WO2013107610A1 - Dispositif de guidage conçu pour une turbine d'un turbocompresseur à gaz d'échappement et turbine correspondante - Google Patents

Dispositif de guidage conçu pour une turbine d'un turbocompresseur à gaz d'échappement et turbine correspondante Download PDF

Info

Publication number
WO2013107610A1
WO2013107610A1 PCT/EP2013/000020 EP2013000020W WO2013107610A1 WO 2013107610 A1 WO2013107610 A1 WO 2013107610A1 EP 2013000020 W EP2013000020 W EP 2013000020W WO 2013107610 A1 WO2013107610 A1 WO 2013107610A1
Authority
WO
WIPO (PCT)
Prior art keywords
guide
insert
turbine
vane
exhaust gas
Prior art date
Application number
PCT/EP2013/000020
Other languages
German (de)
English (en)
Inventor
Thomas Ihli
Manfred GUTHÖRLE
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
Priority to JP2014552560A priority Critical patent/JP2015505004A/ja
Priority to EP13704874.0A priority patent/EP2805028A1/fr
Priority to CN201380005789.3A priority patent/CN104053863B/zh
Publication of WO2013107610A1 publication Critical patent/WO2013107610A1/fr
Priority to US14/324,197 priority patent/US20140321991A1/en

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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting

Definitions

  • the invention relates to a guide for a turbine of an exhaust gas turbocharger specified in the preamble of claim 1.
  • Such a guide is known from EP 2 226 484 A1.
  • the guide is inserted into a turbine housing of a turbine of an exhaust gas turbocharger and comprises an insert element with a first insert part and a second insert part.
  • the first insert part is arranged in the axial direction of the turbine relative to the second insert part.
  • the guide comprises at least a first vane.
  • the guide vane serves to discharge exhaust gas flowing through the turbine so that the exhaust gas can flow in a streamlined manner to a turbine wheel of the turbine arranged downstream of the guide vane.
  • the guide vane is arranged between the insert parts and rotatably supported at least at one of the insert parts about an axis of rotation relative to the insert parts.
  • Such a guide for a turbine of an exhaust gas turbocharger comprises a
  • Insert element with a first insert part and with a second insert part.
  • the first insert part is arranged opposite the second insert part.
  • the guide device further comprises at least one first guide vane for discharging exhaust gas flowing through the turbine.
  • the vane is disposed between the opposing insert members and rotatably supported on at least one of the insert members about an axis of rotation relative to the insert members.
  • At least one second guide vane for discharging the exhaust gas which is immovable relative to the insert parts, i. is fixed.
  • Turbine wheel of the turbine resulting in a particularly efficient operation of the turbine and thus the exhaust gas turbocharger result.
  • This also has an effect on an efficient operation of an internal combustion engine assigned to the turbine, resulting in particularly low fuel consumption and low CO 2 emissions.
  • the guide device according to the invention by means of the first guide vane allows the turbine to be adapted to different exhaust gas mass flows as needed.
  • the first guide vane is rotated relative to the insert parts about the axis of rotation, which is accompanied by an adjustment or adjustment of an effective flow cross section of the guide device to be flowed through by the exhaust gas and thus of the turbine.
  • the effective flow cross section can be set variably, so that the turbine or its turbine wheel can be efficiently driven by the exhaust gas both at relatively low exhaust gas mass flows and when the exhaust gas mass flows are high.
  • At least one of the insert parts and the second guide blade are each formed at least partially in one piece with each other.
  • at least one of Insert members is formed from at least two interconnectedêtzzeilmaschineen, wherein one of theêtzzeil stainede and the second vane are integrally formed with each other.
  • the second vane can be formed from at least two interconnected blade sections, wherein one of the blade sections is formed integrally with at least one of the insert parts or with one of the insert sections.
  • At least one of the insert parts or both insert parts and the second guide vane is possible for at least one of the insert parts or both insert parts and the second guide vane to be formed completely in one piece with one another.
  • the guide is thus time and cost produced.
  • the guide has thereby also only a very small number of parts, so that they can be mounted very easily and inexpensively and used in a turbine housing of the turbine.
  • the guide vanes have at least substantially the same or similar, transient and heat-related deformation behavior, so that the risk of malfunction of the first guide blade, in particular as a result of jamming of the first guide blade with the insert parts, is particularly low. This comes the
  • the at least two insert sections for forming the at least one insert part and / or the at least two blade sections are provided for forming the second guide vane, this is advantageous insofar as the insert sections and / or the
  • Blade sections can be formed from mutually different materials. In other words, it is thereby possible to be able to produce the at least one insert part and / or the second guide vane from mutually different materials.
  • the guide device according to the invention can be used in turbines for internal combustion engines, as a diesel engine, gasoline engine, Diesottomotor or otherwise
  • the guide device according to the invention can be used in particular in radial turbines, in which the turbine wheel is at least substantially flows in the axial direction of exhaust gas. Equally possible is the use of the guide according to the invention in so-called mixed-flow turbines, in which the turbine wheel is flowed obliquely to the axial direction and obliquely to the radial direction of the exhaust gas. Another advantage of each at least partially integral design
  • At least one of the inserts with the second vane is that no additional welding processes for connecting the at least one insert member to the second vane are needed. Thereby, a heat input and thus a possibly occurring due to the heat input distortion of the guide can be avoided.
  • At least one of the insert parts and the second vane are each formed at least partially integrally with each other by means of a casting process.
  • the casting process allows the time-consuming and cost-effective, one-piece production.
  • the second vane can be produced for example as a three-dimensional blading.
  • the first vane can also be designed as a three-dimensional blading.
  • the first guide vane is mounted on at least one of the insert parts via at least one bearing element which is rotatable relative to the insert parts and is formed separately from the first vane and at least partially received in a receiving opening of the at least one of the insert parts.
  • the second guide blade and the first guide blade and / or the second guide blade and at least one of the insert parts are each formed at least partially from mutually different materials.
  • the deformation behavior can be specifically influenced and adjusted, since the different materials, in particular due to different
  • the receiving opening is formed as a passage opening, wherein the bearing element of one of the first
  • Passage opening can be inserted.
  • the first vane between the inserts is arranged as part of the assembly of the guide initially. Subsequently, the bearing element of the side facing away from the first vane side of the at least one insert part inserted into the passage opening or through the passage opening and so stored the first vane in a simple manner to the at least one of the insert parts.
  • the bearing element is received in a further receiving opening of the first vane.
  • the bearing element is inserted into the further receiving opening.
  • the assembly of the first vane on the inserts or on the at least one of the inserts is carried out by simply inserting the bearing element through the through hole and by simply inserting the bearing element in the further receiving opening of the first vane.
  • This storage of the first vane on the at least one of the inserts also avoids undesirably large openings in the inserts, which could lead to undesirable flow losses.
  • an anti-rotation device by means of which the first vane is secured against relative rotation to the bearing element.
  • the first vane can be rotated in a simple manner relative to the inserts about the axis of rotation by the bearing element is rotated about the axis of rotation.
  • the first vane can thereby be coupled in a simple manner via the bearing element to an actuator for rotating the first vane relative to the insert parts.
  • the anti-twist device preferably comprises an outer contour of the bearing element of a different shape and a circular contour with the outer contour in the
  • the outer contour and the inner contour each have an at least substantially wedge-shaped cross section.
  • Fig. 1 is a schematic plan view of a guide for a turbine of a
  • Fig. 2 is a schematic sectional view of the guide device according to Fig. 1;
  • FIGS. 1 and 2 shows a schematic sectional view of a turbine of an exhaust gas turbocharger with a further embodiment of the guide device according to FIGS. 1 and 2;
  • Fig. 4 is a schematic sectional view of another embodiment of the
  • FIG. 5 is a schematic sectional view of another embodiment of the
  • FIG. 7 shows a detail of a schematic front view of the guide device according to FIG. 6;
  • FIG. 8 shows a schematic sectional view of a turbine of an exhaust gas turbocharger with a further embodiment of the guide device according to FIG. 6;
  • FIGS. 1 and 2 show a guide device 10 for a turbine, not shown in FIGS. 1 and 2, of an exhaust gas turbocharger of an internal combustion engine.
  • Internal combustion engine is designed for example as a reciprocating internal combustion engine in the form of a gasoline engine, diesel engine, Diesottomotors or otherwise combustion engine.
  • the turbine designed as a radial turbine comprises a turbine housing with a receiving space in which a turbine wheel is at least partially accommodated.
  • the turbine wheel is rotatable about an axis of rotation relative to the turbine housing.
  • the turbine housing has at least one flow channel, via which exhaust gas of the internal combustion engine can be fed to the turbine wheel.
  • the exhaust gas may flow and thereby drive the turbine wheel via impeller vanes of the turbine wheel.
  • the guide 10 comprises first guide vanes 12 and second guide vanes 14, which are arranged in the flow channel and which can discharge the exhaust gas. By discharging the exhaust gas, this flows to the impeller blades under particularly favorable flow angles.
  • the guide device 10 comprises an insert element 15 with a first insert part 16 and with a second insert part 18.
  • the first insert part 16 is arranged in the axial direction of the turbine relative to the second insert part 18.
  • the guide vanes 12, 14 are arranged between the inserts 16, 18.
  • the insert parts 16, 18 and the relative to the insert parts 16, 18 fixed second guide vanes 14 are integrally formed with each other, for example by means of a casting process.
  • the casting process may be an MIM process (MIM - Metal Injection Molding), in particular a powder injection molding process.
  • the first vanes 12 are also disposed between the inserts 16, 18 but rotatable relative to the inserts 16, 18 about respective axes of rotation 20.
  • the first guide vanes 12 are rotatably supported by means of respective shafts 22 on the first insert part 16 about the axis of rotation 20 relative to the insert parts 16, 18. This means that the shafts 22 are rotatably connected about the axes of rotation 20 relative to the inserts 16, 18 but rotatably connected to the first guide vanes 12.
  • the shafts 22 are partially received in respective first receiving openings 24 of the first guide vanes 12. Furthermore, the shafts 22 are in respective passage openings 26 of the first insert part 16
  • the passage openings 26 and the separate configuration of the shafts 22 of the first guide vanes 12 allows a simple and thus time and cost-effective installation of the first guide vanes 12 on the insert element 15.
  • the first guide vanes 12 between the inserts 16, 18 are arranged so that the
  • the shafts 22 are inserted in a simple manner from a side 28, facing away from the first guide blades 12, of the first insert part 16 through the passage openings 26 and into the first receiving openings 24.
  • the advantages of the guide 10 are, in particular, that the relative to the inserts 16, 18 fixed and integrally formed with the inserts 16, 18, second guide vanes 14 and the rotatable relative to the inserts 16, 18, first vanes 12 at least almost the same transient , heat-related
  • Guide 10 in particular due to jamming of the first vanes 12 with the inserts 16, 18 is particularly low. In other words, the guide 10 and thus the turbine on a very high functional performance security.
  • Another advantage is that due to the integral formation of the inserts 16, 18 with the second vanes 14 additional joining methods, such as
  • Receiving openings 24 of the first guide vanes 12 are received, a respective outer contour, which are formed differently by a circle.
  • Guide vanes 12 recorded partial areas out of round.
  • the respective outer contours are at least substantially wedge-shaped.
  • the first vanes 12 have respective ones, the first ones
  • Receiving openings 24 delimiting inner contours, which as with the
  • the second insert part 18 is also referred to as a cover element or as a counter contour element or contour element, since it is at least partially a counter contour which at least substantially corresponds to an outer contour of the turbine wheel and which covers or covers the turbine wheel in particular in the radial direction. As a result, the exhaust gas driving the turbine wheel can be streamlined from the turbine wheel and introduced into a turbine outlet.
  • the second insert part 18 is at least substantially annular.
  • the first insert 16 is also referred to as a valve ring, since it is at least in
  • first vanes 12 act as valve elements.
  • an effective flow cross-section of the turbine, via which the exhaust gas is supplied to the turbine wheel, can be set, that is, fluidically released or narrowed in comparison thereto.
  • the turbine housing of the turbine is partially visible and designated 30.
  • the insert parts 16, 18 and the second guide vanes 14 are formed separately according to FIG. 3 from each other and firmly connected to each other.
  • the second guide vanes 14 are welded to the second insert part 18 while forming respective weld seams 32 with the first insert part 16 and forming respective, further weld seams 34.
  • the second guide vanes 14 have respective pins 36, which in as
  • a sealing element 40 is provided, which is supported on the one hand on the turbine housing 30 and on the other hand on the second insert part 18.
  • Sealing member 40, the second insert part 18 is sealed to the turbine housing 30, so that the exhaust gas at least substantially not between the
  • Guide device 10 can flow past but at least substantially completely fed via the guide vanes 12, 14 to the turbine wheel and thereby derived aerodynamically favorable or diverted.
  • the second insert part 18 has a receptacle in the present case in the form of an annular groove 41, in which the sealing element 40 partially
  • the second guide vanes 14 are welded to the inserts 16, 18 to form the welds 32, 34.
  • the second guide vanes 14 comprise further pins 42, which are at least partially received in respective, third receiving openings 44 of the first insert part 16.
  • the third receiving openings 44 are present as
  • the second guide vanes 14 and the first insert part 16 are at least partially received in the second receiving openings 38 via their pins 36 and welded to the second insert part 18 to form the weld seams 34 and thereby are connected cohesively.
  • the second insert part 18 of the guide device 10 is composed of a first insert section 46 and a second insert section
  • Insert portion 48 is formed, wherein the insert portions 46, 48 in the present case are interconnected by means of a positive plug connection. Furthermore, the second guide vanes 14, the first insert part 16 and the first insert part 46 are formed integrally with each other. This means that the second insert part 18 is partially formed integrally with the second guide vanes 14 and the first insert part 16.
  • the second guide vanes 14 and the first insert part 16 are formed integrally with one another and separately from the second insert part 18.
  • Each of the second guide vanes 14 now has in each case a plurality, in the present case two pins 36, which are arranged in corresponding second passages designed as passage openings
  • Receiving openings 38 are at least partially included.
  • the second guide vanes 14 are welded to the second insert part 18 to form welds 34.
  • FIG. 9 shows a further embodiment of the guide 10, wherein the pins 36, 42 have respective chamfers 50, so that the pins 36, 42 are formed in regions conical or frustoconical.
  • the chamfers 50 can serve as an insertion aid, so that the pins 36, 42 to simple and thus on time and cost Inserted without tilting in the receiving opening 38, 44 and then welded to form the welds 32, 34 can be welded.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un dispositif de guidage (10) conçu pour une turbine d'un turbocompresseur à gaz d'échappement, comprenant un élément d'insertion (15) qui comporte une première pièce d'insertion (16) et une deuxième pièce d'insertion (18) disposée vis-à-vis de la première pièce d'insertion (16), ainsi qu'au moins une première aube directrice (12) destinée à dévier les gaz d'échappements circulant dans la turbine, qui est disposée entre les pièces d'insertion (16, 18) et qui est montée sur au moins une des pièces d'insertion (16, 18) de manière à effectuer un mouvement de rotation autour d'un axe de rotation (20) par rapport auxdites pièces d'insertion (16, 18). Au moins la deuxième aube directrice (14) est conçue pour dévier les gaz d'échappement qui sont immobiles par rapport aux pièces d'insertion (16, 18). Cette invention se rapport en outre à une turbine correspondante conçue pour un turbocompresseur à gaz d'échappement.
PCT/EP2013/000020 2012-01-18 2013-01-08 Dispositif de guidage conçu pour une turbine d'un turbocompresseur à gaz d'échappement et turbine correspondante WO2013107610A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
JP2014552560A JP2015505004A (ja) 2012-01-18 2013-01-08 排気ガスターボチャージャーのタービンのガイド機構及びそのタービン
EP13704874.0A EP2805028A1 (fr) 2012-01-18 2013-01-08 Dispositif de guidage conçu pour une turbine d'un turbocompresseur à gaz d'échappement et turbine correspondante
CN201380005789.3A CN104053863B (zh) 2012-01-18 2013-01-08 用于废气涡轮增压机的涡轮的导向装置和相应的涡轮
US14/324,197 US20140321991A1 (en) 2012-01-18 2014-07-06 Guide apparatus for a turbine of an exhaust gas turbocharger

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012001236.5 2012-01-18
DE102012001236.5A DE102012001236B4 (de) 2012-01-18 2012-01-18 Leiteinrichtung für eine Turbine eines Abgasturboladers

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US14/324,197 Continuation-In-Part US20140321991A1 (en) 2012-01-18 2014-07-06 Guide apparatus for a turbine of an exhaust gas turbocharger

Publications (1)

Publication Number Publication Date
WO2013107610A1 true WO2013107610A1 (fr) 2013-07-25

Family

ID=47739191

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2013/000020 WO2013107610A1 (fr) 2012-01-18 2013-01-08 Dispositif de guidage conçu pour une turbine d'un turbocompresseur à gaz d'échappement et turbine correspondante

Country Status (6)

Country Link
US (1) US20140321991A1 (fr)
EP (1) EP2805028A1 (fr)
JP (1) JP2015505004A (fr)
CN (1) CN104053863B (fr)
DE (1) DE102012001236B4 (fr)
WO (1) WO2013107610A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20140063474A (ko) 2012-11-16 2014-05-27 에이비비 터보 시스템즈 아게 노즐 링
CN106460547B (zh) * 2014-06-20 2020-05-19 博格华纳公司 具有可调节叶片的涡轮增压器
DE102015225828A1 (de) * 2015-01-07 2016-07-07 Borgwarner Inc. Haltevorrichtung für Schaufellagerringanordnung für Turbolader mit variabler Turbinengeometrie
DE102019125823B4 (de) * 2019-09-25 2023-05-11 Rolls-Royce Solutions GmbH Turbinengehäuse und Abgasturbolader mit Vorleitbeschaufelung und eine Brennkraftmaschine mit einem Abgasturbolader
US11530615B1 (en) * 2022-03-01 2022-12-20 Garrett Transportation I Inc. Method for constructing a fixed-vane ring for a nozzle of a turbocharger turbine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0247905A2 (fr) * 1986-05-30 1987-12-02 Honda Giken Kogyo Kabushiki Kaisha Arrangement d'aubes statoriques variables
US4820118A (en) * 1987-01-23 1989-04-11 Honda Giken Kogyo Kabushiki Kaisha Variable-displacement turbine
DE3912348A1 (de) * 1988-04-15 1989-10-26 Honda Motor Co Ltd Verdraengerturbine mit variabler verdraengung
DE10050157A1 (de) * 2000-10-11 2002-04-18 Daimler Chrysler Ag Leitgitter mit verstellbaren Leitschaufeln für einen Abgasturbolader
EP1201881A2 (fr) * 2000-10-31 2002-05-02 Otto Blank Turbosoufflante
AT411615B (de) * 2000-10-31 2004-03-25 Blank Otto Ing Abgasturbolader für eine brennkraftmaschine
EP2226484A1 (fr) 2007-12-12 2010-09-08 IHI Corporation Turbocompresseur
DE102010047252A1 (de) * 2010-10-04 2011-12-01 Voith Patent Gmbh Leitapparat

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH254459A (de) * 1945-03-02 1948-04-30 Berger Hans Abgasturbolader.
US5214920A (en) * 1990-11-27 1993-06-01 Leavesley Malcolm G Turbocharger apparatus
JPH10274048A (ja) * 1997-03-28 1998-10-13 Toyota Central Res & Dev Lab Inc 可変容量形ターボチャージャ
JP2000110575A (ja) * 1998-10-01 2000-04-18 Toyota Motor Corp 排気駆動式過給機用ベーンノズル
DE10029640C2 (de) * 2000-06-15 2002-09-26 3K Warner Turbosystems Gmbh Abgasturbolader für eine Brennkraftmaschine
US7478991B2 (en) * 2006-03-06 2009-01-20 Honeywell International, Inc. Variable nozzle device
JP4847842B2 (ja) * 2006-10-25 2011-12-28 アイシン高丘株式会社 タービンハウジング
US8414253B2 (en) * 2008-10-23 2013-04-09 Honeywell International, Inc. Turbocharger vane
US8834104B2 (en) * 2010-06-25 2014-09-16 Honeywell International Inc. Vanes for directing exhaust to a turbine wheel

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0247905A2 (fr) * 1986-05-30 1987-12-02 Honda Giken Kogyo Kabushiki Kaisha Arrangement d'aubes statoriques variables
US4820118A (en) * 1987-01-23 1989-04-11 Honda Giken Kogyo Kabushiki Kaisha Variable-displacement turbine
DE3912348A1 (de) * 1988-04-15 1989-10-26 Honda Motor Co Ltd Verdraengerturbine mit variabler verdraengung
DE10050157A1 (de) * 2000-10-11 2002-04-18 Daimler Chrysler Ag Leitgitter mit verstellbaren Leitschaufeln für einen Abgasturbolader
EP1201881A2 (fr) * 2000-10-31 2002-05-02 Otto Blank Turbosoufflante
AT411615B (de) * 2000-10-31 2004-03-25 Blank Otto Ing Abgasturbolader für eine brennkraftmaschine
EP2226484A1 (fr) 2007-12-12 2010-09-08 IHI Corporation Turbocompresseur
DE102010047252A1 (de) * 2010-10-04 2011-12-01 Voith Patent Gmbh Leitapparat

Also Published As

Publication number Publication date
DE102012001236B4 (de) 2024-10-24
CN104053863B (zh) 2016-08-17
DE102012001236A1 (de) 2013-07-18
CN104053863A (zh) 2014-09-17
US20140321991A1 (en) 2014-10-30
EP2805028A1 (fr) 2014-11-26
JP2015505004A (ja) 2015-02-16

Similar Documents

Publication Publication Date Title
EP2209969B1 (fr) Dispositif de suralimentation
WO2013107610A1 (fr) Dispositif de guidage conçu pour une turbine d'un turbocompresseur à gaz d'échappement et turbine correspondante
WO2010069301A2 (fr) Turbines à variabilité intégrale pour turbocompresseurs
WO2013079137A1 (fr) Machine à énergie hydraulique ou pneumatique, en particulier pour un turbocompresseur, doté d'un élément de guidage rotatif disposé en biais
DE102016002722A1 (de) Turboladerturbinendüse und Sicherheitsstruktur
EP2859190B1 (fr) Carter de turbine pour turbocompresseur à gaz d'echappement
WO2012062407A1 (fr) Elément rapporté pour une turbine d'un turbocompresseur à gaz d'échappement, turbocompresseur à gaz d'échappement ainsi que turbine pour un turbocompresseur à gaz d'échappement
EP2707575B1 (fr) Géométrie de turbine/compresseur variable
EP2576989B1 (fr) Turbine pour un turbocompresseur d'échappement
DE102008000508A1 (de) Abgasturbolader mit verstellbarer Turbinengeometrie
EP1878893B1 (fr) Agencement de turbosoufflante de gaz d'échappement
DE102012201135A1 (de) Ladeeinrichtung
DE102012012000B4 (de) Turbine für einen Abgasturbolader
DE112013001879T5 (de) Bajonettabstandshalter-Haltesystem für Schaufelaggregate mit variabler Turbinengeometrie
DE102010062968A1 (de) Radialverdichter für einen Turbolader, Turbolader
DE102015006457A1 (de) Radialverdichter, insbesondere für einen Abgasturbolader einer Verbrennungskraftmaschine
WO2014000976A1 (fr) Turbocompresseur à gaz d'échappement
EP3048265B1 (fr) Procédé de fabrication d'une géométrie variable de turbine
WO2011147511A1 (fr) Turbocompresseur avec un obturateur mobile axialement
DE102009004890A1 (de) Ladeeinrichtung
DE102008000724A1 (de) Abgasturbolader mit verstellbarer Turbinengeometrie
DE102011118112A1 (de) Turbine für einen Abgasturbolader
DE102010047251A1 (de) Leitapparat
DE102021134071A1 (de) Radialturbine mit vtg-leitgitter
WO2013026653A1 (fr) Géométrie variable de turbine/compresseur

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 13704874

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase

Ref document number: 2014552560

Country of ref document: JP

Kind code of ref document: A

NENP Non-entry into the national phase

Ref country code: DE

WWE Wipo information: entry into national phase

Ref document number: 2013704874

Country of ref document: EP