WO2011069571A1 - Turbine pour un dispositif de suralimentation et procédé pour le montage d'une telle turbine - Google Patents

Turbine pour un dispositif de suralimentation et procédé pour le montage d'une telle turbine Download PDF

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Publication number
WO2011069571A1
WO2011069571A1 PCT/EP2010/005685 EP2010005685W WO2011069571A1 WO 2011069571 A1 WO2011069571 A1 WO 2011069571A1 EP 2010005685 W EP2010005685 W EP 2010005685W WO 2011069571 A1 WO2011069571 A1 WO 2011069571A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
housing
guide grid
contour sleeve
exhaust gas
Prior art date
Application number
PCT/EP2010/005685
Other languages
German (de)
English (en)
Inventor
Jürgen Bassler
Theocharis Vryzonis
Original Assignee
Daimler Ag
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 Daimler Ag filed Critical Daimler Ag
Publication of WO2011069571A1 publication Critical patent/WO2011069571A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • 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
    • 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
    • F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
    • 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
    • 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 turbine for a supercharger, in particular for an exhaust gas turbocharger, the type specified in the preamble of claim 1 and a method for assembling such a turbine specified in the preamble of claim 9 Art.
  • DE 10 2005 027 080 A1 discloses an exhaust gas turbine in an exhaust gas turbocharger with a turbine wheel mounted in a housing carrier, to which exhaust gas can be fed via an inlet flow, which can be discharged from the exhaust gas turbine via an outlet channel, with a turbine inlet cross section which, in the transition from the inlet flow to the
  • Turbine is formed between two lateral boundary walls and in which a guide grid and a cooperating with the guide grid, is arranged in the axial direction adjustable axial slide, wherein one of the boundary walls of the
  • Turbine inlet cross-section slidably executed and formed by the axial slide.
  • the guide grid is fixedly mounted in the turbine inlet cross-section housing, wherein the axial slide is arranged on the outlet channel facing side, and wherein the outlet channel facing away from the housing-fixed boundary wall of the
  • Turbine inlet cross section axially flush with the turbine blades of the
  • the known exhaust gas turbine has further potential for improvement to simplify a mounting of the exhaust gas turbine.
  • Charging device in particular for an exhaust gas turbocharger of the type mentioned above and to provide a method for assembling such a turbine, which allow low cost of the turbine.
  • This object is achieved by a turbine for a charging device, in particular for an exhaust gas turbocharger, with the features of patent claim 1 and by a method for assembling such a turbine with the features of patent claim 9.
  • a turbine according to the invention for a charging device in particular a
  • Exhaust gas turbocharger with a recorded by a turbine housing and arranged in a turbine inlet area guide grid and at least partially arranged in a turbine outlet area contour sleeve elements for influencing flow parameters is provided by the fact that the contour sleeve element and / or the guide grid are fixed via a bayonet lock on the turbine housing.
  • the contour sleeve element is integrally formed with the guide grid, which are then fixed by a bayonet fitting associated with this in the turbine housing.
  • the one-piece design keeps the number of parts of the turbine according to the invention low, which is conducive to further cost reduction.
  • Turbine housing can be inserted or pushed out of the housing via the turbine outlet, so so that the contour sleeve member and the guide grid can be mounted in a single step, which keeps the time and thus the cost of installation in a small frame. This is especially true when the guide grid and the contour sleeve member are integrally formed with each other. Likewise, the handling during assembly is simplified because then only a one-piece component must be spent and mounted. Additional assembly steps or arrangements for the handling of multiple components are not required. It should be noted at this point that the movement of the component assembly into the
  • Turbine housing into or out of the turbine housing out in the axial direction of the turbine.
  • This assembly of the component assembly on the turbine outlet has the advantage that the turbine outlet provides a sufficiently large accessibility in the turbine housing, so as to be able to mount the component assembly quickly and easily.
  • the assembly of the component assembly or its definition in the turbine housing on said bayonet closure affects the installation with respect to time and cost continues to be very positive because, for example, a subsequent attachment process, for example by a welding ßrea and additional fasteners, such as a filler metal, not required.
  • the bayonet closure of the turbine according to the invention has the shape that the component composite is introduced from the turbine outlet into the turbine housing and is then rotated in an axial end position, so overlap tabs of the bayonet closure, whereby the composite component is fixed in the axial direction of the turbine. A radial fixation of the component composite takes place via corresponding systems and via corresponding active surfaces in the radial direction.
  • the guide grid and the contour sleeve element is formed integrally, said analogously to the contour sleeve member and / or the guide grid is transferable.
  • the component assembly is a cassette solution of the said components, which is advantageously particularly quick and easy to assemble and in the case of one-piece design keeps the number of parts of the turbine and thus their costs low.
  • the bayonet closure is represented, for example, by a corresponding casting design and machining of the corresponding components or of the component composite, in particular in the case of the one-piece design of the guide grid and of the contour sleeve element.
  • the component composite comprises a slide element for influencing a flow cross-section of the guide grid, whereby on the one hand the turbine to a wide range of operating points of its associated drive unit, such as an internal combustion engine, adaptable, which allows extremely efficient operation of the turbine and thus the drive unit.
  • the Slider element can be mounted together with the guide grid and the contour sleeve element in a single step, which avoids further steps for fixing the slider element and other fastening means. This too is low costs for assembly and thus beneficial for the turbine as a whole.
  • the said slide element may be, for example, an axial slide which is displaceably mounted in the axial direction of the turbine and by means of which the flow cross section in a turbine wheel inlet region, in particular the flow cross section of the guide grid, can be variably adjusted.
  • the component composite with the slider element while the slider element is slidably held or mounted for example, on the contour sleeve member.
  • the invention also includes a charging device, in particular an exhaust gas turbocharger, with a bearing housing and with a turbine according to the invention, wherein the
  • Bayonet lock is provided on sides of the bearing housing.
  • the arrangement of the bayonet closure on the side of the bearing housing has the advantage that thereby minimizing the influence of distortion of the turbine housing by different thermal expansions on a clamping tendency of the slider element, which is a movable component, is possible. This reduces the failure probability of the turbine, which also minimizes the likelihood of costly and time-consuming maintenance or repair work.
  • a heat shield is arranged in the axial direction of the turbine between the bearing housing and the guide grid or between the bearing housing and the guide sleeve integrally formed with the contour sleeve member to heat transfer from the acted upon by a hot medium, such as exhaust gas turbine to reduce the bearing housing at least, which keeps different thermal expansions low.
  • the heat shield is thus also clamped in the turbine housing, thereby avoiding further fasteners that would increase the cost of the turbine.
  • the invention also relates to a method for assembling a turbine for a
  • Charging device in particular an exhaust gas turbocharger, wherein in a
  • Turbine housing a guide grid in a turbine inlet area and a
  • Turbines according to the invention are to be regarded as advantageous embodiments of the method and vice versa.
  • the inventive method allows a particularly simple and thus time and cost assembly of the turbine and thus the entire charging device due to the particularly simple and quick installation and optionally disassembly of the contour sleeve member and / or the guide grid or the composite component described.
  • FIG. 1 shows a detail of a perspective view of an exhaust gas turbocharger with an embodiment of the turbine according to the invention.
  • FIG. 2 shows a detail of a longitudinal sectional view of the exhaust gas turbocharger according to FIG. 1.
  • Fig. 1 shows an exhaust gas turbocharger 10 with a bearing housing 12 in which a running tool is mounted.
  • This power tool includes one shaft and two with the shaft rotatably connected impellers, wherein an impeller as the compressor wheel of a compressor of the exhaust gas turbocharger 10 and an impeller as the turbine wheel of a turbine 14 of the
  • Exhaust gas turbocharger 10 is formed.
  • the turbine wheel is received by a turbine housing 16 of the turbine 14. Also received by the turbine housing 16 is a in one
  • FIGS. 1 and 2 are not shown and formed integrally with the guide grille 18, the contoured sleeve element is not shown in FIGS. 1 and 2 and formed in a turbine outlet region.
  • Contour sleeve element and a trained as an axial slide and on the
  • Contoured sleeve element slidably held slide element is now inserted from a turbine outlet side according to a direction arrow 20 ago in the turbine housing 16 inserted or opposite to this pushed out.
  • a bayonet closure 24 is provided, which thus defines the contour sleeve element, the guide grid 8 and the axial slide in the axial direction according to a directional arrow 22 of the turbine 14 and the exhaust gas turbocharger 10 on the turbine housing 16.
  • Bearing housing 12 is fixed or clamped in the axial direction.
  • the heat shield 26 prevents an excessively high heat transfer from the acted upon by a hot exhaust turbine 14 on the bearing housing 12, which different thermal expansions and thus leakage and negative influences on the mentioned storage of the running gear at least reduced.
  • Tolerance chain allows said turbine wheel.
  • Bayonet catch 24 so this low tolerance chain is a simple and thus time and cost assembly of the composite component beneficial, which is associated with low costs for the exhaust gas turbocharger 10 overall.
  • the turbine housing 16 and the bearing housing 12 are connected by means of a V-band clamp 28, which ensures a firm cohesion and thus secure clamping of the composite component and the heat shield 26.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)

Abstract

L'invention concerne une turbine (14) pour un dispositif de suralimentation (10), en particulier un turbocompresseur à gaz d'échappement (10), doté d'une grille directrice (18) réceptionnée par une enveloppe de turbine (16) et disposée dans une zone d'entrée de turbine et d'un élément de manchon de contour disposé au moins par endroits dans une zone de sortie de turbine pour influencer des paramètres d'écoulement, l'élément de manchon de contour et/ou la grille directrice (18) étant fixés au moyen d'une fermeture à baïonnette (24) sur l'enveloppe de turbine (26). L'invention concerne également un procédé pour le montage d'une turbine (14) pour un dispositif de suralimentation (10), en particulier un turbocompresseur à gaz d'échappement (10), dans lequel une grille directrice (18) et un élément de manchon de contour sont disposés dans une enveloppe de turbine (16) respectivement dans une zone d'entrée de turbine et dans une zone de sortie de turbine pour influencer des paramètres d'écoulement, l'élément de manchon de contour et/ou la grille directrice (18) étant reliés au moyen d'une fermeture à baïonnette (24) à l'enveloppe de turbine (16).
PCT/EP2010/005685 2009-12-10 2010-09-16 Turbine pour un dispositif de suralimentation et procédé pour le montage d'une telle turbine WO2011069571A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009057742.4 2009-12-10
DE200910057742 DE102009057742A1 (de) 2009-12-10 2009-12-10 Turbine für eine Aufladeeinrichtung sowie Verfahren zur Montage einer solchen Turbine

Publications (1)

Publication Number Publication Date
WO2011069571A1 true WO2011069571A1 (fr) 2011-06-16

Family

ID=43242450

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2010/005685 WO2011069571A1 (fr) 2009-12-10 2010-09-16 Turbine pour un dispositif de suralimentation et procédé pour le montage d'une telle turbine

Country Status (2)

Country Link
DE (1) DE102009057742A1 (fr)
WO (1) WO2011069571A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE202015008551U1 (de) * 2015-12-14 2017-03-16 GM Global Technology Operations LLC (n. d. Gesetzen des Staates Delaware) Flanschverbindung eines Turboladers und einer Nachbehandlungsvorrichtung

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB589689A (en) * 1944-03-31 1947-06-26 British Thomson Houston Co Ltd Improvements in and relating to centrifugal compressors
DE4438611A1 (de) * 1994-10-28 1996-05-02 Bmw Rolls Royce Gmbh Radialverdichter oder Radialturbine mit einem Leitschaufeln aufweisenden Diffusor oder Turbinenleitkranz
DE102004031986A1 (de) * 2004-07-01 2006-01-19 Volkswagen Ag Abgasturbolader für eine Brennkraftmaschine
DE102005027080A1 (de) 2005-06-11 2006-12-14 Daimlerchrysler Ag Abgasturbine in einem Abgasturbolader
EP1734231A1 (fr) * 2005-06-16 2006-12-20 BorgWarner Inc. Turbocompresseur et anneau statorique pour celui-ci
DE102007040679A1 (de) * 2007-08-29 2009-03-05 Bayerische Motoren Werke Aktiengesellschaft Leitapparat für eine Turbine eines Abgasturboladers

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB589689A (en) * 1944-03-31 1947-06-26 British Thomson Houston Co Ltd Improvements in and relating to centrifugal compressors
DE4438611A1 (de) * 1994-10-28 1996-05-02 Bmw Rolls Royce Gmbh Radialverdichter oder Radialturbine mit einem Leitschaufeln aufweisenden Diffusor oder Turbinenleitkranz
DE102004031986A1 (de) * 2004-07-01 2006-01-19 Volkswagen Ag Abgasturbolader für eine Brennkraftmaschine
DE102005027080A1 (de) 2005-06-11 2006-12-14 Daimlerchrysler Ag Abgasturbine in einem Abgasturbolader
EP1734231A1 (fr) * 2005-06-16 2006-12-20 BorgWarner Inc. Turbocompresseur et anneau statorique pour celui-ci
DE102007040679A1 (de) * 2007-08-29 2009-03-05 Bayerische Motoren Werke Aktiengesellschaft Leitapparat für eine Turbine eines Abgasturboladers

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Publication number Publication date
DE102009057742A1 (de) 2011-06-16

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