US20140099191A1 - Turbine for an exhaust gas turbocharger - Google Patents

Turbine for an exhaust gas turbocharger Download PDF

Info

Publication number
US20140099191A1
US20140099191A1 US14/106,745 US201314106745A US2014099191A1 US 20140099191 A1 US20140099191 A1 US 20140099191A1 US 201314106745 A US201314106745 A US 201314106745A US 2014099191 A1 US2014099191 A1 US 2014099191A1
Authority
US
United States
Prior art keywords
turbine
wall area
exhaust gas
wall
guide vane
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
US14/106,745
Other languages
English (en)
Inventor
Thorben Kotzbacher
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.)
IHI Charging Systems International GmbH
Original Assignee
IHI Charging Systems International GmbH
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 IHI Charging Systems International GmbH filed Critical IHI Charging Systems International GmbH
Assigned to IHI CHARGING SYSTEMS INTERNATIONAL GMBH reassignment IHI CHARGING SYSTEMS INTERNATIONAL GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KOTZBACHER, THORBEN
Publication of US20140099191A1 publication Critical patent/US20140099191A1/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
    • 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
    • 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
    • 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
    • F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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
    • 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 present invention relates to a turbine for an exhaust gas turbocharger including a turbine casing with a turbine wheel rotatably disposed therein and guide vanes which are adjustably supported for controlling the exhaust gas flow to the turbine wheel.
  • DE 10 2008 034 751 A1 discloses a turbocharger for a combustion engine with a turbine casing and a turbine comprising a turbine wheel arranged therein, wherein the turbine is equipped with adjustable guide vanes for varying a flow cross-section via which the exhaust gas is directed onto the turbine wheel.
  • a floating spacer ring is provided between the adjustable guide vanes and the turbine casing, which is in contact with the incoming exhaust gas via a pressure duct, and the rear side of which may be exposed to the exhaust gas.
  • a force resultant is generated which acts axially upon the spacer ring and pushes the spacer ring against the end faces of the guide vanes by this force resultant.
  • the guide vane structure includes vanes, which are pivotably supported relative to the turbine casing and form an axial inlet nozzle structure adjacent a wall portion of the turbine which extends along the guide vane structure, the wall portion comprising at least a first guide wall area which overlaps the guide vane structure, and which is set back relative to a second guide wall area in which the vanes are pivotably supported and which adjoins the first wall area.
  • Such a turbine for an exhaust gas turbocharger of a combustion engine comprises a turbine casing which at least partially defines an installation space in which a turbine wheel may be arranged so as to be rotatable about an axis of rotation relative to the turbine casing.
  • Exhaust gas of the combustion engine may be supplied to the installation space via at least one flow duct in which a guide vane structure is arranged which is movable relative to the turbine casing.
  • the flow duct is defined in the axial direction of the installation space and thus of the turbine wheel at least partially by at least one wall portion of the turbine which is at least partially overlapping the guide vane.
  • the second wall area is closer to the guide vane than the first wall area. Therefore, the wall areas do not extend in a common plane.
  • the wall areas extend e. g. in two different planes which are arranged in the axial direction on different levels, and which e. g. at least essentially extend parallel to each other and/or which e. g. at least essentially extend vertically to the axial direction.
  • the inventive turbine exhibits especially low friction and an improved variability or adjustability, respectively.
  • the guide vanes may be moved with very low friction and thus operate extremely smoothly, in order to variably establish proper flow conditions for the exhaust gas of the combustion engine entering the flow duct and to precisely adapt the vane positions to different operating points of the combustion engine. This results in an improved operability which keeps the fuel consumption and the CO 2 emission of the combustion engine low.
  • the guide vanes are, for example, pivotable about a pivot axis relative to the turbine casing in order to e. g. adjust a flow cross-section of the inlet flow duct for the exhaust gas. This means that the flow cross-section may be at least partially fluidly blocked or unblocked.
  • the inventive turbine Since the first wall area is set back relative to the second wall area, the inventive turbine exhibits extremely low friction when the guide vane is at least partially opened. This is accompanied by a low hysteresis which in turn enhances the efficient operation and a high efficiency of the turbine.
  • the inventive turbine in particular with opened guide vane, has an extremely high absorption capacity, so that a high exhaust gas mass flow may pass the turbine.
  • the inventive turbine allows a particularly efficient operation of the combustion engine and the realisation of particularly high power and/or torque values, because it permits an extremely high exhaust gas mass flow.
  • the turbine does not represent an undesired high flow resistance for the high exhaust gas mass flow, so that charge changing losses are kept particularly small. This enhances the fuel-efficient operation of the combustion engine and is accompanied by low CO 2 emission.
  • the inventive turbine further comprises a particularly advantageous controllability when installed on a combustion engine, so that the latter can be particularly efficiently operated. Moreover, no negative effects on the efficiency of the turbine and the exhaust gas turbocharger in low speed and/or load ranges occur, so that the inventive turbine provides for a fuel-efficient operation of the combustion engine almost in the entire operating range.
  • the inventive turbine may be employed for combustion engines in the form of gasoline engines or diesel engines, which are reciprocating engines. It may also be employed for other combustion engines which are operated e. g. with gaseous and/or liquid fuels.
  • the wall portion with the wall areas is arranged on the side facing the turbine wheel outlet area of the turbine of the guide vane.
  • the flow duct through the wall portion with the two appropriately formed wall areas is arranged on the side facing the turbine wheel outlet area of the turbine.
  • the first and second wall areas are joined via a third wall area of the wall portion, which is arranged between the first and second wall area.
  • the third wall area extends at an angle of essentially 90° max, each between the first and second wall area.
  • a transition area between the first and second wall area is formed essentially step-shaped.
  • the third wall area is formed essentially arc-shaped, in particular in the radial direction of the installation space thus of the turbine wheel. This enables favourable flow conditions for the exhaust gas through the flow duct. In particular, turbulences and/or other negative effects for an efficient flow of the exhaust gas into the installation space may be avoided. This contributes to a particularly high efficiency and a particularly efficient operation of the inventive turbine.
  • the appropriate design of the first and second wall area as well as, in particular, of the third wall area disposed therebetween has to be adapted to the corresponding requirements and applications.
  • the inventive turbine may be employed, for example, in a combustion engine for a passenger car as well as in a combustion engine for a commercial motor vehicle or another motor vehicle.
  • the first wall area extends at least in the radial direction of the installation space and thus of the turbine wheel at least to the level of the leading edge of a rotor blade of the turbine wheel.
  • the exhaust gas is conveyed to the rotor blade and thus the turbine wheel across the leading edge, with the leading edge extending e. g. at least essentially in the axial direction of the installation space and thus of the turbine wheel.
  • the second wall area adjoins the first wall area at least in the radial direction of the installation space and the turbine wheel. This means that starting from the installation space towards the flow duct, at first the first wall area is provided followed by the second wall area. This contributes to a particularly high efficiency of the inventive turbine.
  • the wall portion is formed by a cover element, in particular a cover plate, of the turbine, which is an insert component which is formed separately from the turbine casing is arranged at least partially in the installation space and by means of which at least one leading edge, in particular a blade edge of the rotor blade of the turbine wheel which is at least partially arranged in the installation space may be at least partially covered or is covered, respectively.
  • the provision of the insert component enables a particularly simple and cost-efficient manufacture and assembly of the inventive turbine, which keeps the costs of the entire combustion engine low.
  • the guide vane is held movable, in particular pivotable, about the pivot axis, on the cover element relative to the turbine casing and the cover element. This enhances a simple and cost-efficient assembly of the inventive turbine.
  • the cover element has a cover contour by means of which the leading edge, in particular the blade edge, is at least partially covered and which is formed at least partially as an at least essentially corresponding complementary contour to the outer contour of the leading edge.
  • a particularly advantageous cover of the leading edge, in particular of the blade edge may be realized.
  • This generates particularly advantageous flow conditions for the exhaust gas flowing to and flowing off the turbine wheel or its rotor blades, respectively.
  • the inventive turbine exhibits a particularly efficient operation and a particularly high efficiency, which enhances an efficient and fuel-efficient operation of the combustion engine.
  • the guide vanes are supported by a retaining component which is formed separately from the turbine casing, in particular on a nozzle ring, wherein the retaining component is an insert component, which is accommodated in the turbine casing.
  • FIG. 1 is an axial cross-sectional view of part of an exhaust gas internal combustion engine
  • FIG. 2 is another and enlarged schematic longitudinal sectional view showing portions of the exhaust gas turbocharger according to FIG. 1 ;
  • FIG. 3 shows portions of a schematic longitudinal sectional view of still another embodiment of the exhaust gas turbocharger according to FIG. 2 ;
  • FIG. 4 shows portions of a schematic longitudinal sectional view of another embodiment of the exhaust gas turbocharger according to FIGS. 2 and 3 .
  • FIG. 1 shows an exhaust gas turbocharger 10 for a combustion engine which is in the form for example of a reciprocating piston engine.
  • the exhaust gas turbocharger 10 comprises a turbine 12 with a turbine casing 14 which houses a turbine wheel 20 and comprises a spiral duct 16 through which the exhaust gas of the combustion engine is supplied to the turbine wheel 20 .
  • the spiral duct 16 is fluidly connected with at least one cylinder of the combustion engine so that exhaust gas from the cylinder may enter the spiral duct 16 .
  • the turbine casing 14 also at least partially defines an installation space 18 in which the turbine wheel 20 of the turbine 12 is accommodated.
  • the turbine wheel 20 is arranged in the installation space 18 and rotatable about an axis of rotation 22 relative to the turbine casing 14 .
  • the turbine wheel 20 is part of a rotor 24 of the exhaust gas turbocharger 10 , which comprises a shaft 26 .
  • the turbine wheel 20 is non-rotatably connected to the shaft 26 which is r supported in a bearing housing 28 of the exhaust gas turbocharger 10 so as to be rotatable about the axis of rotation 22 relative to the turbine casing 12 and the bearing housing 28 .
  • the turbine casing 14 and the bearing housing 28 are connected to each other.
  • the rotor 24 also comprises a compressor wheel 30 of a compressor 32 of the exhaust gas turbocharger 10 .
  • the compressor wheel 30 is also non-rotatably connected to the shaft 26 .
  • the compressor 32 comprises a compressor casing 34 which is also securely connected to the bearing housing 28 and by which an installation space 36 is at least partially defined in which the compressor wheel 30 which is supported rotatably about the axis of rotation 22 relative to the compressor casing 34 is at least partially accommodated.
  • the exhaust gas flowing through the spiral duct 16 is guided by the spiral duct 16 to a nozzle 38 of the turbine 12 , via which the exhaust gas may flow at least essentially in the radial direction to, and impinge on, the turbine wheel 20 .
  • This is indicated in FIG. 1 by a direction arrow 40 .
  • the turbine wheel 20 comprises a hub body 42 provided with a plurality of rotor blades 44 .
  • the rotor blades 44 are arranged at least essentially equally spaced about the circumference of the turbine wheel 20 and securely connected to the hub body 42 .
  • FIG. 1 shows only one of the pluralities of rotor blades 44 .
  • the rotor blade 44 comprises a leading edge 46 which extends at least essentially in the axial direction, via which the turbine wheel 20 is exposed to the exhaust gas flow.
  • the rotor blade 44 further has a blade edge 48 and a trailing edge 50 via which the exhaust gas may flow off the turbine wheel 20 or the rotor blade 44 , respectively.
  • the exhaust gas flows across the leading edge 46 onto the turbine wheel 20 or its rotor blades 44 , respectively, and flows off at least essentially past the trailing edge 50 into a turbine wheel outlet area 52 .
  • the radial direction of the installation space 18 and thus of the turbine wheel 20 or of the turbine 12 , respectively, is indicated in FIG. 1 by a direction arrow 54
  • the axial direction is indicated by a direction arrow 56 in FIG. 1 .
  • the turbine wheel 20 rotates about the axis of rotation 22 , which in turn rotates the shaft 26 as well as the compressor wheel 30 about the axis of rotation 22 .
  • the turbine 12 is a radial turbine and drives the compressor 32 , which is a radial compressor that takes in and compresses air.
  • the sucked-in air flows across a leading edge 58 of a compressor blade 60 of the compressor wheel 30 and flows off across a trailing edge 62 of the compressor blade 60 .
  • the compressed air is then guided through a compressor spiral duct 64 which is formed by the compressor casing 34 to the at least one cylinder of the combustion engine.
  • the nozzle 38 extension in the axial direction of the turbine 12 or of the installation space 18 , respectively, (direction arrow 56 ) at the side facing the bearing housing 28 is delimited at least partially by a nozzle ring 66 .
  • the nozzle ring 66 is formed as a separate insert component relative to the turbine casing 14 and accommodated in the turbine casing 14 .
  • a mounting ring 68 is provided, by which the nozzle ring 66 is retained.
  • the mounting ring 68 is arranged in the axial direction between the turbine casing 14 and the bearing housing 28 and clamped between them. In this manner, the nozzle ring 66 may be indirectly supported by the turbine casing 14 via the mounting ring 68 in a spaced relationship to turbine casing 14 and secured relative thereto.
  • the nozzle 38 is at least partially defined by a cover plate 70 .
  • the cover plate 70 is in the form of an insert component separate from the turbine casing 14 and arranged at least partially in the installation space 18 .
  • the cover plate 70 acts as wall portion which delimits the nozzle 38 in the axial direction of the installation space 18 and thus of the turbine 12 at the side facing the turbine wheel outlet area 52 .
  • guide vanes 72 are supported in the turbine casing 14 between the cover plate 70 and the nozzle ring 66 so as to be pivotable about an axis 76 , which extends at least essentially in the axial direction and thus essentially parallel to the axis of rotation 22 .
  • This allows a variable adjustment of the flow cross-section of the nozzle 38 , through which the exhaust gas of the combustion engine flows from the spiral duct 16 to the turbine wheel 20 .
  • This permits to adjust the turbine 12 to different operating or load points, respectively, of the combustion engine as required, so that the turbine 12 and thus the entire exhaust gas turbocharger 10 may be operated particularly efficiently.
  • the trailing edge 48 of the rotor blade 44 is at least partially, in particular completely, covered or overlapped by the cover plate 70 .
  • the exhaust gas can therefore mainly, in particular exclusively, flow off the rotor blade 44 across the trailing end 50 . This provides for particularly advantageous flow conditions for the exhaust gas entering the turbine wheel 20 .
  • the cover plate 70 comprises an outer contour 74 around the trailing edge 48 which at least essentially corresponds to the shape of the blade edge 48 .
  • the pivot axis 76 can be seen, about which the guide vane 72 may be pivoted.
  • the guide vane 72 is supported pivotably about the pivot axis 76 by the cover plate 70 and the nozzle by bearing journals 78 connected to the guide vane.
  • the bearing journals 78 are seated at least partially in corresponding seats of the cover plate 70 and the nozzle ring 66 .
  • the cover plate 70 comprises, in the radial direction of the turbine 12 starting from the axis of rotation 22 , a first wall area 80 as well as a second wall area 82 adjoining the first wall area in the radial direction.
  • the first wall area 80 which in the axial direction at least partially overlaps the guide vane 72 is set back relative to the second wall area 82 which in the axial direction at least partially overlaps the guide vane 72 .
  • the first wall area 80 extends in the radial inward direction at least essentially to the same level as the leading edge 46 of the rotor blade 44 .
  • the turbine 12 exhibits an extremely low hysteresis, in particular when the guide vane 72 is at least partially opened that is in a position which opens the flow cross-section of the nozzle 38 partially.
  • the first wall area 80 and the second wall area 82 are joined via a third wall area 84 , wherein the third wall area 84 is arranged between the first wall area 80 and the second wall area 82 .
  • the third wall area 84 extends at an angle of essentially 90° each between the first wall area 80 and second wall area 82 . This means that the first wall area 80 , the second wall area 82 and the third wall area 84 are arranged and formed at least essentially step-shaped.
  • FIG. 3 shows an exemplary embodiment of the exhaust gas turbocharger 10 different from that of FIGS. 1 and 2 ,
  • the third wall area 84 according to FIG. 2 extends essentially parallel to the axial direction (direction arrow 56 ) and includes an angle of essentially 90° with the radial direction (direction arrow 54 )
  • the third wall area 84 according to FIG. 3 extends obliquely to the axial direction at an angle with the radial direction different from 90°.
  • the third wall area 84 includes an angle different from 90° both with respect to the first wall area 80 and the second wall area 82 .
  • the third wall area 84 is formed straight, i. e. not arc-shaped, round or the like.
  • FIG. 4 shows still another exemplary embodiment of the exhaust gas turbocharger 10 according to FIGS. 1 to 3 .
  • the third wall area 84 is formed at least essentially arc-shaped in the radial direction (direction arrow 54 ).
  • first wall area 80 , the second wall area 82 and the third wall area 84 may be adapted to the requirements and particular applications.
  • the respective radial extension (length) and/or axial extension (depth of the first wall area 80 , the second wall area 82 and the third wall area 84 ) may be appropriately dimensioned and varied and deviate from the corresponding extensions shown in FIGS. 2 to 4 .
  • contours of the first wall area 80 , the second wall area 82 and the third wall area 84 may be provided which are different from those shown in FIGS. 2 to 4 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)
US14/106,745 2011-07-20 2013-12-14 Turbine for an exhaust gas turbocharger Abandoned US20140099191A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102011108195.3A DE102011108195B4 (de) 2011-07-20 2011-07-20 Turbine für einen Abgasturbolader
DE102011108195.3 2011-07-20
PCT/EP2012/002637 WO2013010617A1 (de) 2011-07-20 2012-06-22 Turbine für einen abgasturbolader

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2012/002637 Continuation-In-Part WO2013010617A1 (de) 2011-07-20 2012-06-22 Turbine für einen abgasturbolader

Publications (1)

Publication Number Publication Date
US20140099191A1 true US20140099191A1 (en) 2014-04-10

Family

ID=46458422

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/106,745 Abandoned US20140099191A1 (en) 2011-07-20 2013-12-14 Turbine for an exhaust gas turbocharger

Country Status (6)

Country Link
US (1) US20140099191A1 (de)
EP (1) EP2734709A1 (de)
JP (1) JP5890021B2 (de)
CN (1) CN103703219B (de)
DE (1) DE102011108195B4 (de)
WO (1) WO2013010617A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013104414A (ja) * 2011-11-16 2013-05-30 Toyota Motor Corp ターボチャージャ
US20180171825A1 (en) * 2016-12-21 2018-06-21 Man Diesel & Turbo Se Turbocharger having a nozzle ring centered by a guiding projection
US20190288517A1 (en) * 2018-03-16 2019-09-19 Uop Llc Consolidation and use of power recovered from a turbine in a process unit
US20250198296A1 (en) * 2022-03-22 2025-06-19 Accelleron Switzerland Ltd. Nozzle ring for a radial turbine, exhaust turbine, and turbocharger

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12329373B2 (en) 2011-05-02 2025-06-17 Biomet Sports Medicine, Llc Method and apparatus for soft tissue fixation
US20170044925A1 (en) * 2014-04-22 2017-02-16 Borgwarner Inc. Turbocharger turbine with variable nozzle
EP3164578B1 (de) * 2014-07-03 2020-06-03 ABB Turbo Systems AG Abströmbereich einer turbine eines abgasturboladers
US9932888B2 (en) * 2016-03-24 2018-04-03 Borgwarner Inc. Variable geometry turbocharger
DE102017127421A1 (de) * 2017-11-21 2019-05-23 Man Energy Solutions Se Radialverdichter
EP3705697B1 (de) * 2017-12-20 2022-02-02 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbine und turbolader
DE102018115448A1 (de) * 2018-06-27 2020-01-02 Ihi Charging Systems International Gmbh Abgasturbolader
DE102018221812B4 (de) * 2018-12-14 2021-08-19 Vitesco Technologies GmbH Abgasturbine mit einer Abgasleiteinrichtung für einen Abgasturbolader und Abgasturbolader

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6012630U (ja) * 1983-07-05 1985-01-28 三菱自動車工業株式会社 可変ノズルベ−ン付タ−ボ過給機
JPS6137404U (ja) * 1984-08-09 1986-03-08 トヨタ自動車株式会社 可変ベ−ン付排気過給機
US4643640A (en) * 1984-04-20 1987-02-17 The Garrett Corporation Gas seal vanes of variable nozzle turbine
US4654941A (en) * 1984-04-20 1987-04-07 The Garrett Corporation Method of assembling a variable nozzle turbocharger
JP2002038965A (ja) * 2000-07-28 2002-02-06 Toyota Motor Corp 可変容量型ターボチャージャ
JP2003027951A (ja) * 2001-07-12 2003-01-29 Ishikawajima Harima Heavy Ind Co Ltd 可変容量型過給機の流量増加構造
JP2008184971A (ja) * 2007-01-30 2008-08-14 Ihi Corp 可変容量型過給機
DE102008000543A1 (de) * 2008-03-06 2009-09-10 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader mit variabler Turbinengeometrie
US7628580B2 (en) * 2004-04-08 2009-12-08 Holset Engineering Company, Limited Variable geometry turbine
US7794200B2 (en) * 2003-05-08 2010-09-14 Honeywell International, Inc. Turbocharger with a variable nozzle device
US20100310365A1 (en) * 2008-02-20 2010-12-09 Ihi Corporation Turbocharger
US20110120124A1 (en) * 2009-11-24 2011-05-26 Klaus Czerwinski Exhaust gas turbocharger
US20140341729A1 (en) * 2011-11-30 2014-11-20 Mitsubishi Heavy Industries Ltd. Radial turbine

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH057461Y2 (de) * 1986-03-20 1993-02-25
US4907952A (en) * 1986-12-05 1990-03-13 Honda Giken Kogyo Kabushiki Kaisha Turbocharger
JPS63183207A (ja) * 1987-01-23 1988-07-28 Honda Motor Co Ltd 可変容量式タ−ビン
US5851104A (en) * 1997-12-15 1998-12-22 Atlas Copco Rotoflow, Inc. Nozzle adjusting mechanism
DE19838928C1 (de) * 1998-08-27 1999-04-22 Daimler Chrysler Ag Variabel einstellbares Leitschaufelgitter
DE102004023214A1 (de) * 2004-05-11 2005-12-08 Volkswagen Ag Abgasturbolader für eine Brennkraftmaschine mit variabler Turbinengeometrie
JP4952558B2 (ja) * 2007-12-12 2012-06-13 株式会社Ｉｈｉ ターボチャージャ
DE102008005658A1 (de) * 2008-01-23 2009-07-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
JP4983693B2 (ja) * 2008-03-31 2012-07-25 株式会社Ｉｈｉ 過給機
DE102008001736A1 (de) * 2008-05-14 2009-11-19 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader für eine Brennkraftmaschine
DE102008034751A1 (de) 2008-07-24 2010-01-28 Benteler Automobiltechnik Gmbh Turbolader mit verstellbarer Turbinengeometrie
EP2351920B1 (de) * 2008-11-05 2016-04-13 IHI Corporation Turbolader
JP2010127093A (ja) * 2008-11-25 2010-06-10 Ihi Corp ターボチャージャ

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6012630U (ja) * 1983-07-05 1985-01-28 三菱自動車工業株式会社 可変ノズルベ−ン付タ−ボ過給機
US4643640A (en) * 1984-04-20 1987-02-17 The Garrett Corporation Gas seal vanes of variable nozzle turbine
US4654941A (en) * 1984-04-20 1987-04-07 The Garrett Corporation Method of assembling a variable nozzle turbocharger
JPS6137404U (ja) * 1984-08-09 1986-03-08 トヨタ自動車株式会社 可変ベ−ン付排気過給機
JP2002038965A (ja) * 2000-07-28 2002-02-06 Toyota Motor Corp 可変容量型ターボチャージャ
JP2003027951A (ja) * 2001-07-12 2003-01-29 Ishikawajima Harima Heavy Ind Co Ltd 可変容量型過給機の流量増加構造
US7794200B2 (en) * 2003-05-08 2010-09-14 Honeywell International, Inc. Turbocharger with a variable nozzle device
US7628580B2 (en) * 2004-04-08 2009-12-08 Holset Engineering Company, Limited Variable geometry turbine
JP2008184971A (ja) * 2007-01-30 2008-08-14 Ihi Corp 可変容量型過給機
US20100310365A1 (en) * 2008-02-20 2010-12-09 Ihi Corporation Turbocharger
DE102008000543A1 (de) * 2008-03-06 2009-09-10 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader mit variabler Turbinengeometrie
US20110120124A1 (en) * 2009-11-24 2011-05-26 Klaus Czerwinski Exhaust gas turbocharger
US20140341729A1 (en) * 2011-11-30 2014-11-20 Mitsubishi Heavy Industries Ltd. Radial turbine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013104414A (ja) * 2011-11-16 2013-05-30 Toyota Motor Corp ターボチャージャ
US20180171825A1 (en) * 2016-12-21 2018-06-21 Man Diesel & Turbo Se Turbocharger having a nozzle ring centered by a guiding projection
US10677099B2 (en) * 2016-12-21 2020-06-09 Man Energy Solutions Se Turbocharger having a nozzle ring centered by a guiding projection
US20190288517A1 (en) * 2018-03-16 2019-09-19 Uop Llc Consolidation and use of power recovered from a turbine in a process unit
US10811884B2 (en) * 2018-03-16 2020-10-20 Uop Llc Consolidation and use of power recovered from a turbine in a process unit
US20250198296A1 (en) * 2022-03-22 2025-06-19 Accelleron Switzerland Ltd. Nozzle ring for a radial turbine, exhaust turbine, and turbocharger
US12553355B2 (en) * 2022-03-22 2026-02-17 Accelleron Switzerland Ltd. Nozzle ring for a radial turbine, exhaust turbine, and turbocharger

Also Published As

Publication number Publication date
JP2014521009A (ja) 2014-08-25
JP5890021B2 (ja) 2016-03-22
CN103703219B (zh) 2016-05-11
WO2013010617A1 (de) 2013-01-24
EP2734709A1 (de) 2014-05-28
DE102011108195B4 (de) 2022-10-27
DE102011108195A1 (de) 2013-01-24
CN103703219A (zh) 2014-04-02

Similar Documents

Publication Publication Date Title
JP5890021B2 (ja) 排気ガスターボチャージャーのタービン
US8844282B2 (en) Exhaust-gas turbocharger having a ball-cock waste-gate valve with a stress-relieved crank arm
KR101306360B1 (ko) 가변 용량형 배기 터보과급기
EP2107250B1 (de) Verdichter mit zwei Rücken an Rücken montierten Laufrädern und entsprechender Turbolader
US9932843B2 (en) Double flow turbine housing turbocharger
JP5609795B2 (ja) 車両用過給装置
JP3851923B2 (ja) 内燃エンジン用排気ガスターボチャージャー
KR20110098761A (ko) 베인 링들을 구비한 간단한 가변 기하형상 터보차저
US10808569B2 (en) Turbocharger
JP2009534569A (ja) 調節可能なタービン形状と羽根保持リングの圧力補償開口部を有するターボチャージャ
US20110131976A1 (en) Exhaust gas turbocharger for an internal combustion engine
CN105587403B (zh) 废气涡轮增压器和内燃机
US9759164B2 (en) Fluid energy machine, in particular for an exhaust gas turbocharger of an automobile
CN111148903A (zh) 用于内燃发动机的增压装置的具有虹膜式隔板机构的径流式压缩机、增压装置和虹膜式隔板机构的叶片
CN107109954B (zh) 涡轮增压器和制造涡轮增压器的方法
US20160024999A1 (en) Turbine housing with dividing vanes in volute
US9752457B2 (en) Turbine housing for a turbocharger
US11255252B2 (en) Radial compressor for a charging device of an internal combustion engine, charging device and lamellas for an iris diaphragm mechanism, and method for producing such lamella
US9121345B2 (en) Turbine for an exhaust turbocharger of an internal combustion engine
JP2013245562A (ja) ターボチャージャ
US9140134B2 (en) Guide vane for a turbo-compressor, guide vane arrangement, turbo-compressor, motor vehicle and method
JP2005240569A (ja) 作動流体還流路を有する過給用コンプレッサ
JP5954292B2 (ja) ターボチャージャ
US10018164B2 (en) Gas compressor pressure relief noise reduction
WO2011015908A1 (en) Variable geometry turbine

Legal Events

Date Code Title Description
AS Assignment

Owner name: IHI CHARGING SYSTEMS INTERNATIONAL GMBH, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:KOTZBACHER, THORBEN;REEL/FRAME:032081/0139

Effective date: 20131113

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: FINAL REJECTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: ADVISORY ACTION MAILED

STCB Information on status: application discontinuation

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