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EP1398463B1 - Aubes de guidage variables et turbosoufflante avec ces aubes - Google Patents

Aubes de guidage variables et turbosoufflante avec ces aubes Download PDF

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Publication number
EP1398463B1
EP1398463B1 EP02020412A EP02020412A EP1398463B1 EP 1398463 B1 EP1398463 B1 EP 1398463B1 EP 02020412 A EP02020412 A EP 02020412A EP 02020412 A EP02020412 A EP 02020412A EP 1398463 B1 EP1398463 B1 EP 1398463B1
Authority
EP
European Patent Office
Prior art keywords
sleeve
guiding grid
vanes
turbine housing
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
EP02020412A
Other languages
German (de)
English (en)
Other versions
EP1398463A1 (fr
Inventor
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 DE50207509T priority Critical patent/DE50207509D1/de
Priority to EP02020412A priority patent/EP1398463B1/fr
Priority to JP2003312620A priority patent/JP4755393B2/ja
Priority to US10/659,786 priority patent/US6916153B2/en
Publication of EP1398463A1 publication Critical patent/EP1398463A1/fr
Application granted granted Critical
Publication of EP1398463B1 publication Critical patent/EP1398463B1/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
    • 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

Definitions

  • the present invention relates to a variable geometry baffle, in particular for a turbine housing with a central outlet, with a ring of vanes arranged around a central axis, each of which is pivotable about a pivot axis, a vane ring for supporting the vanes around the central one Axle and an adjusting ring which is pivotable relative to the blade bearing ring about the central axis and is connected to the blades for adjusting their angular position in each case about their pivot axes.
  • Connections of this latter type have come to be known in a variety of ways, and may be formed by beams around the central axis of levers attached to vanes for the vanes, intermeshing tooth segments, or slot cams guiding lugs on the vanes.
  • the present invention is not limited to any of these compounds.
  • the present invention also relates to a turbocharger with a guide grid according to the invention as well as with at least one turbine housing and a releasably attachable to this bearing housing.
  • Guiding gratings of this type have become known from numerous publications, such as US-A-4,179,247 or US-A-5,146,752. Especially the latter shows how cumbersome to assemble the individual parts of the guide grid on the housing, as different parts must be plugged into each other, fitted and connected together, especially when installed in a turbocharger - or at least in a turbine unit.
  • US-A-4,679,984 shows a baffle according to the preamble of claim 1.
  • the invention is based on the object to reduce the installation costs by a simple and compact design and to be able to mount a guide grid of the type mentioned easily and quickly.
  • This object is achieved with a guide grid according to claim 1.
  • the object is achieved according to the invention in two stages in that the blade bearing ring opposite a central opening having disc with such an axial distance, based on the central axis, is arranged, that between it and the blade bearing ring, the ring of vanes, and that at the central opening at least one driver engages, which is attached to a retractable into the central outlet of the turbine housing sleeve, so that the sleeve for axial fixing of the guide grid in a turbine housing together with the guide grid in the central outlet can be inserted and fastened.
  • the assembly of the actual, known guide grid does not have to take place directly on a wall of the turbine housing, as was the case in the prior art mentioned above, but via a disk having a central opening.
  • the assembly can be done by frictional retention of the sleeve in the central opening. But once you have provided the disc, then the module thus created (the "cassette") in a preferred manner in the turbine housing can be secured by providing the sleeve with at least one driver.
  • This at least one driver is preferably formed by a radially extending and the disc engaging behind the flange.
  • the invention also relates to a turbocharger having such a guide grid, which has at least one turbine housing and a releasably attachable to this bearing housing.
  • This turbocharger is inventively characterized in that on a bearing housing facing the opening of the outlet nozzle surrounding wall of the turbine housing at least one connector for radially fixing the guide grid is provided, whereas the axial fixing is carried out by a sleeve in the outlet holding fixture. In this way, an exact attachment in the shortest possible time and with minimal effort can be achieved.
  • a part of a turbine housing 2 of a turbocharger 1 is shown, which typically has a spiral about a central axis R winding supply channel 9 for a fluid - in the case of a turbocharger of the exhaust gas of an internal combustion engine - has.
  • This fluid is then supplied in the radial direction through a, known per se, arranged around the central axis R ring of vanes 7 a located on the axis R, not shown turbine rotor, which sits at the end of a (also not shown) shaft, the in a bearing housing 40, in bearings 41 and 41 'formed therein.
  • this shaft extends through this bearing housing 40 through to a compressor housing attached to the other end, the compressor rotor of the shaft - and thus of the turbine housing 2 supplied exhaust gases is driven in a known manner.
  • Fig. 2 illustrates these relationships, wherein a rolling bearing with rolling elements 3 in the form of rollers between an adjusting ring 5 and a blade bearing ring 6, in which the pivot axes of the vanes 7 forming adjusting shafts 8 are mounted.
  • the rotation or adjustment of the adjusting shafts 8 and the adjusting ring 5 which actuates them can be effected in a manner known per se and, for example, in the aforementioned US Pat. No. 4,659,295. In any case, causes the known control that the adjusting 5 rotates relative to the stationary blade bearing ring, resulting in a corresponding pivoting of the shafts 8.
  • the exhaust gas of an internal combustion engine supplied via the supply channel 9 is more or less supplied to the turbine rotor (not shown) located in the interior of the guide vane ring, before it exits again at the axial connection piece 10 extending along the central axis of rotation R.
  • This outlet 10 is here decoupled by a decoupling space 42 of a follow it 43, but if desired, it can also be connected directly to an exhaust system.
  • the adjusting ring 5 has a radially inwardly directed running surface 20, on which the rollers 3 can run off. However, this is preferably provided only for tolerance compensation, because in practice it is preferred if the rollers 3 in substantially all operating conditions both with respect to this tread 20 and an opposite outer, forming a shoulder tread 21 on the blade bearing ring 6 have a certain play.
  • rollers 3 are required if a cage or retaining ring 22 is assigned to them.
  • the rollers 3 could also run in recesses of this retaining ring 22, the rollers 3 advantageously have axial extensions 24 of smaller diameter, which engage in holes 25 of the retaining ring 22 so that this one hand ensures their distance in the circumferential direction and on the other hand, the rollers and axially fixed on their track opposite the treads 20 and 21 holds.
  • a sealing ring 27 is inserted into a sealing groove 28 of the blade bearing ring 6.
  • the blade bearing ring 6 lies in the region of a housing wall section 2a.
  • Either the sealing ring 27 is formed as a flexible sealing lip, which lays against the wall 2a. This is not a problem in itself, because these two parts do not move relative to each other during operation. But it can also (possibly additionally) the (or a) sealing ring 27 protrude into a groove of the wall 2a and form a kind of labyrinth seal, and combinations of both possibilities are also possible, as can be found in the field of seals known solutions application. In any case, contaminants from the area of the feed channel 9 are kept away from the rolling bearing 3, 20, 21 with this seal.
  • a blade 7 protective mounting ring or a disc 29 is provided which is mounted on the rotor housing 2 approximately in the region of the apparent from Fig. 1 housing flange 2b.
  • the fastening ring 29 is indicated by dashed lines, e.g. fastened by the sleeves 31 bolt 30 'attached to the blade bearing ring 6, wherein in a known manner, the spacers 31 provide for a slightly greater distance than the width of the blades 7 corresponds, so as not to hinder them in their movement in all temperature ranges. In this way, therefore, the visible from Fig. 2 Leitgitter can be completely pre-assembled to be inserted into the turbine housing 2.
  • the sleeve 45 has at least one driver 46, which carries the disc 29 - and thus the whole Leitgitter module - when inserted into the outlet port 10 and thus determines the axial position of the module.
  • driver 46 it should be understood that it would be possible to provide a plurality of radially protruding projections or projections, in particular at uniform angular intervals, over the circumference of the sleeve 45. It is preferred, however, if - as shown in Fig. 2 - the driver as radially extending from the sleeve 45 extending, the disc 29 engages behind the flange 46 is formed.
  • the disc 29 at the central opening at least one recess 47, in which the at least one driver 46 engages, so that it is preferably flush with the surface of the disc 29.
  • a plurality of recesses distributed over the circumference could also be provided. This would be done at the same time a precise definition of the Leitgitter module in the direction of rotation around the central axis R.
  • the recess 47 is formed as a groove extending in the circumferential direction of the sleeve 45 (see FIG. Fig.
  • At least one bore 48 (FIG. 2) and / or 48 '(FIG. 1) is preferably provided in the disc 29, which accommodates a pin 49 seated in the turbine housing 2, specifically in the wall 2b. It has already been pointed out above that the fixing in the circumferential direction could also take place through the recesses (at least one). According to another alternative, the arrangement could be reversed, so that the disc 29, for example a molded, carries pin which is inserted into a hole of the wall 2b. Furthermore, the definition in the circumferential direction could also be done with the help of bolts, but this is not preferred because of the additional assembly costs.
  • the turbine housing 2 is machined so that the insertion of the sleeve 45 by screwing by means of a thread 50 takes place. Therefore, an internal thread must be cut into the axial neck 10, into which a corresponding external thread of the sleeve 45 can be screwed. In itself, the axial fixing is secured when the disc 29 abuts the wall 2b. However, vibrations during operation may cause the thread to loosen. Therefore, for securing the sleeve 45 can be welded or plastically deformed.
  • a heat shield 32 between the bearing housing 40 and the space enclosed by the guide grid.
  • This heat shield is in the present embodiment on the one hand on a surface of the guide rail - expedient on the blade bearing ring 6.
  • the blade bearing ring 6 at least one radially inwardly (with respect to the central axis R) directed projection 54 have.
  • the heat shield is located on a wall of the bearing housing 40.
  • other arrangements are possible.
  • sleeve 45 In general this will be difficult with a rigid sleeve 45, but it would be possible to use the left end of sleeve 45 in Fig. 1 as, e.g. in axial grooves of the axial neck 10 engaging, form spring tongues, which snap into corresponding locking projections.
  • this arrangement can be reversed again by the sleeve 45 has at least one radially outwardly projecting projection which engages in a recess of the axial neck 10.
  • the recesses 51 will expediently serve at least for applying a corresponding tool.
  • a further possibility in the context of the invention would be to not determine the end position of the guide grid module by the surface of the wall 2b facing it, but to make it adjustable by means of an adjusting arrangement.
  • an adjusting arrangement For example, from the left side (with reference to FIG. 1), at least one, preferably several, adjusting screws determine with their ends on the right side the plane in which the disc 29 is to lie.

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

Claims (10)

  1. Aubes de guidage à géométries variables, en particulier, pour un carter de turbine (2) à tubulure d'échappement (10) centrale, présentant les caractéristiques suivantes :
    une couronne, disposée autour d'un axe (R) central, d'aubes de guidage (7), qui, de leur côté, sont susceptibles de pivoter chacune autour d'un axe de pivotement (8) ;
    une bague de palier d'aube (8) pour le montage en palier des aubes (7) autour de l'axe central (R) ;
    une bague de manoeuvre (5), susceptible de pivoter par rapport à la bague de palier d'aube (6), autour de l'axe central (R), et reliée aux aubes (7) pour la manoeuvre de leur position angulaire chaque fois autour de leurs axes de pivotement (8) ;
    où
    à l'opposé de la bague de palier d'aube (6) est disposé un disque (29) présentant une ouverture (53) centrale, avec un espacement axial, par rapport à l'axe (R) central, tel que, entre le disque et la bague de palier d'aube (6), se trouve la couronne d'aubes de guidage (7), caractérisées en ce que, dans l'ouverture (53) central, respectivement la tubulure d'échappement (10) centrale, du carter de turbine (2) peut être insérée une douille (45) appartenant aux aubes de guidage, de manière que la douille (45) puisse être insérée et fixée, pour obtenir la fixation axiale des aubes de guidage, dans un carter de turbine (2), conjointement avec les aubes de guidage, dans sa tubulure d'échappement (10) centrale.
  2. Aubes de guidage selon la revendication 1, caractérisées en ce que, sur l'ouverture centrale (53) agit au moins un organe d'entraînement (46) monté sur la douille (45), susceptible d'être introduite dans la tubulure d'échappement (10) centrale du carter de turbine (2).
  3. Aubes de guidage selon la revendication 2, caractérisées en ce que le au moins un organe d'entraînement (46) est formé par une bride, s'étendant radialement et saisissant le disque (29) par l'arrière.
  4. Aubes de guidage selon l'une des revendications précédentes, caractérisées en ce que le disque (29) présente, sur l'ouverture centrale (53), au moins un évidement (47), dans lequel s'engage le au moins un organe d'entraînement (46).
  5. Aubes de guidage selon la revendication 4, caractérisées en ce que le au moins un organe d'entraînement (46) s'achève, en affleurement avec la surface du disque (29).
  6. Aubes de guidage selon la revendication 4 ou 5 caractérisées en ce que l'évidement (47) s'étend en forme d'anneau autour de l'ouverture centrale (53) et l'organe d'entraînement (46) est réalisé de préférence sous la forme de bride en saillie radialement.
  7. Aubes de guidage selon l'une des revendications précédentes, caractérisées en ce que, pour la fixation de la douille (29) sur la tubulure d'échappement (10) du carter de turbine (2), est prévu au moins un dispositif de fixation, par exemple un filetage (50), sur la face extérieure de la douille (29).
  8. Turbocompresseur de suralimentation, avec des aubes de guidage selon l'une des revendications précédentes, ainsi qu'avec au moins un carter de turbine (2) et un carter de palier (4) susceptible d'être fixé de façon désolidarisable sur celui-ci, caractérisé en ce que, sur une paroi (2b) tournée vers le carter de palier (4), entourant l'ouverture de la tubulure d'échappement (10), du carter de turbine (2) est prévue au moins une liaison par emboîtement (48', 49), pour la fixation des aubes de guidage en direction périphérique, alors que, par contre, la fixation axiale se fait au moyen d'un dispositif (50 à 52), assurant la fixation de la fouille (29) dans la tubulure d'échappement (10).
  9. Turbocompresseur de suralimentation selon la revendication 8, caractérisé en ce que le disque (29) présente au moins un trou (48') pour le passage d'au moins une cheville, d'une tige d'enfichage (49) ou analogue, pour la fixation des aubes de guidage en direction périphérique.
  10. Turbocompresseur de suralimentation selon la revendication 8 ou 9, caractérisé en ce que le dispositif (32', 50 à 52), maintenant la douille (29) fixée axialement, comprend, sur la tubulure d'échappement (10), au moins une saillie (52) agissant sur la douille (29), en particulier sur un évidement (51) de celle-ci.
EP02020412A 2002-09-10 2002-09-10 Aubes de guidage variables et turbosoufflante avec ces aubes Expired - Lifetime EP1398463B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE50207509T DE50207509D1 (de) 2002-09-10 2002-09-10 Leitgitter variabler Geometrie und Turbolader mit einem solchen Leitgitter
EP02020412A EP1398463B1 (fr) 2002-09-10 2002-09-10 Aubes de guidage variables et turbosoufflante avec ces aubes
JP2003312620A JP4755393B2 (ja) 2002-09-10 2003-09-04 可変の幾何学的形態の案内ベーン及びターボ過給機
US10/659,786 US6916153B2 (en) 2002-09-10 2003-09-10 Guiding grid of variable geometry and turbocharger

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02020412A EP1398463B1 (fr) 2002-09-10 2002-09-10 Aubes de guidage variables et turbosoufflante avec ces aubes

Publications (2)

Publication Number Publication Date
EP1398463A1 EP1398463A1 (fr) 2004-03-17
EP1398463B1 true EP1398463B1 (fr) 2006-07-12

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EP02020412A Expired - Lifetime EP1398463B1 (fr) 2002-09-10 2002-09-10 Aubes de guidage variables et turbosoufflante avec ces aubes

Country Status (4)

Country Link
US (1) US6916153B2 (fr)
EP (1) EP1398463B1 (fr)
JP (1) JP4755393B2 (fr)
DE (1) DE50207509D1 (fr)

Cited By (3)

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Publication number Priority date Publication date Assignee Title
DE102007010840A1 (de) * 2007-03-06 2008-09-11 Volkswagen Ag Abgasturbolader für eine Brennkraftmaschine
DE102008000849A1 (de) 2008-03-27 2009-10-01 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader für ein Kraftfahrzeug
DE102009007663A1 (de) 2009-02-05 2010-08-12 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung

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DE50304673D1 (de) * 2003-10-27 2006-09-28 Borgwarner Inc Strömungsmaschine und Verfahren zum Herstellen eines Leitgitters
EP1574673B1 (fr) * 2004-03-10 2007-04-18 BorgWarner Inc. Aubes de guidage variables et turbosoufflante avec ces aubes
US6925806B1 (en) * 2004-04-21 2005-08-09 Honeywell International, Inc. Variable geometry assembly for turbochargers
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DE102009008531A1 (de) * 2009-02-11 2010-08-12 Bosch Mahle Turbo Systems Gmbh & Co. Kg Verstellring für eine Ladeeinrichtung, insbesondere für einen Abgasturbolader eines Kraftfahrzeugs
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US8695337B2 (en) * 2010-03-31 2014-04-15 Cummins Turbo Technologies Limited Gas sealing arrangement for a variable geometry turbocharger
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JP5949164B2 (ja) * 2012-05-29 2016-07-06 株式会社Ihi 可変ノズルユニット及び可変容量型過給機
US9896957B2 (en) * 2012-11-23 2018-02-20 Borgwarner Inc. Exhaust-gas turbocharger
JP5836317B2 (ja) * 2013-05-16 2015-12-24 株式会社豊田自動織機 可変ノズルターボチャージャ
US9777621B2 (en) 2014-09-26 2017-10-03 Hyundai Motor Company Sealing-coupled apparatus of turbocharger
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CN108026782B (zh) * 2015-09-16 2020-11-03 博格华纳公司 用于涡轮增压器的脉冲分离的可变几何形状的涡轮叶片的筒
CN109891056B (zh) * 2016-11-02 2022-06-24 博格华纳公司 具有多部件涡轮壳体的涡轮
CN107084040A (zh) * 2017-06-07 2017-08-22 河北师范大学 一种非均匀导流叶片开度的可调向心涡轮增压器调节机构
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CN213899062U (zh) * 2017-12-18 2021-08-06 博格华纳公司 用于排气涡轮增压器的涡轮机装置及排气涡轮增压器
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US6916153B2 (en) 2005-07-12
JP4755393B2 (ja) 2011-08-24
EP1398463A1 (fr) 2004-03-17
JP2004132367A (ja) 2004-04-30
DE50207509D1 (de) 2006-08-24

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