EP3073064B1 - Turbocompresseur - Google Patents

Turbocompresseur Download PDF

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Publication number
EP3073064B1
EP3073064B1 EP16165283.9A EP16165283A EP3073064B1 EP 3073064 B1 EP3073064 B1 EP 3073064B1 EP 16165283 A EP16165283 A EP 16165283A EP 3073064 B1 EP3073064 B1 EP 3073064B1
Authority
EP
European Patent Office
Prior art keywords
vane
stop
guide
turbocharger
lever
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.)
Ceased
Application number
EP16165283.9A
Other languages
German (de)
English (en)
Other versions
EP3073064A1 (fr
Inventor
Ralf Böning
Dietmar Metz
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
Publication of EP3073064A1 publication Critical patent/EP3073064A1/fr
Application granted granted Critical
Publication of EP3073064B1 publication Critical patent/EP3073064B1/fr
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/04—Multi-stage pumps specially adapted to the production of a high vacuum, e.g. molecular pumps
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/16—Centrifugal pumps for displacing without appreciable compression
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/54—Building or constructing in particular ways by sheet metal manufacturing
    • 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
    • F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
    • 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
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • 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

Definitions

  • the invention relates to a turbocharger according to the preamble of claim 1.
  • Such a turbocharger is from the EP 1 564 380 A1 known.
  • this document proposes a stop which is integrally connected to the adjusting ring.
  • the projection of the stop of the known turbocharger limits the end positions by contact with mounting rings of the adjusting lever on the blades, which also makes precise adjustment of the end positions difficult, since the mounting rings of these blade adjustment levers are subject to manufacturing tolerances and on the other hand, due to the positioning (division) inaccuracies arise.
  • turbocharger specified in the preamble of claim 1, which allows a simplification of the assembly of the guide grid or diffuser, at least a simple and accurate adjustment of the minimum flow through the diffuser should be possible alone.
  • the stop with which at least one setting of the minimum flow through the nozzle cross-sections formed by the vanes is possible, is formed as a separate component which is fixable in the guide grid, it is possible after mounting the guide grid this stop in a simple way and way to rework the exact setting of the required stop position, since it is not integrally connected to the guide grid. If the need for a readjustment of one of the two end positions of the guide grid, it can be either simply selected and mounted a suitable fitment for the desired end position or adapted the intended stop member by reworking the projection and then mounted in the guide grille. Thus, it is possible to make a precise end position targeted, which is problematic in the generic turbocharger due to the integral formation of the stop.
  • the entire diffuser can be completely pre-assembled as a cartridge and the minimum flow can be adjusted before it is then inserted into the turbine housing.
  • the adjustment of the minimum flow is thus independent of turbine housing and other components of the turbocharger, such as e.g. the bearing housing. Also, the nozzle position between the bearing and turbine housing no longer has any influence on the minimum flow setting. Also, the wear of the adjusting lever and its engagement with the adjusting ring does not affect the minimum flow rate.
  • a guide grid is defined as each independently tradable objects.
  • FIG. 1 an inventive turbocharger 1 is shown, which has a turbine housing 2 and a compressor housing 3 connected thereto via a bearing housing 19.
  • the housings 2, 3 and 19 are arranged along a rotation axis R.
  • the turbine housing 2 is shown partially in section to illustrate the arrangement of a vane ring 6 as part of a radially outer baffle 18 having a plurality of circumferentially spaced vanes 7 with pivot shafts 8.
  • nozzle cross-sections are formed, which are larger or smaller depending on the position of the guide vanes 7 and the turbine rotor 4 mounted in the middle on the axis of rotation R more or less with the supplied via a feed channel 9 and discharged via a central port 10 exhaust gas of an engine, to drive over the turbine rotor 4 a seated on the same shaft compressor rotor 17.
  • an actuating device 11 is provided.
  • This can be designed to be arbitrary, but a preferred embodiment, 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 has integrally formed spacers 16.
  • 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 However, it is possible to provide more or less such spacers 16.
  • Fig. 2 is a partial perspective view of the guide grid 18 shown on an enlarged scale.
  • a blade lever 20 is shown having at one end a mounting ring 21 with a recess 22 in which one end of the blade shaft 8 is fixed.
  • a lever head 23 of the blade lever 20 is disposed in an engagement recess 24 of the adjusting ring 5 and thus is engaged with the adjusting ring 5 in engagement.
  • FIG. 2 the arrangement of a stop 25 in the form of a separate component.
  • the stop 25 has a stop body 26, which has been fixed in the illustrated embodiment on the blade bearing ring 6.
  • the stopper body 6 has a radially outwardly projecting projection 27, which engages in a groove 31 of the adjusting ring 5.
  • the groove 31 of the adjusting ring 5 is bounded by two stop cams 29 and 30.
  • the stop cams 29 and 30 have inwardly into the groove 31 facing abutment abutment surfaces which can engage with the corresponding adjacent surface of the projection 27.
  • a stop position on the stop cam 29 for adjusting the minimum flow through the nozzle cross sections of the guide grid 18 is shown.
  • a stop web 28 is arranged at the upper end of a side facing the stop cam 29 side surface 34 which extends at right angles to the side surface 34.
  • This stop bar 28 can be reworked for exact position adjustment in case of need, should In the course of the assembly of the guide grid 18 it turns out that the exact position can not yet be set.
  • the stop 25 can then be separated from the blade bearing ring 6 and be reworked in a precision device by removing a suitable portion of the stop web 28.
  • Fig. 3 an embodiment of the guide grid 18 according to the invention is shown.
  • all parts that are those of Fig. 2 provided with the same reference numerals, so that reference can be made in terms of training and function to the above description.
  • the stop 25 of the second embodiment is provided with an adjusting plate 32.
  • the adjusting plate 32 has a fixing plate 35 which can be fixed to the stopper body 26, such as by a Fixierclip 36.
  • Fixierclip 36 any other types of mounting options for the adjusting plate 32 on the stopper body 26 are conceivable.
  • the adjusting plate 32 is provided in this embodiment with a stop plate 33 which extends parallel to the side surface 34 of the projection 27 and to this one Fig. 3 apparent distance, so as to be able to define the exact stop position.
  • the stop position can be effected by the replacement of the adjusting plate 32, so that in this embodiment, an exact adjustment, in particular the minimum flow, in a simple and cost-effective manner is possible.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Claims (6)

  1. Turbocompresseur (1) à géométrie de turbine variable (VTG), comprenant
    - un carter de turbine (2) avec un canal d'alimentation (9) pour les gaz d'échappement ;
    - un rotor de turbine (4) qui est supporté de manière rotative dans le carter de turbine (2) ; et
    - un aubage directeur (18),
    - qui entoure radialement à l'extérieur le rotor de turbine (4),
    - qui présente un anneau de support d'aubes (6),
    - qui présente une pluralité d'aubes directrices (7) qui présentent chacune un arbre d'aube (8) supporté dans l'anneau de support d'aubes (6),
    - qui présente un anneau de réglage (5) qui est en liaison fonctionnelle avec les aubes directrices (7) par le biais de leviers d'aubes (20) associés, fixés au niveau des arbres d'aubes (8) au niveau de l'une de leurs extrémités, chaque levier d'aube (20) présentant à l'autre extrémité une tête de levier (23) qui peut être amenée en prise avec un évidement d'engagement associé (24) de l'anneau de réglage (5), et
    - qui présente une butée (25) au moins pour l'ajustement du flux minimal à travers les sections transversales de buse formées par les zones directrices (7),
    - la butée (25) étant réalisée sous forme de composant séparé pouvant être fixé dans l'aubage directeur (18),
    caractérisé en ce que
    - la butée (25) peut être fixée à l'anneau de support d'aubes (6) et présente une saillie (27) qui s'engage dans une rainure (31) de l'anneau de réglage (5), et
    - en ce que la butée (25) est pourvue d'une tôle d'ajustement (32) qui présente une plaque de butée (33) qui s'étend parallèle à une surface latérale (34) de la saillie (27) et est éspacée de la surface latérale (34).
  2. Turbocompresseur selon la revendication 1, caractérisé en ce que la tôle d'ajustement (32) est réalisée sous la forme d'un composant remplaçable, de dimensions variables et pouvant être fixé à une butée (25).
  3. Turbocompresseur selon la revendication 1 ou 2, caractérisé en ce que le flux minimal est ajusté par le positionnement de l'arbre d'aubes (8) par rapport au levier d'aube (20).
  4. Aubage directeur (18) pour un turbocompresseur (1) à géométrie de turbine variable (VTG), qui entoure radialement à l'extérieur un rotor de turbine (4) du turbocompresseur (1) et qui présente les pièces suivantes :
    - un anneau de support d'aubes (6),
    - une pluralité d'aubes directrices (7) qui présentent chacune un arbre d'aube (8) supporté dans l'anneau de support d'aubes (6),
    - un anneau de réglage (5) qui est en liaison fonctionnelle avec les aubes directrices (7) par le biais de leviers d'aubes associés (20) fixés au niveau des arbres d'aubes (8) au niveau de l'une de leurs extrémités, chaque levier d'aube (20) présentant à l'autre extrémité une tête de levier (32) qui peut être amenée en prise avec un évidement d'engagement associé (24) de l'anneau de réglage (5), et
    - une butée (25) au moins pour l'ajustement du flux minimal à travers les sections transversales de buse formées par les aubes directrices (7),
    - la butée (25) étant réalisée sous forme de composant séparé pouvant être fixé dans l'aubage directeur (18),
    caractérisé en ce que
    - la butée (25) peut être fixée à l'anneau de support d'aubes (6) et présente une saillie (27) qui s'engage dans une rainure (31) de l'anneau de réglage (5), et
    - en ce que la butée (25) est pourvue d'une tôle d'ajustement (32).
  5. Aubage directeur selon la revendication 4, caractérisé en ce que la tôle d'ajustement (32) est réalisée sous la forme d'un composant remplaçable, de dimensions variables et pouvant être fixé à une butée (25).
  6. Aubage directeur selon la revendication 4 ou 5, caractérisé en ce que le flux minimal est ajusté par le positionnement de l'arbre d'aubes (8) par rapport au levier d'aube (20).
EP16165283.9A 2006-05-19 2007-05-16 Turbocompresseur Ceased EP3073064B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006023923 2006-05-19
EP07725312.8A EP2018480B1 (fr) 2006-05-19 2007-05-16 Turbocompresseur

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP07725312.8A Division EP2018480B1 (fr) 2006-05-19 2007-05-16 Turbocompresseur
EP07725312.8A Division-Into EP2018480B1 (fr) 2006-05-19 2007-05-16 Turbocompresseur

Publications (2)

Publication Number Publication Date
EP3073064A1 EP3073064A1 (fr) 2016-09-28
EP3073064B1 true EP3073064B1 (fr) 2017-09-20

Family

ID=38353448

Family Applications (2)

Application Number Title Priority Date Filing Date
EP16165283.9A Ceased EP3073064B1 (fr) 2006-05-19 2007-05-16 Turbocompresseur
EP07725312.8A Ceased EP2018480B1 (fr) 2006-05-19 2007-05-16 Turbocompresseur

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP07725312.8A Ceased EP2018480B1 (fr) 2006-05-19 2007-05-16 Turbocompresseur

Country Status (7)

Country Link
US (1) US8328520B2 (fr)
EP (2) EP3073064B1 (fr)
JP (1) JP2009537727A (fr)
KR (1) KR101400878B1 (fr)
CN (1) CN101438062A (fr)
BR (1) BRPI0709404B1 (fr)
WO (1) WO2007134787A1 (fr)

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US8122716B2 (en) * 2008-06-04 2012-02-28 Honeywell International Inc. VNT flow calibration adjustment
DE102008035749B4 (de) 2008-07-31 2018-05-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader
CN102159794B (zh) * 2008-09-18 2015-04-15 西门子公司 用于可变导向叶片的方法、系统和装置
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
KR101031633B1 (ko) * 2009-04-17 2011-04-27 (주)계양정밀 가변 지오메트리 터보차져의 노즐어셈블리 및 그 제작방법
JP5907884B2 (ja) * 2009-11-27 2016-04-26 ボーグワーナー インコーポレーテッド ターボチャージャ
DE112010004596T5 (de) * 2009-11-27 2013-01-24 Borgwarner Inc. Turbolade
DE102009057664A1 (de) * 2009-12-09 2011-06-16 Ihi Charging Systems International Gmbh Verstelleinrichtung für eine Aufladeeinrichtung, insbesondere für einen Abgasturbolader
KR101739400B1 (ko) 2010-03-03 2017-05-24 보르그워너 인코퍼레이티드 스탬핑된 조절 링 조립체를 구비한 비용 절감된 가변구조 터보차저
JP5787988B2 (ja) * 2010-05-19 2015-09-30 ボーグワーナー インコーポレーテッド ターボチャージャ
DE112011103045T5 (de) * 2010-09-27 2013-07-04 Borgwarner Inc. Verfahren zur Herstellung eines Turboladers
DE102010043145B4 (de) 2010-10-29 2022-02-10 BMTS Technology GmbH & Co. KG Variable Turbinen-/Verdichtergeometrie
CN103189613B (zh) * 2010-12-08 2015-11-25 博格华纳公司 排气涡轮增压器
US9506371B2 (en) * 2011-08-08 2016-11-29 Borgwarner Inc. Turbocharger
IN2014DN07030A (fr) * 2012-02-02 2015-04-10 Borgwarner Inc
JP6175491B2 (ja) * 2012-04-27 2017-08-02 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
JP6588826B2 (ja) 2012-11-23 2019-10-09 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
DE112014000758T5 (de) * 2013-03-11 2015-10-22 Borgwarner Inc. Abgasturbolader
JP5984789B2 (ja) * 2013-12-16 2016-09-06 株式会社アキタファインブランキング Ｖｇｓタイプターボチャージャにおける排気ガイドアッセンブリ
DE102016203025A1 (de) * 2016-02-26 2017-08-31 Bosch Mahle Turbo Systems Gmbh & Co. Kg Variable Turbinengeometrie
JP6642718B2 (ja) * 2016-08-08 2020-02-12 株式会社Ihi 可変容量型過給機
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Also Published As

Publication number Publication date
BRPI0709404A2 (pt) 2011-07-12
US8328520B2 (en) 2012-12-11
KR20090010199A (ko) 2009-01-29
KR101400878B1 (ko) 2014-05-29
EP2018480B1 (fr) 2016-06-15
EP2018480A1 (fr) 2009-01-28
WO2007134787A1 (fr) 2007-11-29
US20100014961A1 (en) 2010-01-21
BRPI0709404B1 (pt) 2019-08-06
EP3073064A1 (fr) 2016-09-28
CN101438062A (zh) 2009-05-20
JP2009537727A (ja) 2009-10-29

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