EP1536103B1 - Turbomachine avec aubes de guidage et agencement de fixation - Google Patents

Turbomachine avec aubes de guidage et agencement de fixation Download PDF

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Publication number
EP1536103B1
EP1536103B1 EP03027266.0A EP03027266A EP1536103B1 EP 1536103 B1 EP1536103 B1 EP 1536103B1 EP 03027266 A EP03027266 A EP 03027266A EP 1536103 B1 EP1536103 B1 EP 1536103B1
Authority
EP
European Patent Office
Prior art keywords
ring
housing arrangement
radially
guide
carrier ring
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.)
Expired - Lifetime
Application number
EP03027266.0A
Other languages
German (de)
English (en)
Other versions
EP1536103A1 (fr
Inventor
Dietmar Metz
Hans-Peter Schmalzl
Ralf Böning
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.)
BorgWarner Inc
Original Assignee
BorgWarner 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 BorgWarner Inc filed Critical BorgWarner Inc
Priority to EP03027266.0A priority Critical patent/EP1536103B1/fr
Priority to JP2004300938A priority patent/JP4430507B2/ja
Priority to US10/998,516 priority patent/US7189058B2/en
Publication of EP1536103A1 publication Critical patent/EP1536103A1/fr
Application granted granted Critical
Publication of EP1536103B1 publication Critical patent/EP1536103B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the present invention relates to a turbomachine according to the preamble of claim 1.
  • turbomachines are conventionally designed in a variety of ways, for example as secondary air pumps or turbines, but especially as a turbocharger, which often have separate and attached housing parts for the turbine and their storage. Therefore, the term "housing assembly" in the context of the present invention should be understood to include either the turbine or the bearing housing or both.
  • Guideways are subjected to the most diverse, including pulsating, stresses in turbomachines, be it by the forces of the flow medium itself, be it by temperature influences or by externally coming and impressed vibrations (for example, an internal combustion engine).
  • guide gratings have hitherto been clamped either on a wall of the housing itself or via a carrier ring, but in any case fixedly in the housing, usually in a turbine housing. Examples of this can be found in the EP-B1-0 226 444 , of the US-A-5,146,752 where the carrier or blade bearing ring is clamped by bolts.
  • US-A-2,447,942 shows a distributor for a turbine in which the vane ring g is supported with axial and radial play.
  • DE-A-197 03 033 shows an exhaust gas turbine of a turbocharger in which a ring seal is provided between a blade bearing ring also mounted axially and radially with play and a housing part.
  • the conventional rigid attachment although inherently providing a desired fixed spatial relationship of the parts to each other, is detrimental to the faulting problem. Because, for example, temperature-induced strains of the material, when tightened, inevitably lead to the aforementioned distortions. But these should be avoided.
  • the carrier ring is fixed by means of a fastening device axially and / or radially movable on the housing assembly.
  • the carrier ring is designed as a blade bearing ring for supporting the shafts or axles of moving guide vanes. Because the previously so difficult to control phenomenon of clamping the vanes, according to the invention certainly avoided as well as distortions of the blade bearing ring, which may also be cause for malfunction.
  • axial mobility can take place with adaptation to temperature conditions in the manner known from the mounting of laser mirrors of a laser resonator on rods which stretch under the influence of temperature and thus the mirror (here at least one of the rings, such as the blade bearing ring). Keep in the correct distance, so as to avoid jamming of the vanes.
  • the fastening device has a radially extending, in particular radially outer, recess, preferably a groove, in particular an annular groove, in the carrier ring and a recess, preferably a groove, in particular an annular groove, in a radially opposite wall of the housing arrangement, wherein an insert part, for example a snap ring, piston ring or Segerring) is provided between this recess or depression while allowing the axial and / or radial mobility.
  • an insert part for example a snap ring, piston ring or Segerring
  • a turbine housing 2 is connected to a flange 16 of a bearing housing, from which a cylindrical piece 40 projects into the turbine housing 2 and supports the shaft 35 of a turbine rotor 4.
  • the turbine housing 2 comprises a supply channel 9 surrounding the turbine rotor 4 for a fluid driving the turbine rotor 4 (in the case of a turbocharger this is the exhaust gas of an internal combustion engine), a rotor space 23 and an axial connection 10 through which the fluid or the exhaust gas is emitted again becomes.
  • a device is provided at the outlet of the feed channel 9 or in front of the rotor chamber 23, which device is known in the art as the "variable turbine nozzle guide grid".
  • This guide grid substantially comprises a ring of movable guide vanes 7 concentrically surrounding the turbine rotor 4, which are mounted on adjusting shafts (or stub shafts) fixedly connected to them in a carrier ring 6 coaxially surrounding the turbine rotor 4, which is known in the art - in the case of turbochargers - Also known as "blade bearing ring".
  • the rotation or adjustment of the adjusting 8 can in itself, for example from the US-A-4,659,295 Known manner be done by an actuator 11 has a control housing 12 which controls the control movement of a attached to her, only dash-dotted lines plunger member whose movement via an actuating lever 13, an associated with this actuating shaft 14 and for example via an opening in a behind the vane ring 6 located adjusting ring 5 engaging eccentric 15 is converted into a slight rotational movement of this ring 5 around the axis R.
  • the guide vanes 7 are adjusted relative to the turbine rotor 4 with respect to their rotational position in a known manner so that they are adjustable from an approximately tangential extending an extreme position in an approximately radially veriaufende other extreme position.
  • the exhaust gas of an internal combustion engine supplied via the supply channel 9 is supplied to the turbine rotor 4 more or less before it exits again at the axial connection piece 10 extending along the axis of rotation R.
  • FIG. 1 also shows, the mounting ring 29 is pushed onto an annular shoulder 17 of a wall 2 'of the turbine housing 2 and optionally bolted or even with slight play placed to - as will be explained, to allow an axial displacement.
  • a plate spring or a heat shield 32 may engage an inner flange 6 'of the blade bearing ring 6 to hold the guide grid in the axial direction and to press against the wall 2'.
  • the other radial end of the plate spring 32 is located on the cylinder piece 40 of the bearing housing. Also in the axial direction of the mounting ring 29 relative to the wall 2 'may have an easy game.
  • a plate spring 32 is provided to load the blade bearing ring 6 on the radially inwardly located projection 6 ', this ring 6 is according to the invention secured such that it is a slight mobility, in the radial and / or in the axial direction, possible ,
  • This attachment is made in the illustrated embodiment on the radially outer side of the blade bearing ring 6 at a bifurcated wall 27 of the turbine housing 2 (as is preferred), but the attachment could also be done radially inside the bearing housing, for example on the cylinder piece 40.
  • Fig. 2 show that, relationships in detail.
  • the blade bearing ring 6 has a blade bearing chamber 8 facing portion of smaller diameter (in Fig. 2 right), who with. a game g is able to pass under an annular projection 33.
  • the radial clearance g serves to enable radial expansions of the blade bearing ring 6.
  • a section of the blade bearing ring 6 facing away from the blade bearing chamber 8 (left in FIG Fig. 2 ) has a larger diameter and has, relative to the inner surface of the wall 27, an equal or different game g 'g', which serves the same purpose.
  • a radially extending recess 25 is provided in the larger diameter portion of the blade bearing ring 6, which could be formed as a single recess in itself (it would then several such wells distributed over the circumference of the blade bearing ring), but is designed for manufacturing reasons, but also because of easier assembly as a groove and in particular as an annular groove.
  • the suspension may be caused for example by corrugations, but is preferably designed in the manner of a snap ring, piston ring or Segerrings and an open separation point 28 (FIG. Fig.
  • the radial depth of the groove 25 is suitably dimensioned so that it in the compressed state of the ring 26 whose, at least approximately, total radial width (possibly minus the game g ') can accommodate.
  • this groove 25 spring ring 26 projects - again with some play - in a groove 25 opposite groove 31, which causes the fork shape of the radially inwardly projecting wall 27 in cross section. It is understood that - if only, distributed over the circumference of the vane bearing ring 6 recesses each with an insert to be used (with the cross section of the ring 26) and this groove 31 could be formed by distributed individual recesses or recesses, but that a groove or an annular groove is preferable.
  • the groove 31 and / or the ring 26 In order to load the blade bearing ring 6 against the shoulder surface 24, it is advantageous for the groove 31 and / or the ring 26 to be one Fig. 2 apparent bevel 32 '(the groove 31) and a wedge surface 34 (of the ring 26).
  • eyelets 37 are according to the illustration of Fig. 3 formed on the upper side of the ring 26 on both sides of the separation point 28, but could possibly also protrude laterally in the axial direction. In this case, they are preferably integrally formed by co-punching, although it would theoretically be possible to weld or solder them on (which may possibly impair the elasticity of the ring 26).
  • the two eyelets 37 When mounting you press, for example, with a pair of pliers, the two eyelets 37 against each other, so that the distance between the separation point 28 is at least reduced or even closed. This reduces the diameter of the ring 26 and this penetrates into the interior of the groove 25 (FIG. Fig. 2 ) one.
  • the in Fig. 2 left boundary wall of the groove 31 has an axial slot opening 36 for the access of a mounting tool, such as a pair of pliers, to the eyelets 37 on.
  • the spacer 38 is no longer used to enforce a fastening screw, this spacer very aerodynamic and thin, for example, with an aircraft wing similar flow profile in the direction of Supply channel 9 can be formed to the rotation axis R, so that only small flow losses for the turbine wheel 4 supplied fluid can be expected. It is also possible, the spacer 38 opposite surface of the mounting ring 30 'deepen something, so that any axial movement of the spacer 38 is guided. Conversely, the mounting ring 30 'with (dashed lines indicated) holes 39 are provided to store stub axle 41 of the vanes 7 therein.
  • vane ring 6 can be pre-assembled with the blade ring of the blades 7 and the mounted thereon mounting ring 30 'inserted into the turbine housing 2, in which case a special game against the annular shoulder 17 is no longer essential.
  • the invention can also be applied to guide vanes of constant geometry. Also it would be straight in the case of the Fig. 4 possible to dispense entirely on a sloping or wedge surface in the groove 31 and bring about the loading force by the aforementioned plate spring 32. Conversely, on the plate spring 32 in the presence of at least one of the inclined or wedge surfaces 32, 34th

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

Claims (7)

  1. Turbomachine avec une grille directrice dans un agencement de boîtier (2, 40) recevant une turbine (4) avec une tubulure de sortie centrale (10) qui présente :
    une couronne d'aubes directrices (7) disposée autour d'un axe central (R) ;
    une bague de support (6) sur laquelle est montée la couronne d'aubes directrices (7) autour de l'axe central (R), laquelle bague de support (6) est insérée dans l'agencement de boîtier (2, 40) ;
    la bague de support (6) étant fixée de manière déplaçable axialement et/ou radialement sur l'agencement de boîtier (2, 40) au moyen d'un dispositif de fixation (26, 27, 31-34) et étant précontrainte axialement contre l'agencement de boîtier (27, 33), caractérisée en ce que le dispositif de fixation (26, 27, 31-34) présente un évidement (25) s'étendant radialement, en particulier radialement extérieur, réalisé sous forme de rainure annulaire dans la bague de support (6) et un renfoncement (31) réalisé sous forme de rainure annulaire dans une paroi radialement opposée (27) de l'agencement de boîtier (2, 40), et en ce qu'une pièce d'insertion (26) est prévue entre cet évidement (25) ou ce renfoncement (31) en permettant le déplacement axial et/ou radial, la pièce d'insertion (26) étant réalisée sous forme de bague élastique introduite dans les rainures annulaires, avec une surface de clavetage radialement extérieure (34), ou un arrondi, pour l'application contre une portion de la paroi (27) à l'intérieur de sa rainure (31), et la rainure annulaire (31) possédant une surface de clavetage (32) pour l'application de la bague élastique (26).
  2. Turbomachine selon la revendication 1, caractérisée en ce qu'au moins l'une des caractéristiques suivantes est prévue :
    a) elle est réalisée sous forme de turbocompresseur ;
    b) la grille conductrice possède une géométrie variable, la bague de support (6) étant réalisée sous forme de bague de support d'aubes pour le support des arbres ou des axes (41) d'aubes directrices mobiles (7) et de préférence les aubes directrices (7) sont supportées entre elle (6) et une bague de montage opposée (30 ; 30').
  3. Turbomachine selon la revendication 1 ou 2, caractérisée en ce que l'agencement de boîtier (2, 40) présente une butée (24) et la bague de support (6) est sollicitée par force par le dispositif de fixation (26, 27, 31-34) contre cette butée (24) et en ce que de préférence, la sollicitation du dispositif de fixation (26, 27, 31-34) présente une force orientée vers la grille directrice.
  4. Turbomachine selon l'une quelconque des revendications 1 à 3, caractérisée en ce que la bague élastique (26) présente au moins une pièce de montage saillante, en particulier au moins un oeillet (37), et en ce que la rainure annulaire respective (31) possède une ouverture de fente axiale (36) pour l'accès d'un outil de montage à la pièce de montage saillante (37).
  5. Turbomachine selon l'une quelconque des revendications 1 à 4, caractérisée en ce qu'entre la bague de support (6) et la paroi (27) radialement opposée de l'agencement de boîtier (2, 40) et/ou entre la pièce d'insertion (26) et la paroi interne de l'évidement (31) et/ou du renfoncement (25) est prévu un espacement (g", g"') pour permettre un libre déplacement.
  6. Bague de fixation pour une turbomachine selon l'une quelconque des revendications 1 à 5, laquelle bague (26) est formée d'un matériau annulaire élastique présentant une zone de séparation (28), caractérisée en ce que des deux côtés de la zone de séparation (28) est prévue au moins une pièce de montage saillante (37) pour la compression de la bague (26).
  7. Bague de fixation selon la revendication 6, caractérisée en ce qu'au moins l'une des pièces de montage saillantes, de préférence les deux, sont réalisées sous forme d'oeillets (37), de préférence façonnés.
EP03027266.0A 2003-11-28 2003-11-28 Turbomachine avec aubes de guidage et agencement de fixation Expired - Lifetime EP1536103B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP03027266.0A EP1536103B1 (fr) 2003-11-28 2003-11-28 Turbomachine avec aubes de guidage et agencement de fixation
JP2004300938A JP4430507B2 (ja) 2003-11-28 2004-10-15 流体流れエンジン及びそのための支持リング
US10/998,516 US7189058B2 (en) 2003-11-28 2004-11-29 Fluid flow engine and support ring for it

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03027266.0A EP1536103B1 (fr) 2003-11-28 2003-11-28 Turbomachine avec aubes de guidage et agencement de fixation

Publications (2)

Publication Number Publication Date
EP1536103A1 EP1536103A1 (fr) 2005-06-01
EP1536103B1 true EP1536103B1 (fr) 2013-09-04

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EP03027266.0A Expired - Lifetime EP1536103B1 (fr) 2003-11-28 2003-11-28 Turbomachine avec aubes de guidage et agencement de fixation

Country Status (3)

Country Link
US (1) US7189058B2 (fr)
EP (1) EP1536103B1 (fr)
JP (1) JP4430507B2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015220988A1 (de) * 2015-10-27 2017-04-27 Robert Bosch Gmbh Förderungseinheit, sowie Brennstoffzellenvorrichtung mit einer Förderungseinheit
DE102018115448A1 (de) 2018-06-27 2020-01-02 Ihi Charging Systems International Gmbh Abgasturbolader

Families Citing this family (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1394363B1 (fr) * 2002-08-26 2006-03-01 BorgWarner Inc. Système d'aubes de guidage variables pour une turbine
DE50205993D1 (de) * 2002-08-26 2006-05-04 Borgwarner Inc Turbolader und Schaufellagerring hierfür
DE60226784D1 (de) * 2002-09-05 2008-07-03 Honeywell Int Inc Turbolader mit verstellbaren leitschaufeln
DE102004038748A1 (de) * 2004-08-10 2006-02-23 Daimlerchrysler Ag Abgasturbolader für eine Brennkraftmaschine
JP2006207526A (ja) 2005-01-31 2006-08-10 Mitsubishi Heavy Ind Ltd 可変容量型排気ターボ過給機及び可変ノズル機構構成部材の製造方法
DE102005012048A1 (de) * 2005-03-08 2006-09-14 Dr.Ing.H.C. F. Porsche Ag Turbinengehäuse eines Abgasturboladers mit verstellbarer Turbinengeometrie
EP1960632B1 (fr) * 2005-11-30 2019-08-21 Dresser-Rand Company Dispositif de fermeture d'extremite pour carter de turbomachine
JP2009524773A (ja) * 2006-01-27 2009-07-02 ボーグワーナー・インコーポレーテッド ウェーブスプリングを用いたｖｔｇ機構組立体
EP1816317B1 (fr) * 2006-02-02 2013-06-12 IHI Corporation Turbocompresseur à géométrie variable
US20090067996A1 (en) * 2006-02-16 2009-03-12 Borg Warner Inc. Blade bearing ring assembly of a turbocharger with a variable turbine geometry
EP1994268B1 (fr) * 2006-03-14 2016-10-12 BorgWarner, Inc. Turbocompresseur
JP2008215083A (ja) * 2007-02-28 2008-09-18 Mitsubishi Heavy Ind Ltd 可変容量型排気ターボ過給機における可変ノズル機構部取付構造
JP4930150B2 (ja) * 2007-03-29 2012-05-16 株式会社Ｉｈｉ 可変ノズル機構付き膨張タービン
JP4930151B2 (ja) * 2007-03-29 2012-05-16 株式会社Ｉｈｉ 可変ノズル機構付き膨張タービン
GB0708975D0 (en) * 2007-05-10 2007-06-20 Cummins Turbo Tech Ltd Variable geometry turbine
DE102007057309A1 (de) * 2007-11-28 2009-06-10 Continental Automotive Gmbh Hitzeschild und Turbolader mit einem Hitzeschild
DE102008000776B4 (de) 2008-01-21 2022-04-14 BMTS Technology GmbH & Co. KG Turbine mit varialber Turbinengeometrie, insbesondere für einen Abgasturbolader, sowie Abgasturbolader
DE102008005404A1 (de) 2008-01-21 2009-07-23 Bosch Mahle Turbo Systems Gmbh & Co. Kg Turbolader
DE102008014678B4 (de) 2008-03-18 2014-08-14 Continental Automotive Gmbh Turbolader mit einer variablen Turbinengeometrie VTG
JP5082991B2 (ja) * 2008-03-31 2012-11-28 株式会社Ｉｈｉ 過給機
DE102008017821A1 (de) * 2008-04-08 2009-10-22 Continental Automotive Gmbh Befestigungselement und Abgasturbolader mit variabler Turbinengeometrie
US8267647B2 (en) * 2008-07-09 2012-09-18 Borgwarner Inc. Variable geometry turbocharger lower vane ring retaining system
DE102008053170A1 (de) * 2008-10-24 2010-04-29 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung mit variabler Turbinen-/Verdichtergeometrie, insbesondere für einen Abgasturbolader eines Kraftfahrzeugs
DE102009007663A1 (de) 2009-02-05 2010-08-12 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
DE102009009129B4 (de) * 2009-02-17 2022-11-03 BMTS Technology GmbH & Co. KG Turbolader mit variabler Turbinengeometrie
DE102009012065A1 (de) * 2009-03-06 2010-09-09 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung, insbesondere für ein Kraftfahrzeug, mit einer variablen Turbinengeometrie
EP2514945B2 (fr) 2009-12-17 2019-12-25 IHI Corporation Turbocompresseur
CN102762838B (zh) * 2010-02-25 2015-06-10 株式会社Ihi 可变容量式涡轮增压器
JPWO2011152454A1 (ja) * 2010-06-01 2013-08-01 株式会社Ihi 固定翼式ターボチャージャ
JP5494248B2 (ja) * 2010-06-02 2014-05-14 株式会社Ｉｈｉ 固定翼式ターボチャージャ
EP2617960B1 (fr) 2010-09-13 2020-03-18 IHI Corporation Turbocompresseur du type à aubes fixes
DE102010064047A1 (de) 2010-12-23 2012-06-28 Man Diesel & Turbo Se Strömungsmaschine
US8985943B2 (en) * 2011-09-30 2015-03-24 Honeywell International Inc. Turbocharger variable-nozzle assembly with vane sealing arrangement
JP5710452B2 (ja) * 2011-11-16 2015-04-30 トヨタ自動車株式会社 ターボチャージャ
US8834028B2 (en) * 2011-12-22 2014-09-16 Energy Recovery, Inc. Debris resistant thrust bearing assembly for high speed hydraulic centrifugal turbines and pumps
DE102012001603B4 (de) * 2012-01-26 2019-11-21 Ihi Charging Systems International Gmbh Abgasturbolader
JP5942464B2 (ja) * 2012-02-21 2016-06-29 トヨタ自動車株式会社 過給機
DE102013007443A1 (de) * 2013-04-30 2014-10-30 Rolls-Royce Deutschland Ltd & Co Kg Brennerdichtung für Gasturbinen-Brennkammerkopf und Hitzeschild
CN107109954B (zh) * 2014-12-19 2019-12-10 沃尔沃卡车集团 涡轮增压器和制造涡轮增压器的方法
JP6325479B2 (ja) * 2015-03-30 2018-05-16 株式会社豊田自動織機 ターボチャージャ
CN108884838B (zh) * 2016-01-20 2021-02-05 三菱重工发动机和增压器株式会社 固定静叶片式旋转机械及固定静叶片式旋转机械的装配方法
CN109477419B (zh) 2016-08-24 2020-11-17 株式会社Ihi 可变容量型增压器
DE102016123249A1 (de) * 2016-12-01 2018-06-07 Man Diesel & Turbo Se Turbolader
DE102017218303B4 (de) 2017-10-13 2024-04-18 Vitesco Technologies GmbH Verfahren zur Befestigung eines Leitapparates einer variablen Turbinengeometrie an einem Gehäuse einer Turboladereinrichtung
EP3767081A1 (fr) * 2019-07-15 2021-01-20 ABB Schweiz AG Logement de turbine doté d'une bride de raccordement à faible tension et turbine de gaz d'échappement dotée d'un tel logement de turbine
DE102021108686A1 (de) * 2021-04-07 2022-10-13 Borgwarner Inc. Turbinenanordnung mit separater leiteinrichtung
DE102021204366A1 (de) 2021-04-30 2022-11-03 Vitesco Technologies GmbH Abgasturbolader mit einem Integralgehäuse und variabler Turbinengeometrie und Integralgehäuse für einen Abgasturbolader

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR994013A (fr) * 1944-12-05 1951-11-09 Rateau Soc Perfectionnement à l'exécution des distributeurs et tuyères de turbines
US4659295A (en) * 1984-04-20 1987-04-21 The Garrett Corporation Gas seal vanes of variable nozzle turbine
DE19703033A1 (de) * 1997-01-29 1998-07-30 Asea Brown Boveri Abgasturbine eines Turboladers
US5947681A (en) * 1997-03-17 1999-09-07 Alliedsignal Inc. Pressure balanced dual axle variable nozzle turbocharger
DE19961613A1 (de) * 1999-12-21 2001-07-19 Daimler Chrysler Ag Abgasturbine eines Abgasturboladers für eine Brennkraftmaschine
DE10029640C2 (de) * 2000-06-15 2002-09-26 3K Warner Turbosystems Gmbh Abgasturbolader für eine Brennkraftmaschine
DE10237413B4 (de) * 2002-08-16 2004-07-15 Daimlerchrysler Ag Abgasturbolader für eine Brennkraftmaschine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015220988A1 (de) * 2015-10-27 2017-04-27 Robert Bosch Gmbh Förderungseinheit, sowie Brennstoffzellenvorrichtung mit einer Förderungseinheit
DE102018115448A1 (de) 2018-06-27 2020-01-02 Ihi Charging Systems International Gmbh Abgasturbolader
US11220957B2 (en) 2018-06-27 2022-01-11 Ihi Charging Systems International Gmbh Exhaust gas turbocharger

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US7189058B2 (en) 2007-03-13
US20060034684A1 (en) 2006-02-16
JP2005163783A (ja) 2005-06-23
EP1536103A1 (fr) 2005-06-01
JP4430507B2 (ja) 2010-03-10

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