EP1734231B1 - Turbocompresseur avec turbine a geometrie variable - Google Patents

Turbocompresseur avec turbine a geometrie variable Download PDF

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Publication number
EP1734231B1
EP1734231B1 EP05013040.0A EP05013040A EP1734231B1 EP 1734231 B1 EP1734231 B1 EP 1734231B1 EP 05013040 A EP05013040 A EP 05013040A EP 1734231 B1 EP1734231 B1 EP 1734231B1
Authority
EP
European Patent Office
Prior art keywords
bearing ring
blade bearing
turbine housing
turbine
turbocharger
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 - Fee Related
Application number
EP05013040.0A
Other languages
German (de)
English (en)
Other versions
EP1734231A1 (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.
  • a turbocharger is known from EP 0 204 033 A known.
  • Another turbocharger 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.
  • turbocharger according to the preamble of claim 1, which allow a simplification of assembly by reducing the items to be assembled.
  • An embodiment of the invention provides as a fastening device before 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 arrangement can be formed in a particularly preferred embodiment by a arranged on the side of the bearing housing disc spring and a heat shield, which faces 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 molded spacers 16, which in detail in FIGS. 2 and 3 are shown.
  • three spacers 16 are arranged at an angular distance of 120 ° in each case on the circumference of the blade bearing ring 6. In principle, it is possible to provide more or less such spacers 16, but results in accordance with the training Fig. 2 a particularly advantageous geometric arrangement.
  • a vane bearing ring 6 which has a fastening device 19 for fixing the vane bearing ring 6 on the turbine housing 2, which in one piece at least one of the spacers 16 is arranged.
  • 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 centering shoulder 23 is provided with respect to the main body 22 with a shoulder, so that adjacent to the groove 20, an axial bearing surface 24 and a radially aligned centering surface or a centering result.
  • FIGS. 5 and 6 an inventive turbocharger 1 and an inventive blade bearing ring 6 is shown.
  • 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 at least one of the spacers 16, which in the in the FIGS. 5 and 6 shown assembled state with a mating surface 27 of the turbine housing 2.
  • 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.
  • Particularly preferred embodiment further comprises a projection 29 which is arranged on an inner peripheral surface 30 of the blade bearing ring 6, which in detail from the FIGS. 5 and 6 results.
  • 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 disc assembly 32, which is mainly from the enlarged view of Fig. 6 is apparent.
  • the disc assembly 32 has a conical disc spring 33 and a heat shield 34 disposed on sides of the turbine housing 2.
  • 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 is shown in detail from the illustration of Fig. 7 results.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Claims (5)

  1. Turbocompresseur (1) à géométrie de turbine variable (VTG)
    - avec un carter de turbine (2) avec un conduit d'admission (9) pour des gaz d'échappement ;
    - avec un rotor de turbine (4) qui est supporté de manière rotative dans le carter de turbine (2) ;
    - avec un aubage directeur (18) de géométrie de turbine variable, qui entoure radialement à l'extérieur le rotor de turbine (4) et qui présente un anneau de support d'aubes (6) qui est pourvu d'éléments d'espacement (16) pour maintenir un espace libre (13) pour des aubes directrices (7) de l'aubage directeur (18) ; et
    - avec un dispositif de fixation (19 ; 19') formé d'une seule pièce au niveau d'au moins l'un des éléments d'espacement (16) pour la fixation de l'anneau de support d'aubes (6) au niveau du carter de turbine (2),
    caractérisé en ce que
    - le dispositif de fixation (19') est réalisé sous forme de surface de centrage orientée radialement (26) qui, dans l'état de montage de l'anneau de support d'aubes (6), forme un ajustement serré avec une surface conjuguée (27) du carter de turbine (2).
  2. Turbocompresseur selon la revendication 1, caractérisé en ce que l'anneau de support d'aubes (6) présente une saillie (29) faisant saillie radialement vers l'intérieur, au niveau de sa surface périphérique interne (30).
  3. Turbocompresseur selon la revendication 2, caractérisé en ce que la saillie (29) est disposée au niveau de l'extrémité axiale (31) de l'anneau de support d'aubes (6) adjacente aux éléments d'espacement (16).
  4. Turbocompresseur selon la revendication 2 ou 3, caractérisé en ce que la saillie (29), dans l'état de montage de l'anneau de support d'aubes (6), coopère avec un agencement de disque (32), de préférence constitué d'un ressort Belleville (33) et d'un bouclier thermique (34) tourné vers le carter de turbine (2), pour former un serrage axial de l'anneau de support d'aubes (6) entre le logement de palier (28) et le carter de turbine (2).
  5. Turbocompresseur selon l'une quelconque des revendications 1 à 4, caractérisé en ce qu'entre le carter de turbine (2) et l'anneau de support d'aubes (6) est disposé un disque intermédiaire (35).
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 EP1734231A1 (fr) 2006-12-20
EP1734231B1 true 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 (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11174868B2 (en) 2019-03-25 2021-11-16 Kabushiki Kaisha Toyota Jidoshokki Turbocharger

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7918023B2 (en) * 2007-02-08 2011-04-05 Honeywell International Inc. Method for manufacturing a variable-vane mechanism for a turbocharger
ATE522702T1 (de) * 2007-12-12 2011-09-15 Honeywell Int Inc Variable düse für einen turbolader mit durch radiale glieder positioniertem düsenring
DE102008000776B4 (de) 2008-01-21 2022-04-14 BMTS Technology GmbH & Co. KG Turbine mit varialber Turbinengeometrie, insbesondere für einen Abgasturbolader, sowie Abgasturbolader
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
DE102008029080B4 (de) 2008-06-19 2022-04-21 BMTS Technology GmbH & Co. KG Abgasturbolader für ein Kraftfahrzeug
DE102008051041B4 (de) * 2008-10-09 2014-03-13 Continental Mechanical Components Germany Gmbh Turbolader mit Befestigungselementen zum Befestigen von Schaufellagerringen einer variablen Turbinengeometrie VTG
DE102009057742A1 (de) * 2009-12-10 2011-06-16 Daimler Ag Turbine für eine Aufladeeinrichtung sowie Verfahren zur Montage einer solchen Turbine
EP2336495B1 (fr) 2009-12-16 2012-03-07 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
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
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
DE102018115448A1 (de) 2018-06-27 2020-01-02 Ihi Charging Systems International Gmbh Abgasturbolader
CN117553010A (zh) * 2022-08-05 2024-02-13 盖瑞特动力科技(上海)有限公司 具有用于压缩机的叶片式扩散器的涡轮增压器

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Publication number Priority date Publication date Assignee Title
DE3516738A1 (de) * 1985-05-09 1986-11-13 Mtu Motoren- Und Turbinen-Union Friedrichshafen Gmbh, 7990 Friedrichshafen Stroemungsmaschine
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
EP1528225B1 (fr) * 2003-10-27 2006-08-16 BorgWarner Inc. Turbomachine et méthode de fabrication pour un anneau de guidage

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11174868B2 (en) 2019-03-25 2021-11-16 Kabushiki Kaisha Toyota Jidoshokki Turbocharger

Also Published As

Publication number Publication date
EP1734231A1 (fr) 2006-12-20

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