EP1564380A1 - Unité de turbine comprenant un système d'aubes de guidage variables et un anneau de commande - Google Patents

Unité de turbine comprenant un système d'aubes de guidage variables et un anneau de commande Download PDF

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Publication number
EP1564380A1
EP1564380A1 EP04003513A EP04003513A EP1564380A1 EP 1564380 A1 EP1564380 A1 EP 1564380A1 EP 04003513 A EP04003513 A EP 04003513A EP 04003513 A EP04003513 A EP 04003513A EP 1564380 A1 EP1564380 A1 EP 1564380A1
Authority
EP
European Patent Office
Prior art keywords
adjusting
projection
ring
adjusting ring
stop
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.)
Withdrawn
Application number
EP04003513A
Other languages
German (de)
English (en)
Inventor
Dietmar Metz
Ralf Böning
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
Application filed by BorgWarner Inc filed Critical BorgWarner Inc
Priority to EP04003513A priority Critical patent/EP1564380A1/fr
Publication of EP1564380A1 publication Critical patent/EP1564380A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation
    • 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
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/72—Adjusting of angle of incidence or attack of rotating blades by turning around an axis 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
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources

Definitions

  • the present invention relates to a turbine unit, in particular for a Turbocharger having a rotor housing with at least one supply channel for a fluid, Furthermore, a turbine rotor, which is mounted in a turbine chamber of the rotor housing and the periphery of which is the fluid via a guide vane of variable turbine geometry is supplied.
  • the baffle has a vane ring with a variety of this blade bearing ring in the form of a ring mounted blades, each from a substantially tangential position with respect to the rim in an approximately radial Position are adjustable, of which at least one position by at least one with a Counter stop cooperative stop are determined, as well as at least one Adjustment element for adjusting the position of the blades.
  • An actuator is for generating to be transferred to the guide vane with variable turbine geometry Control movements provided via an adjusting ring which is coaxial with the blade bearing ring and is arranged adjacent thereto, and with the at least one adjusting element movably connected.
  • turbines can for example for secondary air pumps, but also for operation with liquid drive medium be used.
  • Turbine units of this type have become known from several documents. So will US-A-6,397,597 and 6,546,728 each describe a similar construction, which has arranged on the housing, located outside of the guide grid attacks. However, this arrangement makes the construction cumbersome difficult to assemble and not inexpensive.
  • DE-A-197 31 715 shows a space-saving construction in which the adjusting ring has a circumferential slot, in which a housing-fixed pin engages as a stop.
  • the slot weakens the already relatively narrow adjusting ring, where then of course only for a relatively thin pin space remains. But there, especially When braking trucks, very high forces acting on the baffle, is the pin constantly in danger of being sheared off.
  • the invention is therefore based on the object, a space-saving and at the same time robust To provide stop arrangement for a turbine unit of the type mentioned, and this is achieved in a surprisingly simple manner in that the attack by a formed on the adjusting ring projection is formed.
  • the projection now creates, instead of a weakening of the adjusting, even one Reinforcement, Since the stop is formed directly on the adjusting ring, he can with be made in one piece, as corresponds to a preferred embodiment, and therefore requires no assembly.
  • a particularly compact design results when the projection of the adjusting ring extends in the axial direction.
  • the compact design also serves, if the projection in at least one of Laying layers on a guide grid attached to the counter-stop, so that no separate Stop must be provided outside the Leitgitters.
  • the projection in at least one of the layers bears against the axis region of the respective adjacent blade, because with it two effects are achieved at the same time: on the one hand it does not need any Separate stop, which would have to be mounted, because the (geometric) axes for the rotation of the blades, including the blades themselves, have to be in a baffle anyway be provided; this results in at most one dimensioning question. On the other hand, the stop then acts on the counter-acting blades no unwanted moment, if he just in the axis range of these blades for Plant comes.
  • the projection in particular between the axis regions engages two adjacent blades and with a free ends of the respective Adjusting element forming levers connected to the leading ring of the adjusting ring is.
  • This wreath will then be relatively strong, the projection can easily with it rigidly connected, in particular integrally made of one piece with the wreath be enabled, and the engagement of the projection between two adjacent blades it (with appropriate distance dimensioning), to interact with both blades, that the projection in the maximum closed position of the blades on an axis region of a blade rests in the maximum open position of the blades on the other hand.
  • the invention also relates to a corresponding guide grid with the features of claim 5 and to an adjusting ring for such a guide grid with the Features of claim 8, which of course also independent articles of commerce can represent.
  • a turbocharger 1 in a conventional manner a turbine housing part 2 and an associated compressor housing part 3 along an axis of rotation R are arranged.
  • the turbine housing part 2 is partially shown in section, so that a blade bearing ring 6 forming a radially outer guide grid, distributed over the circumference Guide vanes 7 about their the blade bearing ring 6 passing through pivot axes.
  • an actuating device 11 To control the movement or the position of the guide vanes 7 is an actuating device 11 provided. This can be of any nature in itself, but it is preferable if, in a conventional manner, it has a control housing 12 that controls the movement a ram member 14 attached to it controls its movement over an adjusting with an axis 16 each of an adjusting lever 17 on a rear the vane ring 6 (left behind behind in Fig. 1) located adjusting ring 5 in a light Implement the same rotational movement. The details of this linkage will be explained later.
  • the guide vanes 7 are positioned above the shafts 8 their rotational position relative to the turbine rotor 4 adjusted so that it is approximately tangential extending an extreme position (maximum closure) in an approximately radially extending other extreme position (maximum opening) are adjustable.
  • This will do so via the feed channel supplied exhaust gas of an internal combustion engine more or less the turbine rotor 4 supplied before it at the extending along the rotation axis R Axialstutzen 10 comes out again. It remains between the blade bearing ring 6 and a annular part 15 of the turbine housing part 2 a relatively narrow blade space thirteenth to allow the wreath of the blades 7 a free mobility.
  • Fig. 2 shows the guide grid according to the invention with the adjusting ring 5 and the blade bearing ring 6 in a view from the side of the compressor 21 (FIG. 1). You can see also the blade bearing shafts 8, which are mounted on the blade bearing ring 6 in the form of a ring and at one end (i.e., at the side facing the viewer of FIG. wear the lever 17 and are firmly connected to these, at the other end (dashed drawn) the guide vanes. 7
  • the adjusting ring 5 runs with him stored Rollers 18 on a tread 19 forming shoulder of the adjusting ring, wherein the Rolling by a mitbewegten (not shown) cage ring at an angular distance held each other. 2 shows the state with fully open blades 7, which assume an approximately radial position with respect to the axis R in this position.
  • the adjusting lever 17 are with their free, slightly rounded ends in recesses in an axially protruding from the adjusting ring 5 rim 20, as shown particularly in FIG. 4th (In minimally open position of the vanes 7) is visible. Further, there is a projection 22 is provided, which serves as a stop for limiting the adjustment of the blades. 7 serves. This projection 22 preferably extends from the adjusting ring 5 in axial Direction, and in particular is formed integrally with the adjusting ring 5, so that for the latter gives a stiffening effect.
  • the stop in order to perform a movement limitation in Contact the respective end position with a corresponding counterstop. this could be any axial counter-projection on the blade bearing ring 6. It is preferred however, if the dimensioning is such that the projection 22 at the axis region, d.i. here at the respective shaft 8 comprehensive fastening ring 17 'of the adjusting lever contribute, the ring 17 ', if necessary, flattened at the contact point or be thickened.
  • the axial arrangement of the projection 22 is indeed preferred, if necessary but the projection also provided on the inside of the adjusting ring 5 and with at least one projecting on the outside of the blade bearing ring 6 Counter-projection can work together, especially - as can be seen - between the two Rings 5, 6 a certain gap 24 may be provided. But it is also apparent that In contrast, the preferred embodiment shown will be more robust. It is also clear that if necessary, with a single counter-stop (the ring 17 ') manages and the projection 22 does not necessarily have to lie centrally between two blades, but if desired, only in the one end position, e.g. the illustrated maximum open Position of the vanes 7, one of the rings 17 'applies, whereas he in the other End position (maximum closed blades 7) has no counter-attack, because then the adjoining blades 7 themselves act as a stop.
  • FIG. 3 shows that the blades 7 have an approximately tangential position with respect to the rings 5, 6 occupy while essentially close the guide grid. The use of a End stop for this minimally open position is therefore cheaper than the juxtaposed Leaves 7 act as an end stop, because then through the leverage of a large moment load are exposed.
  • the stopper 22 as shown particularly in FIG. 4 - a left and a right stop surface 22 'and 22 ", each of which is adjacent to one of the adjacent mounting rings 17 'create.
  • a screw e.g. insert a worm screw and use it as an adjustable stopper.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
EP04003513A 2004-02-17 2004-02-17 Unité de turbine comprenant un système d'aubes de guidage variables et un anneau de commande Withdrawn EP1564380A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04003513A EP1564380A1 (fr) 2004-02-17 2004-02-17 Unité de turbine comprenant un système d'aubes de guidage variables et un anneau de commande

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04003513A EP1564380A1 (fr) 2004-02-17 2004-02-17 Unité de turbine comprenant un système d'aubes de guidage variables et un anneau de commande

Publications (1)

Publication Number Publication Date
EP1564380A1 true EP1564380A1 (fr) 2005-08-17

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EP04003513A Withdrawn EP1564380A1 (fr) 2004-02-17 2004-02-17 Unité de turbine comprenant un système d'aubes de guidage variables et un anneau de commande

Country Status (1)

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EP (1) EP1564380A1 (fr)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007112910A1 (fr) * 2006-03-30 2007-10-11 Borgwarner Inc. turbocompresseur
WO2007134787A1 (fr) * 2006-05-19 2007-11-29 Borgwarner Inc. Turbocompresseur
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
DE112010004596T5 (de) 2009-11-27 2013-01-24 Borgwarner Inc. Turbolade
CN102906392A (zh) * 2010-05-19 2013-01-30 博格华纳公司 涡轮增压器
DE112011103045T5 (de) 2010-09-27 2013-07-04 Borgwarner Inc. Verfahren zur Herstellung eines Turboladers
US8545173B2 (en) 2008-02-12 2013-10-01 Honeywell International, Inc. Process for calibrating a variable-nozzle assembly of a turbocharger and a variable-nozzle assembly facilitating such process
CN104018889A (zh) * 2013-03-01 2014-09-03 株式会社Ihi 可变喷嘴单元以及可变容量型增压器
US20150292350A1 (en) * 2012-11-23 2015-10-15 Borgwarner Inc. Exhaust-gas turbocharger
US20150361818A1 (en) * 2014-06-16 2015-12-17 Rolls-Royce Plc Assembly
WO2015195766A1 (fr) 2014-06-20 2015-12-23 Borgwarner Inc. Turbocompresseur à aubes réglables
US20160010542A1 (en) * 2013-03-11 2016-01-14 Borgwarner Inc. Exhaust-gas turbocharger
CN105484809A (zh) * 2011-08-08 2016-04-13 博格华纳公司 涡轮增压器
DE102015217438A1 (de) 2015-09-11 2017-03-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg Verfahren zum Herstellen einer variablen Turbinengeometrie eines Abgasturboladers
WO2018029985A1 (fr) * 2016-08-08 2018-02-15 株式会社Ihi Compresseur de suralimentation à capacité variable
DE102008049005B4 (de) 2008-09-25 2018-06-14 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
EP3640451A1 (fr) * 2018-10-19 2020-04-22 Borgwarner Inc. Turbocompresseur à géométrie de turbine variable
US10927702B1 (en) 2019-03-30 2021-02-23 Savant Holdings LLC Turbocharger or turbocharger component
US11585266B2 (en) * 2018-10-09 2023-02-21 Ihi Corporation Variable geometry mechanism and turbocharger

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2860827A (en) * 1953-06-08 1958-11-18 Garrett Corp Turbosupercharger
DE2455361A1 (de) * 1973-12-11 1975-06-12 Plessey Handel Investment Ag Turbine bzw. kompressor insbesondere fuer turbolader
US4804316A (en) * 1985-12-11 1989-02-14 Allied-Signal Inc. Suspension for the pivoting vane actuation mechanism of a variable nozzle turbocharger
DE3941715A1 (de) * 1989-12-18 1991-06-20 Porsche Ag Abgasturbolader fuer eine brennkraftmaschine
DE19731715A1 (de) * 1996-07-24 1998-01-29 Toyota Motor Co Ltd Turbolader mit variabler Düse
EP1304462A2 (fr) * 2001-10-22 2003-04-23 Toyota Jidosha Kabushiki Kaisha Dispositif de commande d'un actionneur

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2860827A (en) * 1953-06-08 1958-11-18 Garrett Corp Turbosupercharger
DE2455361A1 (de) * 1973-12-11 1975-06-12 Plessey Handel Investment Ag Turbine bzw. kompressor insbesondere fuer turbolader
US4804316A (en) * 1985-12-11 1989-02-14 Allied-Signal Inc. Suspension for the pivoting vane actuation mechanism of a variable nozzle turbocharger
DE3941715A1 (de) * 1989-12-18 1991-06-20 Porsche Ag Abgasturbolader fuer eine brennkraftmaschine
DE19731715A1 (de) * 1996-07-24 1998-01-29 Toyota Motor Co Ltd Turbolader mit variabler Düse
EP1304462A2 (fr) * 2001-10-22 2003-04-23 Toyota Jidosha Kabushiki Kaisha Dispositif de commande d'un actionneur

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007112910A1 (fr) * 2006-03-30 2007-10-11 Borgwarner Inc. turbocompresseur
WO2007134787A1 (fr) * 2006-05-19 2007-11-29 Borgwarner Inc. Turbocompresseur
EP3073064A1 (fr) 2006-05-19 2016-09-28 BorgWarner, Inc. Turbocompresseur
US8328520B2 (en) 2006-05-19 2012-12-11 Borgwarner Inc. Turbocharger with separately formed vane lever stops
US8545173B2 (en) 2008-02-12 2013-10-01 Honeywell International, Inc. Process for calibrating a variable-nozzle assembly of a turbocharger and a variable-nozzle assembly facilitating such process
DE102008049005B4 (de) 2008-09-25 2018-06-14 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
EP2226474A3 (fr) * 2009-02-11 2012-05-16 Bosch Mahle Turbo Systems GmbH & Co. KG Bague de réglage pour un dispositif de charge, notamment pour une turbosoufflante de gaz d'échappement d'un véhicule automobile
US8747058B2 (en) 2009-02-11 2014-06-10 Bosch Mahle Turbo Systems GmbH Co. KG Adjusting ring for a charging device, more preferably for an exhaust gas turbocharger of a motor vehicle
EP2226474A2 (fr) 2009-02-11 2010-09-08 Bosch Mahle Turbo Systems GmbH & Co. KG Bague de réglage pour un dispositif de charge, notamment pour une turbosoufflante de gaz d'échappement d'un véhicule automobile
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
JP2013512386A (ja) * 2009-11-27 2013-04-11 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
CN102906392A (zh) * 2010-05-19 2013-01-30 博格华纳公司 涡轮增压器
DE112011101698T5 (de) 2010-05-19 2013-04-11 Borgwarner Inc. Turbolader
JP2013526679A (ja) * 2010-05-19 2013-06-24 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
CN102906392B (zh) * 2010-05-19 2015-02-11 博格华纳公司 涡轮增压器以及用于其的引导栅和该引导栅的停止件
DE112011103045T5 (de) 2010-09-27 2013-07-04 Borgwarner Inc. Verfahren zur Herstellung eines Turboladers
CN105484809A (zh) * 2011-08-08 2016-04-13 博格华纳公司 涡轮增压器
US20150292350A1 (en) * 2012-11-23 2015-10-15 Borgwarner Inc. Exhaust-gas turbocharger
US9896957B2 (en) * 2012-11-23 2018-02-20 Borgwarner Inc. Exhaust-gas turbocharger
CN104018889B (zh) * 2013-03-01 2017-04-12 株式会社Ihi 可变喷嘴单元以及可变容量型增压器
CN104018889A (zh) * 2013-03-01 2014-09-03 株式会社Ihi 可变喷嘴单元以及可变容量型增压器
US9945245B2 (en) 2013-03-01 2018-04-17 Ihi Corporation Variable nozzle unit and variable geometry system turbocharger
US9988975B2 (en) * 2013-03-11 2018-06-05 Borgwarner Inc. Exhaust-gas turbocharger
US20160010542A1 (en) * 2013-03-11 2016-01-14 Borgwarner Inc. Exhaust-gas turbocharger
US20150361818A1 (en) * 2014-06-16 2015-12-17 Rolls-Royce Plc Assembly
US9970313B2 (en) * 2014-06-16 2018-05-15 Rolls-Royce Plc Unison ring assembly
WO2015195766A1 (fr) 2014-06-20 2015-12-23 Borgwarner Inc. Turbocompresseur à aubes réglables
DE102015217438A1 (de) 2015-09-11 2017-03-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg Verfahren zum Herstellen einer variablen Turbinengeometrie eines Abgasturboladers
WO2018029985A1 (fr) * 2016-08-08 2018-02-15 株式会社Ihi Compresseur de suralimentation à capacité variable
US11585266B2 (en) * 2018-10-09 2023-02-21 Ihi Corporation Variable geometry mechanism and turbocharger
EP3640451A1 (fr) * 2018-10-19 2020-04-22 Borgwarner Inc. Turbocompresseur à géométrie de turbine variable
US11131238B2 (en) 2018-10-19 2021-09-28 Borgwarner Inc. Turbocharger with variable turbine geometry
US10927702B1 (en) 2019-03-30 2021-02-23 Savant Holdings LLC Turbocharger or turbocharger component

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