EP1734231A1 - Turbocompresseur et anneau statorique pour celui-ci - Google Patents

Turbocompresseur et anneau statorique pour celui-ci Download PDF

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Publication number
EP1734231A1
EP1734231A1 EP20050013040 EP05013040A EP1734231A1 EP 1734231 A1 EP1734231 A1 EP 1734231A1 EP 20050013040 EP20050013040 EP 20050013040 EP 05013040 A EP05013040 A EP 05013040A EP 1734231 A1 EP1734231 A1 EP 1734231A1
Authority
EP
European Patent Office
Prior art keywords
bearing ring
blade bearing
turbine housing
turbocharger
turbocharger according
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.)
Granted
Application number
EP20050013040
Other languages
German (de)
English (en)
Other versions
EP1734231B1 (fr
Inventor
Michael Stilgenbauer
Gerald Schall
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 EP05013040.0A priority Critical patent/EP1734231B1/fr
Publication of EP1734231A1 publication Critical patent/EP1734231A1/fr
Application granted granted Critical
Publication of EP1734231B1 publication Critical patent/EP1734231B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/33—Retaining components in desired mutual position with a bayonet coupling

Definitions

  • the invention relates to a turbocharger according to the preamble of claim 1 and a blade bearing ring therefor according to the preamble of claim 11.
  • Such a turbocharger or such a blade bearing ring is from the EP 1 394 364 A1 known.
  • the vane ring is provided with spacers to maintain a clearance for the vanes of a baffle.
  • the spacers of the blade bearing ring are each provided with a bore for connecting bolts. In the assembled state, the connecting bolts pass through the holes and engage in a bearing ring of the turbine housing arranged adjacent to the blade bearing ring.
  • a kind of bayonet lock is possible, which is formed by a groove which is arranged on at least one of the spacers of the blade bearing ring and cooperates in the assembled state with a suitably designed and arranged web of the turbine housing.
  • An alternative preferred embodiment provides as a fastening means a radially aligned centering surface, which forms a press fit with a suitably arranged and formed counter surface of the turbine housing in the assembled state.
  • Radial alignment in this context means that the centering surface has radially inwardly with respect to the axis of rotation of the turbine rotor, wherein the mating surface of the turbine housing accordingly faces radially outward.
  • the fastener in forming the fastener as a press fit, it is also possible to provide additional axial securing of the vane ring by cooperating with a disc assembly disposed between the turbine housing and the bearing housing of the turbocharger.
  • This disc assembly can be formed in a particularly preferred embodiment by a arranged on the side of the bearing housing disc spring and a heat shield, the facing the turbine housing.
  • the turbine housing is formed of a material which has a low temperature resistance
  • an insert disk of particularly temperature-resistant material for protecting the guide vanes between the blade bearing ring and the turbine housing.
  • a turbocharger 1 according to the invention is shown, which has a turbine housing 2 and a compressor housing 3 connected thereto via a bearing housing 28.
  • the housings 2, 3 and 28 are arranged along a rotation axis R.
  • the turbine housing is shown partially in section to illustrate the arrangement of a vane ring 6 and a radially outer vane 18 formed therefrom which has a plurality of circumferentially spaced vanes 7 with pivot axes 8.
  • nozzle cross-sections are formed, which are larger or smaller depending on the position of the guide vanes 7 and apply more or less to the located in the middle of the axis of rotation R turbine rotor 4 with the supplied via a feed channel 9 and discharged via a central port 10 exhaust gas of an engine to drive via the turbine rotor 4 a seated on the same shaft compressor motor 17.
  • an actuating device 11 is provided.
  • a control housing 12 which controls the control movement of a ram member 14 attached to her to implement the movement thereof to a located behind the blade bearing ring 6 adjusting 5 in a slight rotational movement of the same.
  • a clearance 13 for the vanes 7 is formed between the vane ring 6 and an annular part 15 of the turbine housing 2.
  • the blade bearing ring 6 integrally formed spacers 16, which are shown in detail in FIGS. 2 and 3.
  • three spacers 16 at an angular distance of 120 ° at the periphery of Blade bearing ring 6 is arranged. In principle, it is possible to provide more or less such spacers 16, but results in the embodiment of FIG. 2 is a particularly advantageous geometric arrangement.
  • FIGS. 2 to 4 show an embodiment of the blade bearing ring 6, which has a fastening device 19 for fixing the blade bearing ring 6 on the turbine housing 2, which is arranged in one piece on at least one of the spacers 16.
  • the fastening device 19 has a groove 20 which is arranged between a, preferably cylindrically shaped, main part 22 of the spacer 16 and a centering shoulder 23.
  • the main part 22 is due to the one-piece design in the blade bearing ring 6 and the centering 23 is arranged at the free end of the spacer 16.
  • the centering shoulder 23 is provided with a shoulder relative to the main body 22 so that an axial contact surface 24 and a radially aligned centering surface or a centering diameter result adjacent to the groove 20.
  • a web 21 of the turbine housing 2 engages in the groove 20 and thus forms a bayonet-like closure device for fixing the blade bearing ring 6 on the turbine housing 2.
  • FIGS. 5 and 6 show an alternative embodiment of the turbocharger 1 according to the invention or the blade bearing ring 6 according to the invention.
  • This embodiment has a fastening device 19 ', which instead of a groove on at least one of the spacers 16 and a corresponding web on the turbine housing 2 has a radially aligned centering surface 26 on at least one of the spacers 16, in the assembled state shown in Figs. 5 and 6 interacts with a mating surface 27 of the turbine housing 2. By this interaction, a press fit in the radial direction is achieved, which is sufficient in principle to fix the blade bearing ring 6 on the turbine housing 2.
  • a projection 29 is provided which is arranged on an inner circumferential surface 30 of the blade bearing ring 6, which results in detail from FIGS. 5 and 6.
  • the projection 29 in this case has radially inward, ie in the direction of the axis of rotation R, and is arranged at the axial end 31 of the blade bearing ring 6, which is the spacers 16 adjacent.
  • This projection 29, which forms a radially encircling collar, cooperates with a disk arrangement 32, which is apparent above all from the enlarged representation of FIG. 6.
  • the disc assembly 32 has a conical disc spring 33 and a heat shield 34 disposed on the turbine housing 2 side is.
  • FIG. 7 is an embodiment of the turbocharger 1, which is intended for a low-temperature use, in which accordingly the material of the turbine housing 2 may have lower temperature resistance.
  • a high-temperature resistant insert 35 is provided between the blade bearing ring 6 and the turbine housing 2, which results in detail from the illustration of FIG. 7.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP05013040.0A 2005-06-16 2005-06-16 Turbocompresseur avec turbine a geometrie variable Expired - Fee Related EP1734231B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05013040.0A EP1734231B1 (fr) 2005-06-16 2005-06-16 Turbocompresseur avec turbine a geometrie variable

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05013040.0A EP1734231B1 (fr) 2005-06-16 2005-06-16 Turbocompresseur avec turbine a geometrie variable

Publications (2)

Publication Number Publication Date
EP1734231A1 true EP1734231A1 (fr) 2006-12-20
EP1734231B1 EP1734231B1 (fr) 2018-05-02

Family

ID=35229899

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05013040.0A Expired - Fee Related EP1734231B1 (fr) 2005-06-16 2005-06-16 Turbocompresseur avec turbine a geometrie variable

Country Status (1)

Country Link
EP (1) EP1734231B1 (fr)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008098024A2 (fr) * 2007-02-08 2008-08-14 Honeywell International Inc. Procédé de fabrication d'un mécanisme d'aube variable pour un turbocompresseur
WO2009076062A2 (fr) 2007-12-12 2009-06-18 Honeywell International Inc. Buse variable pour turbocompresseur, comportant une aube distributrice positionnée par des éléments radiaux
DE102008020932A1 (de) * 2008-04-25 2009-10-29 Continental Automotive Gmbh Turbolader mit einer variablen Turbinengeometrie VTG
WO2010040643A1 (fr) * 2008-10-09 2010-04-15 Continental Automotive Gmbh Turbocompresseur comprenant des éléments de fixation destinés à la fixation de bagues de palier d'aubes d'une turbine à géométrie variable vtg
DE102008014680A1 (de) 2008-03-18 2010-09-23 Continental Automotive Gmbh Leitgitteranordnung eines Abgasturboladers, Abgasturbolader und Verfahren zur Herstellung einer Leitgitteranordnung
WO2011069571A1 (fr) * 2009-12-10 2011-06-16 Daimler Ag Turbine pour un dispositif de suralimentation et procédé pour le montage d'une telle turbine
EP2336495A1 (fr) 2009-12-16 2011-06-22 BorgWarner, Inc. Turbosoufflante de gaz d'échappement
KR20110068847A (ko) 2009-12-16 2011-06-22 보르그워너 인코퍼레이티드 배기 가스 터보차저
DE102011005151A1 (de) * 2011-03-04 2012-09-06 Bayerische Motoren Werke Aktiengesellschaft Abgasturbolader für eine Brennkraftmaschine
WO2013072732A1 (fr) * 2011-11-16 2013-05-23 Toyota Jidosha Kabushiki Kaisha Turbocompresseur
US8662833B2 (en) 2008-01-21 2014-03-04 Bosch Mahle Turbo Systems Gmbh & Co. Kg Turbocharger with variable turbine geometry
US20150198164A1 (en) * 2014-01-15 2015-07-16 General Electric Company Rotary machine having a volute assembly-bearing housing joint with interlocking teeth
USD777212S1 (en) 2015-06-20 2017-01-24 General Electric Company Nozzle ring
WO2020001805A1 (fr) * 2018-06-27 2020-01-02 Ihi Charging Systems International Gmbh Turbocompresseur de gaz d'échappement avec couronne directrice centrée
DE102008029080B4 (de) 2008-06-19 2022-04-21 BMTS Technology GmbH & Co. KG Abgasturbolader für ein Kraftfahrzeug

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7424752B2 (ja) 2019-03-25 2024-01-30 株式会社豊田自動織機 ターボチャージャ

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0204033A1 (fr) * 1985-05-09 1986-12-10 Mtu Motoren- Und Turbinen-Union Friedrichshafen Gmbh Turbomachine
JPH10103070A (ja) * 1996-09-27 1998-04-21 Toyota Motor Corp 可変容量ターボチャージャ
DE10337491A1 (de) * 2003-08-14 2005-03-17 Volkswagen Ag Abgasturbolader für eine Brennkraftmaschine
EP1528225A1 (fr) * 2003-10-27 2005-05-04 BorgWarner Inc. Turbomachine et méthode de fabrication pour un anneau de guidage

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0204033A1 (fr) * 1985-05-09 1986-12-10 Mtu Motoren- Und Turbinen-Union Friedrichshafen Gmbh Turbomachine
JPH10103070A (ja) * 1996-09-27 1998-04-21 Toyota Motor Corp 可変容量ターボチャージャ
DE10337491A1 (de) * 2003-08-14 2005-03-17 Volkswagen Ag Abgasturbolader für eine Brennkraftmaschine
EP1528225A1 (fr) * 2003-10-27 2005-05-04 BorgWarner Inc. Turbomachine et méthode de fabrication pour un anneau de guidage

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 1998, no. 09 31 July 1998 (1998-07-31) *

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008098024A3 (fr) * 2007-02-08 2008-10-23 Honeywell Int Inc Procédé de fabrication d'un mécanisme d'aube variable pour un turbocompresseur
CN101743382B (zh) * 2007-02-08 2013-05-22 霍尼韦尔国际公司 用于制造涡轮增压器所用的可变叶片机构的方法
WO2008098024A2 (fr) * 2007-02-08 2008-08-14 Honeywell International Inc. Procédé de fabrication d'un mécanisme d'aube variable pour un turbocompresseur
US7918023B2 (en) 2007-02-08 2011-04-05 Honeywell International Inc. Method for manufacturing a variable-vane mechanism for a turbocharger
CN101896692B (zh) * 2007-12-12 2014-03-12 霍尼韦尔国际公司 用于涡轮增压器的具有由径向构件定位的喷嘴环的可变喷嘴
WO2009076062A2 (fr) 2007-12-12 2009-06-18 Honeywell International Inc. Buse variable pour turbocompresseur, comportant une aube distributrice positionnée par des éléments radiaux
WO2009076062A3 (fr) * 2007-12-12 2010-01-21 Honeywell International Inc. Buse variable pour turbocompresseur, comportant une aube distributrice positionnée par des éléments radiaux
US8480358B2 (en) 2007-12-12 2013-07-09 Honeywell International Inc. Variable nozzle for a turbocharger, having nozzle ring located by radial members
CN101896692A (zh) * 2007-12-12 2010-11-24 霍尼韦尔国际公司 用于涡轮增压器的具有由径向构件定位的喷嘴环的可变喷嘴
US8662833B2 (en) 2008-01-21 2014-03-04 Bosch Mahle Turbo Systems Gmbh & Co. Kg Turbocharger with variable turbine geometry
DE102008014680A1 (de) 2008-03-18 2010-09-23 Continental Automotive Gmbh Leitgitteranordnung eines Abgasturboladers, Abgasturbolader und Verfahren zur Herstellung einer Leitgitteranordnung
DE102008020932B4 (de) * 2008-04-25 2010-09-23 Continental Automotive Gmbh Turbolader mit einer variablen Turbinengeometrieeinrichtung
DE102008020932A1 (de) * 2008-04-25 2009-10-29 Continental Automotive Gmbh Turbolader mit einer variablen Turbinengeometrie VTG
DE102008029080B4 (de) 2008-06-19 2022-04-21 BMTS Technology GmbH & Co. KG Abgasturbolader für ein Kraftfahrzeug
CN102177312A (zh) * 2008-10-09 2011-09-07 欧陆汽车有限责任公司 具有用于固定可变几何形状的涡轮叶片vtg的叶片支撑环的固定部件的涡轮增压器
WO2010040643A1 (fr) * 2008-10-09 2010-04-15 Continental Automotive Gmbh Turbocompresseur comprenant des éléments de fixation destinés à la fixation de bagues de palier d'aubes d'une turbine à géométrie variable vtg
CN102177312B (zh) * 2008-10-09 2015-04-29 大陆汽车有限公司 具有用于固定可变几何形状的涡轮叶片vtg的叶片支撑环的固定部件的涡轮增压器
US8764389B2 (en) 2008-10-09 2014-07-01 Continental Automotive Gmbh Turbocharger having fastening elements for fastening vane bearing rings of a variable turbine geometry VTG
WO2011069571A1 (fr) * 2009-12-10 2011-06-16 Daimler Ag Turbine pour un dispositif de suralimentation et procédé pour le montage d'une telle turbine
KR20110068847A (ko) 2009-12-16 2011-06-22 보르그워너 인코퍼레이티드 배기 가스 터보차저
EP2336495A1 (fr) 2009-12-16 2011-06-22 BorgWarner, Inc. Turbosoufflante de gaz d'échappement
DE102009058411A1 (de) 2009-12-16 2011-06-22 BorgWarner Inc., Mich. Abgasturbolader
DE102011005151A1 (de) * 2011-03-04 2012-09-06 Bayerische Motoren Werke Aktiengesellschaft Abgasturbolader für eine Brennkraftmaschine
WO2013072732A1 (fr) * 2011-11-16 2013-05-23 Toyota Jidosha Kabushiki Kaisha Turbocompresseur
US20150198164A1 (en) * 2014-01-15 2015-07-16 General Electric Company Rotary machine having a volute assembly-bearing housing joint with interlocking teeth
US9909589B2 (en) * 2014-01-15 2018-03-06 General Electric Company Rotary machine having a volute assembly-bearing housing joint with interlocking teeth
USD777212S1 (en) 2015-06-20 2017-01-24 General Electric Company Nozzle ring
WO2020001805A1 (fr) * 2018-06-27 2020-01-02 Ihi Charging Systems International Gmbh Turbocompresseur de gaz d'échappement avec couronne directrice centrée
CN112292511A (zh) * 2018-06-27 2021-01-29 Ihi供应系统国际有限责任公司 具有定心的导向叶片环的废气涡轮增压器
US11220957B2 (en) 2018-06-27 2022-01-11 Ihi Charging Systems International Gmbh Exhaust gas turbocharger

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