择性地构造成单蜗旋或双蜗旋的旋转旁通阀的涡轮增压器
US20170234212A1 (en) * 2016-02-17 2017-08-17 Honeywell International Inc. Turbocharger with rotary bypass valve operable to selectively configure the turbine volute as single-scroll or twin-scroll
US10890105B2 (en) 2017-02-28 2021-01-12 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Exhaust gas turbocharger
CN110050115A (zh) * 2017-02-28 2019-07-23 三菱重工发动机和增压器株式会社 排气涡轮增压器
JPWO2018158849A1 (ja) * 2017-02-28 2019-11-07 三菱重工エンジン＆ターボチャージャ株式会社 排気タービン過給機
EP3546720A4 (fr) * 2017-02-28 2020-01-01 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbocompresseur d'échappement
WO2018158849A1 (fr) * 2017-02-28 2018-09-07 三菱重工エンジン＆ターボチャージャ株式会社 Turbocompresseur d'échappement
US20220316349A1 (en) * 2019-07-09 2022-10-06 Cummins Ltd. Turbine assembly
US11891921B2 (en) * 2019-07-09 2024-02-06 Cummins Ltd Turbine assembly
WO2021192565A1 (fr) * 2020-03-24 2021-09-30 株式会社豊田自動織機 Turbocompresseur
JP2021152337A (ja) * 2020-03-24 2021-09-30 株式会社豊田自動織機 ターボチャージャ
JP7298525B2 (ja) 2020-03-24 2023-06-27 株式会社豊田自動織機 ターボチャージャ
IL287648B2 (en) * 2021-10-28 2023-06-01 Gregory KATS rotary engine

Also Published As

Publication number Publication date
WO2005040560A1 (fr) 2005-05-06
AU2003278524A1 (en) 2005-05-11
EP1725742A1 (fr) 2006-11-29

Similar Documents

Publication Publication Date Title
US20080038110A1 (en) Sector-Divided Turbine Assembly With Axial Piston Variable-Geometry Mechanism
US9708925B2 (en) Adjustable-trim centrifugal compressor, and turbocharger having same
US7305827B2 (en) Inlet duct for rearward-facing compressor wheel, and turbocharger incorporating same
US8123470B2 (en) Turbine assembly with semi-divided nozzle and half-collar piston
US8191367B2 (en) Sliding piston cartridge and turbocharger incorporating same
US7828517B2 (en) Variable-geometry turbocharger with asymmetric divided volute for engine exhaust gas pulse optimization
US8113770B2 (en) Turbine assembly for an exhaust gas-driven turbocharger having a variable nozzle
EP2762682B1 (fr) Turbine axiale avec logement de turbine divisé de manière méridienne
KR101905792B1 (ko) 펄스 분리형 가변 터빈 구조 터보차저를 위한 카트리지
WO2012060187A1 (fr) Carter de turbine pour turbocompresseur à double volute
US20050163606A1 (en) Centrifugal compressor with channel ring defined inlet recirculation channel
EP2762683B1 (fr) Turbine axiale avec carter de turbine divisé en secteurs
CN111133174B (zh) 用于涡轮机的涡轮的扩散器空间
EP2028347B1 (fr) Turbocompresseur avec ensemble de piston coulissant
US11319964B2 (en) Turbocharger and bearing housing therefor
JP2008045473A (ja) 可変容量ターボチャージャ

Legal Events

Date Code Title Description
AS Assignment

Owner name: HONEYWELL INTERNATIONAL, INC., NEW JERSEY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:ROBERTS, QUENTIN;BERNARDINI, LUCIANO;LOMBARD, ALAIN;AND OTHERS;REEL/FRAME:018967/0942;SIGNING DATES FROM 20070124 TO 20070128

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION