WO2022228803A1 - Turbocompresseur à gaz d'échappement doté d'un carter intégral et d'une géométrie de turbine variable et carter intégral pour un turbocompresseur à gaz d'échappement - Google Patents

Turbocompresseur à gaz d'échappement doté d'un carter intégral et d'une géométrie de turbine variable et carter intégral pour un turbocompresseur à gaz d'échappement Download PDF

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Publication number
WO2022228803A1
WO2022228803A1 PCT/EP2022/058111 EP2022058111W WO2022228803A1 WO 2022228803 A1 WO2022228803 A1 WO 2022228803A1 EP 2022058111 W EP2022058111 W EP 2022058111W WO 2022228803 A1 WO2022228803 A1 WO 2022228803A1
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WO
WIPO (PCT)
Prior art keywords
exhaust gas
housing
bearing
turbine
integral
Prior art date
Application number
PCT/EP2022/058111
Other languages
German (de)
English (en)
Inventor
Tim Roßbach
Michael STERR
Original Assignee
Vitesco Technologies GmbH
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 Vitesco Technologies GmbH filed Critical Vitesco Technologies GmbH
Publication of WO2022228803A1 publication Critical patent/WO2022228803A1/fr

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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
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • 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
    • F05D2230/52—Building or constructing in particular ways using existing or "off the shelf" parts, e.g. using standardized turbocharger elements
    • 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
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • Exhaust gas turbocharger with an integral housing and variable turbine geometry and integral housing for an exhaust gas turbocharger
  • the invention relates to an exhaust gas turbocharger for an internal combustion engine with an exhaust gas turbine with variable turbine geometry and an integral housing combined from bearing housing and turbine housing, and such an integral housing for such an exhaust gas turbocharger with variable turbine geometry.
  • Exhaust gas turbochargers are increasingly being used to increase the performance of motor vehicle combustion engines. This is happening more and more often with the aim of reducing the size and weight of the combustion engine with the same or even increased performance and at the same time reducing consumption and thus CC emissions, in view of the increasingly strict legal requirements in this regard.
  • the operating principle is to use the energy contained in the exhaust gas flow to increase the pressure in the intake tract of the combustion engine and thus achieve better filling of the combustion chamber with air-oxygen and thus be able to convert more fuel, petrol or diesel, per combustion process. i.e. to increase the power of the combustion engine.
  • a conventional exhaust gas turbocharger has an exhaust gas turbine arranged in the exhaust tract of the internal combustion engine, a radial air compressor arranged in the intake tract and a bearing unit arranged in between.
  • the exhaust gas turbine has a turbine housing and a turbine impeller which is arranged therein and is driven by the exhaust gas mass flow.
  • the radial air compressor has a compressor housing and a compressor impeller which is arranged therein and which generates boost pressure.
  • the turbine impeller and the compressor impeller are arranged in a rotationally fixed manner on the opposite ends of a common shaft, the so-called rotor shaft, and thus form the so-called turbocharger rotor.
  • the rotor shaft extends axially between the turbine impeller and the compressor impeller through the bearing unit arranged between the exhaust gas turbine and the radial air compressor and is rotatably mounted radially and axially in this, with respect to the rotor shaft rotation axis.
  • the turbine impeller driven by the exhaust gas mass flow drives the compressor impeller via the rotor shaft, which increases the pressure in the intake tract of the combustion engine, based on the fresh air mass flow behind the fresh air compressor, and thus causes better filling of the combustion chamber with air-oxygen.
  • a common exhaust gas turbocharger has a multi-part structure.
  • a turbine housing that can be arranged in the exhaust tract of the internal combustion engine, a compressor housing that can be arranged in the intake tract of the internal combustion engine, and a bearing housing between the turbine housing and the compressor housing are arranged next to one another on a common turbocharger axis and are connected to one another in terms of assembly.
  • a further structural unit of the exhaust gas turbocharger is the turbocharger rotor, which has a rotor shaft, a turbine wheel arranged in the turbine housing and a compressor wheel arranged in the compressor housing.
  • the turbine wheel and the compressor wheel are arranged on the opposite ends of the common rotor shaft and are non-rotatably connected thereto.
  • the rotor shaft extends axially along its longitudinal axis, the rotor shaft axis of rotation, in the direction of the turbocharger axis through the bearing housing and is rotatably mounted in it axially and radially about its rotor shaft axis of rotation, with the rotor shaft axis of rotation and the turbocharger axis coinciding.
  • the turbine housing has one or more exhaust gas spiral ducts, also referred to as exhaust gas flows, which are arranged in a ring, encompassing the turbine impeller and the turbocharger axis, tapering in a snail shape towards the turbine impeller and which have a radially inwardly directed annular duct opening, the exhaust gas annular duct.
  • the exhaust gas spiral ducts also have a respective or common exhaust gas feed duct, through which the exhaust gas mass flow flows into the respective exhaust gas flow and from there through the inwardly directed exhaust gas annular duct via the turbine impeller into an exhaust gas discharge duct and is discharged into the exhaust system of the internal combustion engine.
  • the radial inner contour of the turbine housing follows the outer contour of the turbine impeller accommodated therein over a certain area, between the annular exhaust gas channel and the exhaust gas discharge channel. This area of the inner contour of the turbine housing is referred to as the sealing contour and causes the exhaust gas mass flow to flow as completely as possible through the blading of the turbine wheel 21 and not past it.
  • the compressor housing has an air inlet port with an air inlet duct for connection to the fresh air intake system of the internal combustion engine. Above A fresh air mass flow is sucked in through this air intake duct by the compressor impeller from the fresh air intake system.
  • the compressor housing generally has an air spiral duct, a so-called fresh air flow, which encompasses the compressor impeller and the turbocharger axis in a ring shape and widens in a snail shape away from the compressor impeller.
  • This air spiral duct has an annular duct opening, the so-called diffuser, through which the fresh air mass flow flows away from the compressor impeller under increased pressure into the air spiral duct and from there through an outwardly directed fresh air discharge duct into the distributor pipe of the combustion engine.
  • the bearing housing is arranged axially between the turbine housing and the compressor housing.
  • a bearing arrangement for the axial bearing and for the rotary bearing of the rotor shaft is accommodated in the bearing housing.
  • the bearing arrangement generally consists of two radial shaft bearings arranged at an axial distance from one another for rotary bearing and one axial shaft bearing for supporting axial forces acting on the rotor shaft during operation.
  • Oil supply channels are provided in the bearing housing to lubricate and supply oil to the bearing components.
  • a compressor housing connection flange is provided on the side of the bearing housing facing the fresh air compressor, to which the compressor housing is connected to the bearing housing.
  • a turbine housing connection flange is provided, on which the turbine housing is connected to the bearing housing.
  • a so-called heat shield is usually arranged, which shields the housing wall of the bearing housing facing the turbine housing, also known as the bearing housing shield, and the bearing components in the bearing housing against the high exhaust gas temperatures in the exhaust gas turbine.
  • Exhaust gas turbines and radial air compressors are turbomachines and, due to physical laws, have an optimal operating range that depends on the size and design and is characterized by the mass throughput, the pressure ratio and the speed of the respective impeller.
  • an exhaust gas turbine is fitted, for example, with an exhaust gas annular duct forming or in the exhaust annular duct in the transition between the exhaust gas spiral duct and the turbine impeller and is equipped with the "Variable Turbine Geometry" (VTG) exhaust gas guiding device.
  • VVG Very Turbine Geometry
  • variable turbine geometry is set in such a way that the speed of the turbine and compressor impeller and the pressure ratio, especially on the exhaust gas turbine, can be kept within the desired working range of the exhaust gas turbocharger.
  • Such an exhaust gas guide device is generally formed by a bearing ring disk and a cover ring disk, which are arranged concentrically and at an axial distance from one another, forming the annular exhaust gas channel.
  • a plurality of exhaust gas guide vanes are arranged distributed over the circumference, which are mounted in the bearing ring disk so that they can rotate about a respective blade axis of rotation, with the blade axis of rotation being at least predominantly axially aligned in relation to the turbine axis, and the Exhaust guide vanes extend over their blade width in the axial direction between the bearing washer and the cover washer.
  • the exhaust gas guide vanes are mounted such that they can rotate about their respective vane axes of rotation, from a closed position over a radial pivot range to an open position.
  • an actuating mechanism is usually arranged on the outside of the bearing ring disk, which is provided for actuating the exhaust gas guide vanes. With the help of this adjusting mechanism, the rotational position of the exhaust gas guide vanes is changed as required, thus influencing the degree of reaction, the intake capacity and the pressure ratio of the exhaust gas turbine.
  • an exhaust gas guiding device is accommodated in the turbine housing from the bearing housing side of the turbine housing.
  • the object of the present invention is therefore to provide an exhaust gas turbocharger with a variable exhaust gas guide device and a housing concept for such an exhaust gas turbocharger, which at least reduces the disadvantages mentioned above.
  • the proposed objects according to the invention are characterized above all by a reduction in the number of individual complex housing components, simplified assembly of the exhaust gas guide device in the housing, the enabling of simplified, efficient thermal management for the exhaust gas turbine and bearing unit and the associated reduced requirements for the material, a reduced axial installation space requirements of the exhaust gas turbocharger, simplified accessibility of the exhaust gas guide for repair and maintenance work, and, as a result, lower manufacturing costs for the product.
  • the arrangement of the exhaust gas outlet connection on the integral housing which is easy to implement in terms of design and production technology, cover enables easy application adaptation to different exhaust systems.
  • an exhaust gas turbocharger for an internal combustion engine which has an exhaust gas turbine with an exhaust gas guide device, a radial air compressor, and a bearing unit with a rotor shaft mounted in a shaft bearing arrangement.
  • the exhaust gas turbine has a turbine impeller non-rotatably connected to a first shaft end of the rotor shaft, a turbine housing with at least one exhaust gas spiral duct, which surrounds the turbine impeller at least over part of its circumference, and a variable exhaust gas guiding device arranged in a transition region between the exhaust gas spiral duct and the turbine impeller .
  • the radial air compressor has a compressor housing and a compressor impeller which interacts therewith and is non-rotatably connected to a second shaft end of the rotor shaft.
  • the bearing unit has a bearing housing which is arranged between the turbine housing and the compressor housing and in which the shaft bearing arrangement is accommodated, the rotor shaft extending along a rotor shaft axis of rotation in the axial direction through the bearing housing, and in the shaft bearing arrangement around the rotor shaft axis of rotation, together with the turbine wheel and the compressor wheel, is rotatably mounted.
  • the exhaust gas turbocharger according to the invention is characterized in particular by the fact that the bearing housing and the turbine housing are designed together as an integral housing manufactured in one piece and that the exhaust gas guide device is inserted in the axial direction into a receiving opening of the integral housing from an exhaust gas outlet side of the integral housing that faces away from the compressor housing and that an integral housing cover is arranged on the exhaust gas outlet side of the integral housing, which cover at least partially covers the receiving opening and has an exhaust gas outlet connection with an exhaust gas outlet channel.
  • the integral housing has a coolant duct, which connects the exhaust gas spiral duct on a bearing housing side facing the compressor housing Integral housing at least partially surrounds and extends into the bearing housing forming part of the integral housing.
  • the coolant channel also extends at least partially over the outer circumference of the exhaust gas spiral channel.
  • the exhaust gas spiral duct is designed in such a way that on a bearing housing side of the integral housing facing the compressor housing it overhangs at least partially in the axial direction towards the compressor housing over the part of the integral housing forming the bearing housing. This advantageously contributes to shortening the overall axial length of the exhaust gas turbocharger.
  • variable exhaust gas guide device has a bearing ring disk, a cover ring disk, several exhaust gas guide vanes arranged distributed between the bearing ring disk and the cover ring disk over their circumference, and an actuating mechanism.
  • the receiving opening in the part of the integral housing that forms the turbine housing is delimited in the axial direction by a bearing housing plate.
  • the exhaust gas guiding device is inserted into the receiving opening in such a way that the cover ring disk is arranged on the side of the exhaust gas guiding device facing away from the bearing housing plate and the actuating mechanism is arranged in the receiving opening on the side facing away from the bearing housing plate.
  • a stop shoulder can be provided on the bearing housing shield, on which the cover ring disk is positioned centered on the axis of rotation of the rotor shaft.
  • An axial stop for the exhaust-gas guiding device can also be implemented as a result. This ensures precise positioning and centering of the exhaust gas guiding device in relation to the axis of rotation of the rotor shaft in a simple manner.
  • the actuating mechanism arranged on the exhaust gas outlet side of the exhaust gas guiding device is covered by the integral housing cover and the integral housing cover adjoins the integral housing in an exhaust-tight manner.
  • a circumferential sealing ring can be provided in the radial outer area of the integral housing cover for sealing between the turbine housing and the integral housing cover.
  • variable exhaust gas guide device and the integral housing cover are designed as a pre-assembled cartridge assembly. This enables separate or parallel pre-assembly of this cartridge assembly and simplified final assembly in one joining process.
  • Another embodiment of the exhaust gas turbocharger according to the invention is based on the embodiment in which the exhaust gas guide device has a bearing ring disk, a cover ring disk, several exhaust gas guide vanes arranged between the bearing ring disk and the cover ring disk distributed over their circumference, as well as an actuating mechanism and is inserted into the receiving opening in such a way that the cover ring disk is on the the side facing the bearing housing plate and the bearing washer with the actuating mechanism are arranged on the side of the exhaust gas guiding device facing away from the bearing housing plate in the receiving opening.
  • a sealing contour is formed by the bearing ring disk in relation to an outer contour of the turbine impeller.
  • the sealing contour is the transition area between the annular exhaust gas duct and the exhaust gas discharge duct, in which the radial inner contour of the components encompassing the turbine impeller, or the further course of the annular duct front wall on the exhaust gas outlet side, the outer contour of the turbine wheel is adjusted in such a way that the exhaust gas mass flow flows as completely as possible through the blading of the turbine wheel and not past it.
  • the annular exhaust gas channel is formed between the cover ring disk and the bearing ring disk, with the cover ring disk forming the annular channel rear wall on the bearing housing side and the bearing ring disk forming the annular channel front wall on the exhaust gas outlet side.
  • the ring channel front wall on the bearing ring disk is continued here as a sealing contour, with the smallest possible distance, along the outer contour of the turbine impeller.
  • the sealing contour can be produced with high precision and in simple processing steps on the separate bearing ring disk.
  • the integral housing according to the invention for an exhaust gas turbocharger according to the invention in which the bearing housing and the turbine housing are combined with an exhaust gas spiral duct as a component manufactured from one piece, is characterized in that there is a receiving opening for receiving the exhaust gas guide device from one of the Bearing housing facing away from the exhaust gas outlet side of the integral housing ago in the axial direction.
  • An advantageous embodiment of the integral housing according to the invention is characterized in that it has a coolant channel which at least partially encompasses the exhaust gas spiral channel on a bearing housing side of the integral housing and extends into the part of the integral housing that forms the bearing housing.
  • a coolant channel which at least partially encompasses the exhaust gas spiral channel on a bearing housing side of the integral housing and extends into the part of the integral housing that forms the bearing housing.
  • Another embodiment of the integral housing according to the invention for an exhaust gas turbocharger is characterized in that the exhaust gas spiral duct on the bearing housing side, i.e. the side of the exhaust gas spiral duct facing away from the exhaust gas outlet side, at least partially overhangs in the axial direction over the part of the integral housing that forms the bearing housing.
  • the claimed axial installation space of the integral housing is advantageously reduced.
  • Show it: 1 shows a simplified three-dimensional representation of an embodiment of a conventional exhaust-gas turbocharger with variable turbine geometry (VTG), with a housing cut open in a quarter section along the turbocharger axis;
  • VFG variable turbine geometry
  • VVTG variable turbine geometry
  • FIG. 1 shows an embodiment of a conventional exhaust gas turbocharger 1 consisting of an exhaust gas turbine 20, a radial air compressor 30 and the bearing unit 40 arranged axially in between.
  • a conventional exhaust gas turbocharger 1 consisting of an exhaust gas turbine 20, a radial air compressor 30 and the bearing unit 40 arranged axially in between.
  • an upper quarter of the turbine housing 21 of the compressor housing 31 and the bearing housing 41 is continuously cut out along the turbocharger axis 11, which coincides with the turbine axis.
  • the sectional view allows an insight into the structure and arrangement of the essential components of the exhaust gas turbocharger 1.
  • the turbine housing 21 that can be arranged in the exhaust tract of the internal combustion engine, the compressor housing 31 that can be arranged in the intake tract of the internal combustion engine, and the bearing housing 41 of the rotor bearing unit 40 between the turbine housing 21 and the compressor housing 31 are arranged one behind the other on the common turbocharger axis 11 and are connected to one another in terms of assembly.
  • the so-called turbocharger rotor 10 of the exhaust gas turbocharger 1 consists of the turbine rotor 12, the compressor rotor 13 and the rotor shaft 14.
  • the turbine rotor 12 and the compressor rotor 13 are arranged on the opposite ends of the common rotor shaft 14 and are non-rotatably connected to them.
  • the rotor shaft 14 extends axially through the bearing unit 40 in the direction of the turbocharger axis 11 and is rotatably mounted in it, by means of radial shaft bearings and one axial shaft bearing, axially and radially about its longitudinal axis, the rotor shaft axis of rotation 15, with the rotor shaft axis of rotation 15 and the turbocharger axis 11 coincide, i.e. coincide.
  • the turbocharger rotor 10 rotates in operation to Rotor shaft axis of rotation 15 of the rotor shaft 14.
  • the rotor axis of rotation and the turbocharger axis 11 are represented by the drawn-in center line and characterize the axial alignment of the exhaust gas turbocharger 1.
  • the compressor impeller 13 is arranged centrally in the compressor housing 31, with the compressor housing 31 having an air inlet connector 33 with the air inlet duct 33a for the intake air mass flow and a compressor spiral duct 32 arranged around the compressor impeller 13 for discharging the compressed air mass flow.
  • the turbine impeller 12 is arranged centrally in the impeller chamber 25, with the turbine housing 21 having an exhaust gas spiral duct 22 arranged around the turbine impeller 12 for supplying the exhaust gas mass flow to the turbine impeller 12 and an exhaust gas outlet connector 74 with an exhaust gas outlet duct 74a for discharging the exhaust gas -Has mass flow.
  • an exhaust gas guide device 50 In the transition area, radially between the exhaust gas spiral channel 22 and the turbine wheel inlet opening (not visible here) of the impeller space 25, an exhaust gas guide device 50, also referred to as variable turbine geometry or VTG for short, is arranged in a ring around the turbine impeller 12.
  • This exhaust gas guide device 50 has a bearing ring disk 51 , a cover ring disk 52 and exhaust gas guide vanes 60 .
  • annular exhaust gas duct 54 that runs concentrically around turbine impeller 12 and connects exhaust gas spiral duct 22 and impeller space 25, with an annular duct rear wall 55 on bearing housing side 23 of turbine housing 21 and an annular duct front wall 56 on the Exhaust gas outlet side 24 of the turbine housing 21 is formed, with a ring channel width being defined by the distance between the ring channel rear wall 55 and the ring channel front wall 56 .
  • annular duct 54 Arranged in annular duct 54 are a plurality of exhaust gas guide vanes 60, each of which has a vane leading edge, a vane trailing edge, and a vane axis of rotation which, with respect to turbocharger axis 11, is at least predominantly axial, between annular duct rear wall 55 and annular duct front wall 56, i.e transverse to the direction of flow of the exhaust gas mass flow, over the annular channel width, and the exhaust guide vanes 60 extend from the vane leading edge to the vane trailing edge in Flow direction of the exhaust gas mass flow extend.
  • the exhaust guide vanes 60 are rotatably mounted about their respective vane axes of rotation from a closed position to an open position.
  • an actuating mechanism 59 is provided, which is arranged on the bearing housing side 23 of the bearing ring disk and the turbine housing 21 and is operatively connected to the blade axes of rotation of the exhaust gas guide vanes 60 for their synchronous actuation.
  • FIG. 1 An embodiment of an exhaust gas turbocharger 1 according to the invention is shown in FIG. This also has the essential components of a conventional exhaust gas turbocharger as shown in FIG. 1, which are identified in FIG. 2 with the same reference symbols.
  • a lubricant inlet channel 45 for feeding in the lubricant, for example from the oil circuit of a connected internal combustion engine, and a lubricant outlet channel 46 for returning the lubricant, for example into said oil circuit.
  • the bearing housing 41 and the turbine housing 21 are formed together as an integral housing 71 manufactured in one piece and that the exhaust gas guide device 50, from an exhaust gas outlet side 24 of the integral housing 71 facing away from the compressor housing 31 (i.e. in Fig. 1 from the right) is inserted into a receiving opening 72 of the integral housing 71 in the axial direction relative to the turbocharger axis 11 .
  • the receiving opening 72 is delimited here radially by a peripheral edge of the housing wall of the exhaust gas spiral duct 22 lying on the exhaust gas outlet side 24 .
  • the receiving opening 72 is through the so-called bearing housing shield 42, which is formed by the wall of the part of the integral housing 71 that forms the bearing housing 41.
  • an integral housing cover 73 On the exhaust gas outlet side 24 of the integral housing 71, an integral housing cover 73 is arranged, which has the receiving opening 72 at least partially covers and has an exhaust gas outlet nozzle 74 with an exhaust gas outlet channel 74a to which, for example, the exhaust system of an internal combustion engine can be connected.
  • the integral housing cover 73 connects to the outside of the housing wall of the exhaust gas spiral duct 22 in an exhaust-tight manner at its peripheral outer edge and in this way seals the integral housing 71 on the exhaust gas outlet side 24, apart from the exhaust gas outlet duct 74a, from the environment.
  • the exhaust gas guiding device 50 including the actuating mechanism 59 is also covered or enclosed by the integral housing cover 73 .
  • the exhaust gas can therefore only be routed in a controlled manner via the annular exhaust gas channel 54 formed between the cover ring disk 52 and the bearing ring disk 51, along the sealing contour 53 through the blading of the turbine rotor 12 into the exhaust gas outlet channel 74a and from there, for example, into a subsequent exhaust gas aftertreatment system (not shown) are initiated.
  • a circumferential sealing ring 76 for example, can be arranged in the radial edge area of integral housing cover 73 between the outside of the housing wall of exhaust gas spiral duct 22 and integral housing cover 73.
  • a circumferential annular shoulder 26 extending in the axial direction is provided for centering and positioning the integral housing cover 73 on the integral housing 71 Integral housing cover 73 is provided for this purpose with a cover edge 77 designed to complement the ring shoulder 26 , which cooperates with the ring shoulder 26 , centering the integral housing cover 73 with respect to the rotor shaft axis of rotation 15 .
  • the half-sectional representation of the exhaust gas turbocharger 1 in Fig. 2 also clearly shows that the integral housing 71 has a coolant channel 75, which at least partially surrounds the exhaust gas spiral channel 22 on the bearing housing side 23 of the integral housing 71 facing the compressor housing 31, with this also extends at least partially over the outer circumference of the exhaust gas spiral duct 22 and thus at least partially envelops the exhaust gas spiral duct 22 over a large area.
  • the coolant channel 75 extends into that part of the integral housing 71 which forms the bearing housing 41 whereby the area of the bearing arrangement in the bearing housing 41 is effectively shielded and cooled from the heat input from the area of the exhaust gas spiral channel 22 .
  • the coolant preferably a coolant
  • the coolant is supplied to the integral housing 71 via a coolant inlet connection 75a, flows through the coolant channel 75 and is then discharged from the integral housing 71 via a coolant outlet connection 75b.
  • the integral housing 71 is in fluid connection, for example, directly with a cooling system of the internal combustion engine via the coolant inlet connection 75a and the coolant outlet connection 75b.
  • the embodiment of the exhaust gas turbocharger 1 according to the invention shown in Fig. 2 is also characterized in that the exhaust gas spiral duct 22 of the integral housing 71 according to the invention on a bearing housing side 23 facing the compressor housing 31 at least partially in the axial direction towards the compressor housing 31 via the bearing housing 41 forming Part of integral housing 71 overhangs. As can be seen, this enables a compact design of the exhaust gas turbocharger.
  • variable exhaust gas guide device 50 of the exhaust gas turbocharger 1 is shown in detail in the installation position in FIG. 2 .
  • the variable exhaust gas guide device 50 has a bearing ring disk 51 , a cover ring disk 52 , a plurality of exhaust gas guide vanes 60 arranged distributed over the circumference between the bearing ring disk 51 and the cover ring disk 52 , and an actuating mechanism 59 .
  • the receiving opening 72 is delimited in the axial direction by a bearing housing shield 42 in the part of the integral housing 71 that forms the turbine housing 21, the bearing housing shield 42 being formed by a housing wall of the integral housing 71 that holds the part of the integral housing 71 that forms the bearing housing 41 in the interior of the receiving opening limited.
  • the exhaust gas guiding device 50 is arranged in the receiving opening 72 such that the cover ring disk 52 is arranged on the side facing the bearing housing plate 42 and the actuating mechanism 59 is arranged on the side of the exhaust gas guiding device 50 facing away from the bearing housing plate 42 in the receiving opening 72 .
  • the cover ring disk 52, the exhaust gas guide vanes 60, the bearing ring disk 51 and the actuating mechanism 59 are arranged in the direction of the exhaust gas outlet side 24 according to the aforementioned sequence, with the cover ring disk 52 being on a stop section 42a of the bearing housing shield 42 positioned centered on the axis of rotation of the rotor shaft 15 .
  • the stop shoulder is designed, for example, as a step that is set back from the plane of the bearing housing shield 42 and rotates in relation to the rotor shaft axis of rotation 15, which serves both as an axial stop and as a centering cylinder.
  • the design of the exhaust gas guide device 50 also shows that the sealing contour 53 is formed by the bearing ring disk 51 in relation to the outer contour of the turbine rotor 12.
  • the sealing contour 53 can also be formed by the inner wall of the integral housing cover 73 .
  • variable exhaust gas guide device 50 and the integral housing cover 26 can be designed as a pre-assembled cartridge assembly.
  • the components of the exhaust gas guide device 50 are connected directly or indirectly to the integral housing cover 73 in terms of assembly technology and can be inserted together with this as a structural unit in the receiving opening 72 .
  • the integral housing 71 shown represents an embodiment of the integral housing 71 according to the invention, in which the bearing housing 41 of the bearing unit 40 and the turbine housing 21 of the exhaust gas turbine 20 with the exhaust gas spiral duct 22 in one piece manufactured component are summarized.
  • a receiving opening 72 for receiving an exhaust gas guide device 50 is provided in the axial direction from an exhaust gas outlet side 24 of the integral housing 71 facing away from the bearing housing 41 , in the part of the integral housing 71 forming the turbine housing 21 .
  • the integral housing 71 shown also has the coolant duct 75, which at least partially surrounds the exhaust gas spiral duct 22 on its bearing housing side 23 and extends into the part of the bearing housing 41 forming the Integral housing 71 extends, while the exhaust gas spiral channel 22 is formed so that it at least partially overhangs the bearing housing 41 forming part of the integral housing 71 on the bearing housing side 23 in the axial direction.

Abstract

L'invention concerne un turbocompresseur à gaz d'échappement (1) pour un moteur à combustion interne qui comprend une turbine à gaz d'échappement (20) possédant un dispositif de guidage de gaz d'échappement (50), un compresseur d'air radial (30) et une unité de palier (40) disposée entre la turbine et le compresseur, dans laquelle un arbre de rotor (14) est monté rotatif conjointement avec la roue de turbine (12) et la roue de compresseur (13). Le logement de palier (41) et le carter de turbine (21) sont conçus sous la forme d'un carter intégral (71) d'un seul tenant et le dispositif de guidage de gaz d'échappement (50) est inséré dans la direction axiale dans une ouverture de réception (72) du carter intégral (71) depuis un côté sortie de gaz d'échappement (24) du carter intégral (71) orienté à l'opposé du compresseur d'air radial (30), et un couvercle de carter intégral (73) est disposé sur le côté sortie de gaz d'échappement (24) du carter intégral (71) et recouvre au moins partiellement l'ouverture de réception (72) et présente un raccord de sortie de gaz d'échappement (74) pourvu d'un canal de sortie de gaz d'échappement (74a). L'invention concerne également le carter intégral (71) pour le turbocompresseur à gaz d'échappement selon l'invention. Les objets selon l'invention permettent néanmoins de réduire la taille de construction axiale ainsi que les coûts de fabrication.
PCT/EP2022/058111 2021-04-30 2022-03-28 Turbocompresseur à gaz d'échappement doté d'un carter intégral et d'une géométrie de turbine variable et carter intégral pour un turbocompresseur à gaz d'échappement WO2022228803A1 (fr)

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DE102021204366.6A DE102021204366A1 (de) 2021-04-30 2021-04-30 Abgasturbolader mit einem Integralgehäuse und variabler Turbinengeometrie und Integralgehäuse für einen Abgasturbolader
DE102021204366.6 2021-04-30

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WO2022228803A1 true WO2022228803A1 (fr) 2022-11-03

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Citations (7)

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EP1536103A1 (fr) 2003-11-28 2005-06-01 BorgWarner Inc. Turbomachine avec aubes de guidage et agencement de fixation
DE102008000776A1 (de) 2008-01-21 2009-08-13 Bosch Mahle Turbo Systems Gmbh & Co. Kg Turbine, insbesondere für einen Abgasturbolader, sowie Abgasturbolader
DE102008017821A1 (de) 2008-04-08 2009-10-22 Continental Automotive Gmbh Befestigungselement und Abgasturbolader mit variabler Turbinengeometrie
WO2014140598A1 (fr) * 2013-03-15 2014-09-18 Imperial Innovations Limited Turbine asymétrique à double entrée
US20140369811A1 (en) * 2012-01-25 2014-12-18 Borgwarner Inc. Integrated turbocharger casting
DE102018221812A1 (de) 2018-12-14 2020-06-18 Continental Automotive Gmbh Abgasturbine mit einer Abgasleiteinrichtung für einen Abgasturbolader und Abgasturbolader
US20200248586A1 (en) * 2019-01-31 2020-08-06 Transportation IP Holdings, LLP Systems for a turbocharger

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US3673798A (en) 1971-01-08 1972-07-04 Gen Motors Corp Turbocharged internal combustion engine
JP5915146B2 (ja) 2011-12-16 2016-05-11 株式会社Ihi 可変ノズルユニット及び可変容量型過給機

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1536103A1 (fr) 2003-11-28 2005-06-01 BorgWarner Inc. Turbomachine avec aubes de guidage et agencement de fixation
DE102008000776A1 (de) 2008-01-21 2009-08-13 Bosch Mahle Turbo Systems Gmbh & Co. Kg Turbine, insbesondere für einen Abgasturbolader, sowie Abgasturbolader
DE102008017821A1 (de) 2008-04-08 2009-10-22 Continental Automotive Gmbh Befestigungselement und Abgasturbolader mit variabler Turbinengeometrie
US20140369811A1 (en) * 2012-01-25 2014-12-18 Borgwarner Inc. Integrated turbocharger casting
WO2014140598A1 (fr) * 2013-03-15 2014-09-18 Imperial Innovations Limited Turbine asymétrique à double entrée
DE102018221812A1 (de) 2018-12-14 2020-06-18 Continental Automotive Gmbh Abgasturbine mit einer Abgasleiteinrichtung für einen Abgasturbolader und Abgasturbolader
US20200248586A1 (en) * 2019-01-31 2020-08-06 Transportation IP Holdings, LLP Systems for a turbocharger

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