EP1676980B1 - Turbocompresseur à géométrie variable - Google Patents

Turbocompresseur à géométrie variable Download PDF

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Publication number
EP1676980B1
EP1676980B1 EP04030888.4A EP04030888A EP1676980B1 EP 1676980 B1 EP1676980 B1 EP 1676980B1 EP 04030888 A EP04030888 A EP 04030888A EP 1676980 B1 EP1676980 B1 EP 1676980B1
Authority
EP
European Patent Office
Prior art keywords
bearing ring
disc
turbocharger
support pin
vane bearing
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.)
Active
Application number
EP04030888.4A
Other languages
German (de)
English (en)
Other versions
EP1676980A1 (fr
Inventor
Ralf Böning
Dietmar Metz
Dirk Frankenstein
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
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=34928016&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1676980(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by BorgWarner Inc filed Critical BorgWarner Inc
Priority to EP04030888.4A priority Critical patent/EP1676980B1/fr
Priority to JP2005348934A priority patent/JP4578394B2/ja
Priority to KR1020050124596A priority patent/KR101172834B1/ko
Priority to CNB2005101340463A priority patent/CN100478546C/zh
Priority to US11/321,300 priority patent/US7507067B2/en
Publication of EP1676980A1 publication Critical patent/EP1676980A1/fr
Application granted granted Critical
Publication of EP1676980B1 publication Critical patent/EP1676980B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/04—Arrangement of sensing elements responsive to load
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer

Definitions

  • the invention relates to a blade bearing ring arrangement for a turbocharger with variable turbine geometry (VTG) according to the preamble of claim 1.
  • VFG variable turbine geometry
  • the VTG cartridge of such from the EP 1 236 866 A known turbocharger consists of a nozzle with blades and levers and turbine housing side disc. The attachment of the disc to a vane bearing ring of a vane bearing assembly takes place in generic turbochargers by means of screws or welding. To be able to set a defined width for the flow channel, which forms between the blade bearing ring and disc and in which the blades of the VTG are located, spacer sleeves are required, which can be removed in the case of a welded joint after welding again. By welding, however, a distortion of the disc caused by strong heat input. A distortion of the disc can lead to a clamping of the blades due to the consequent local gap reduction between blades and disc.
  • the solution of this object is achieved by the features of claim 1.
  • a heat choke is provided which surrounds the recess for the support pin end to be welded.
  • This heat choke is designed as a circumferential groove around the recess for the support pin end to be welded.
  • the first end of the support pins can be screwed, riveted or otherwise fixed to the disc.
  • the support pins preferably have a very small diameter of a few millimeters, so that the resulting flow cross-section reduction and the associated Strömungsverwirbelonne remain minimal.
  • FIG. 2 only one vane bearing assembly 1 of a turbocharger according to the invention shown.
  • the blade bearing arrangement 1 has a blade bearing ring 2, on which a disc 3 is arranged at a defined distance.
  • the disc 3 is preferably formed of the same material as the blade bearing ring 2 and serves, as stated, to set an exact axial gap in order to define a flow channel 4 can.
  • a support pin 5 For attachment of the disc 3 on the blade bearing ring 2 is at least one, but usually provided a plurality of support pins, of which in Fig. 2 a support pin 5 is visible.
  • the support pin 5 has a first and a second end 6 and 7, respectively. Between the ends 6 and 7, a shaft region 8 arranged in the flow channel 4 is arranged in the assembled state.
  • the second end 7 of the support pin 5 is disposed in a recess 11 of the disc 3 and connected in a flared area 12 of the recess 11 with the disc 3 via a weld 13.
  • the end 7 is roof-like tapered at its end face in order to achieve a perfecting of the weld 13 can.
  • a heat choke in the form of a circumferential groove 14 is provided, which prevents the heat can penetrate directly into the massive part of the disc 3, which helps to avoid distortion of the disc 3 during welding and also reduces the required input welding energy.
  • the disc 3 is provided with one recess 11 per support pin 5, wherein each of these recesses 11 the above-described heat choke in the form of the circumferential groove 14 is attached.
  • the first end 6 of the support pin 5 is screwed to the blade bearing ring 2 for fixing the disc 3 on the blade bearing ring 2.
  • spacers between the blade bearing ring 2 and disc 3 are inserted to the defined distance to be able to adjust between the blade bearing ring 2 and the disc 3.
  • the welding of the second end 7 and the removal of the spacers takes place.

Claims (4)

  1. Agencement de bague de palier d'aube (1) pour un turbocompresseur à géométrie de turbine variable, comprenant
    - une bague de palier d'aube (2) et une rondelle (3), qui peut être fixée sur la bague de palier d'aube (2) pour réaliser un canal d'écoulement (4) ; et
    - au moins une broche de support (5) qui est connectée par sa première extrémité (6) à la bague de palier d'aube (2) et qui est soudée par sa deuxième extrémité (7) à la rondelle (3), laquelle, pour chaque broche de support (5), présente un évidement (11) pour l'extrémité de broche de support (7) à souder, lequel est entouré par une restriction thermique (14), caractérisé en ce que
    - la restriction thermique est réalisée sous forme de rainure (14) entourant l'évidement (11).
  2. Agencement de bague de palier d'aube selon la revendication 1, caractérisé en ce que la première extrémité (6) de la broche de support (5) est pourvue d'un filetage extérieur (9).
  3. Agencement de bague de palier d'aube selon la revendication 1 ou 2, caractérisé en ce que la broche de support (5) présente une portion de tige (8) entre la première et la deuxième extrémité (6, respectivement 7), dont le diamètre extérieur est rétréci.
  4. Turbocompresseur à géométrie de turbine variable comprenant un agencement de bague de palier d'aube selon l'une quelconque des revendications 1 à 3.
EP04030888.4A 2004-12-28 2004-12-28 Turbocompresseur à géométrie variable Active EP1676980B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP04030888.4A EP1676980B1 (fr) 2004-12-28 2004-12-28 Turbocompresseur à géométrie variable
JP2005348934A JP4578394B2 (ja) 2004-12-28 2005-12-02 可変タービン形状のターボ過給機
KR1020050124596A KR101172834B1 (ko) 2004-12-28 2005-12-16 가변 터빈 구조의 터보차저
CNB2005101340463A CN100478546C (zh) 2004-12-28 2005-12-27 涡轮几何尺寸可变的涡轮增压器
US11/321,300 US7507067B2 (en) 2004-12-28 2005-12-28 Turbocharger of variable turbine geometry

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04030888.4A EP1676980B1 (fr) 2004-12-28 2004-12-28 Turbocompresseur à géométrie variable

Publications (2)

Publication Number Publication Date
EP1676980A1 EP1676980A1 (fr) 2006-07-05
EP1676980B1 true EP1676980B1 (fr) 2015-10-14

Family

ID=34928016

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04030888.4A Active EP1676980B1 (fr) 2004-12-28 2004-12-28 Turbocompresseur à géométrie variable

Country Status (5)

Country Link
US (1) US7507067B2 (fr)
EP (1) EP1676980B1 (fr)
JP (1) JP4578394B2 (fr)
KR (1) KR101172834B1 (fr)
CN (1) CN100478546C (fr)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2009526938A (ja) * 2006-02-16 2009-07-23 ボーグワーナー・インコーポレーテッド 可変タービンジオメトリを有するターボチャージャのブレード支持リング組立体
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
DE102008005658A1 (de) * 2008-01-23 2009-07-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
AT504758B1 (de) * 2008-04-03 2009-06-15 Avl List Gmbh Abgasturbolader mit einer abgasturbine
AT504446B1 (de) * 2008-01-24 2009-05-15 Avl List Gmbh Abgasturbolader
AT504757B1 (de) * 2008-04-03 2009-08-15 Avl List Gmbh Abgasturbolader mit einer abgasturbine
US8021107B2 (en) * 2008-02-25 2011-09-20 Honeywell International Inc. Variable-nozzle assembly for a turbocharger
DE102008039093A1 (de) * 2008-08-21 2010-02-25 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader für ein Kraftfahrzeug
WO2012047527A2 (fr) * 2010-09-27 2012-04-12 Borgwarner Inc. Procédé de fabrication d'un turbocompresseur
JP5849151B2 (ja) * 2011-04-11 2016-01-27 ボーグワーナー インコーポレーテッド 排気ガスターボチャージャの軸受ハウジング
AU2011381039A1 (en) * 2011-11-16 2014-05-29 Mack Trucks, Inc. Diesel engine arrangement and method for varnish build-up control
JP6111260B2 (ja) * 2011-11-23 2017-04-05 ボーグワーナー インコーポレーテッド 排気ガスターボチャージャ
KR101983756B1 (ko) * 2012-03-15 2019-09-03 보르그워너 인코퍼레이티드 배기가스 터보차저
US11085320B2 (en) * 2018-09-25 2021-08-10 Garrett Transportation I Inc Variable vane mechanism of turbocharger having predetermined vane clearance
DE102019217316A1 (de) * 2019-11-08 2021-05-12 Volkswagen Aktiengesellschaft Abgasturbolader für Hochleistungsmotorkonzepte
CN110925242B (zh) * 2019-12-13 2020-12-15 宗立君 一种涡轮增压器

Family Cites Families (12)

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Publication number Priority date Publication date Assignee Title
JPS60169604A (ja) * 1984-02-15 1985-09-03 Nissan Motor Co Ltd ラジアルタ−ビン可変ノズル
DE3516738A1 (de) * 1985-05-09 1986-11-13 Mtu Motoren- Und Turbinen-Union Friedrichshafen Gmbh, 7990 Friedrichshafen Stroemungsmaschine
DE3541508C1 (de) * 1985-11-23 1987-02-05 Kuehnle Kopp Kausch Ag Abgasturbolader
DE3941715A1 (de) * 1989-12-18 1991-06-20 Porsche Ag Abgasturbolader fuer eine brennkraftmaschine
US5207565A (en) * 1992-02-18 1993-05-04 Alliedsignal Inc. Variable geometry turbocharger with high temperature insert in turbine throat
JP3664761B2 (ja) * 1994-12-22 2005-06-29 三菱重工業株式会社 排気ターボ過給機の可変容量タービン
JPH1162603A (ja) * 1997-08-25 1999-03-05 Mitsubishi Heavy Ind Ltd 可変容量過給機
JP3771765B2 (ja) * 2000-01-24 2006-04-26 三菱重工業株式会社 可変ターボチャージャ
JP3735262B2 (ja) * 2001-02-27 2006-01-18 三菱重工業株式会社 可変容量タービン用可変ノズル機構およびその製作方法
JP2003049663A (ja) * 2001-08-03 2003-02-21 Sogi Kogyo Kk Ｖｇｓタイプターボチャージャにおける可変翼の製造方法並びにこの方法によって製造された可変翼
JP2003184563A (ja) * 2001-12-14 2003-07-03 Aisin Seiki Co Ltd 可変容量ターボチャージャ
DE50304673D1 (de) * 2003-10-27 2006-09-28 Borgwarner Inc Strömungsmaschine und Verfahren zum Herstellen eines Leitgitters

Also Published As

Publication number Publication date
KR101172834B1 (ko) 2012-08-10
JP4578394B2 (ja) 2010-11-10
KR20060076206A (ko) 2006-07-04
US20060140751A1 (en) 2006-06-29
EP1676980A1 (fr) 2006-07-05
US7507067B2 (en) 2009-03-24
CN100478546C (zh) 2009-04-15
JP2006189041A (ja) 2006-07-20
CN1796729A (zh) 2006-07-05

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