WO2012062407A1 - Elément rapporté pour une turbine d'un turbocompresseur à gaz d'échappement, turbocompresseur à gaz d'échappement ainsi que turbine pour un turbocompresseur à gaz d'échappement - Google Patents

Elément rapporté pour une turbine d'un turbocompresseur à gaz d'échappement, turbocompresseur à gaz d'échappement ainsi que turbine pour un turbocompresseur à gaz d'échappement Download PDF

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Publication number
WO2012062407A1
WO2012062407A1 PCT/EP2011/005309 EP2011005309W WO2012062407A1 WO 2012062407 A1 WO2012062407 A1 WO 2012062407A1 EP 2011005309 W EP2011005309 W EP 2011005309W WO 2012062407 A1 WO2012062407 A1 WO 2012062407A1
Authority
WO
WIPO (PCT)
Prior art keywords
exhaust gas
turbine
gas turbocharger
insert element
spiral
Prior art date
Application number
PCT/EP2011/005309
Other languages
German (de)
English (en)
Inventor
Torsten Hirth
Benjamin Schaal
Siegfried Sumser
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
Priority to JP2013538088A priority Critical patent/JP6025737B2/ja
Publication of WO2012062407A1 publication Critical patent/WO2012062407A1/fr
Priority to US13/893,278 priority patent/US20130330178A1/en

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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
    • 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
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • 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

Definitions

  • the invention relates to an insert element for a turbine of an exhaust gas turbocharger according to claim 1, an exhaust gas turbocharger for an internal combustion engine according to claim 4, a turbine for an exhaust gas turbocharger specified in the preamble of claim 7, an exhaust gas turbocharger according to claim 8 and a turbine for an exhaust gas turbocharger in the Preamble of claim 9 specified type.
  • DE 25 39 711 discloses a volute casing for turbomachinery, in particular in an exhaust gas turbocharger with at least partially adjustable cross-section, wherein at least one slidably guided on the radially inner wall of the volute casing is provided following this wall in the circumferential direction displaceable tongue.
  • DE 10 2008 039 085 A1 discloses an internal combustion engine for a vehicle as known, which comprises an exhaust-gas turbocharger.
  • the exhaust gas turbocharger comprises a compressor in an intake tract of the internal combustion engine and a turbine in an exhaust gas tract of the internal combustion engine, wherein the turbine has a turbine housing which comprises a spiral duct coupled to an exhaust pipe of the exhaust gas tract and a turbine wheel.
  • the turbine wheel is within a receiving space of the
  • Turbine arranged and driven to drive a non-rotatably connected to the turbine wheel compressor wheel of the compressor acted upon by the spiral duct exhaust gas of the internal combustion engine.
  • the turbine comprises an adjusting device, by means of which a spiral inlet cross section of the spiral channel and a nozzle cross section of the spiral channel to the receiving space are jointly adjustable.
  • the first aspect of the invention relates to an insert element for a turbine of a
  • Exhaust gas turbocharger which is at least partially, in particular completely, can be used in a housing of the turbine, and which has at least one in the circumferential direction of the insert element at least partially extending over the circumference and flowing through the turbine exhaust flowing through the spiral channel.
  • the spiral channel is at least partially open in the axial direction of the insert element and thus of the turbine on at least one end face of the insert element.
  • the insert element is particularly time-consuming and inexpensive to produce, which is particularly due to the open design of the spiral channel.
  • the insert element is, for example, as a turned part and / or as a milled part, i. produced by turning and / or milling, or by another, in particular machining, manufacturing process.
  • insert element can by a combination of manufacturing processes, in particular the described
  • the spiral channel not required. This keeps the production costs for the insert element and thus for the turbine low, which has an advantageous effect on particularly low production costs for the exhaust gas turbocharger.
  • the spiral channel on the at least one end face in the circumferential direction of the insert element and thus the turbine circumferentially formed completely open. This allows a particularly time-consuming and cost-effective production of the insert element, resulting in low production costs for the exhaust gas turbocharger.
  • exhaust gas turbochargers is in the context of a serial production of cars to a component which is to be manufactured in particularly high quantities.
  • the low production costs made possible by the insert element according to the invention due to economies of scale, have a particularly advantageous effect on low costs for the motor vehicles.
  • the insert element according to the invention also allows a particularly
  • the turbine which is designed for example as a radial turbine, exhaust gas flowing through to a turbine wheel of the turbine, which in the assembled state of the exhaust gas turbocharger in the radial direction of the
  • At least substantially annular insert element is arranged inside the insert element.
  • the spiral channel has an outlet opening, via which the spiral channel in the radial direction of the insert element on the inside of the
  • the spiral channel allows the exhaust gas to be guided in such a way that it can flow and thus drive the turbine wheel at least substantially in the radial direction of the insert element or of the turbine wheel.
  • the insert element has at least one further in the circumferential direction of the insert element at least partially extending over the circumference and flowing through the turbine exhaust gas flowing through the spiral channel, the further spiral channel in the axial direction on at least one end side of the insert element at least partially is open.
  • the insert element is also particularly time-consuming and inexpensive to produce, if several, i. E. at least two, three or more, spiral channels are provided.
  • Insertion element with the plurality of spiral channels a particularly favorable flow against the turbine wheel, so that the turbine is particularly efficient operable.
  • This efficient operation of the turbine due to the favorable flow conditions for the turbine also affects a very good efficiency of the entire exhaust gas turbocharger, which the fuel consumption and the C0 2 emissions of the exhaust gas turbocharger associated internal combustion engine, which is to be charged by means of the exhaust gas turbocharger, keeps low.
  • the insert element can also be used for an otherwise fluid energy machine, in particular a charging device, as an exhaust gas turbocharger of an internal combustion engine.
  • the insert element according to the invention can also be used in a charging device, for example one
  • Turbomachine for a fuel cell.
  • the exhaust gas of the fuel cell flows through the turbine, wherein the exhaust gas of the fuel cell by means of the
  • insert element according to the invention is particularly streamlined the turbine wheel can be fed.
  • the insert element according to the invention has a plurality of spiral channels, then these are arranged, for example, in the circumferential direction of the insert element behind one another and / or in the axial direction at a common height. It can also be provided that the spiral channels are arranged in the axial direction of the insert element next to one another and / or in the circumferential direction at a common height. The corresponding arrangement of the spiral channels is on the corresponding spiral channels.
  • the second aspect of the invention relates to an exhaust gas turbocharger for a
  • Internal combustion engine which comprises a turbine and at least one at least partially accommodated in a turbine housing of the turbine insert element, in particular an inventive insert element.
  • the insert element has at least one in the circumferential direction of the insert element at least
  • Insert element especially due to the open design of the spiral channel to produce particularly cost, which has a positive effect on low production costs for the turbine and thus for the entire exhaust gas turbocharger.
  • Spiral channel in the axial direction of the exhaust gas turbocharger on a in the direction of a Turbine outlet of the turbine facing end side of the insert element at least partially open and / or the exhaust gas turbocharger comprises
  • the insert element allows through the at least one spiral channel a particularly streamlined guidance of the exhaust gas to a turbine wheel of the turbine of the exhaust gas turbocharger, so that the entire exhaust gas turbocharger has a particularly efficient operation.
  • the insert element is particularly cost-effective
  • the insert element of the second aspect of the invention is, for example, as a turned part and / or as a milled part, i. by turning and / or by milling or by another, in particular machining, manufacturing process and / or by a
  • both the insert element of the first as well as the second aspect of the invention is formed as a sheet-metal component, which comprises a plurality of welded together and / or otherwise connected or joined sheet metal parts.
  • the insert element of the second aspect of the invention is in contact, for example, with another component of the exhaust gas turbocharger.
  • the insert element rests against the component, and the component covers, for example with a wall, the open region of the spiral channel.
  • the component is for example the
  • insert element indirectly supported on the bearing housing, whereby the Insert element under application of force in contact with the component or the component is held under application of force in contact with the insert element.
  • a spring element in particular a plate spring, is provided, by means of which the insert element is supported on the bearing housing.
  • the bearing housing can at least partially at least indirectly on the
  • At least one cover element is provided, by means of which a region of the spiral channel in which the spiral channel is formed open, at least partially covered.
  • the open area of the spiral channel is completely covered by the lid member, so that a particularly streamlined guidance of the exhaust gas can be made to the turbine wheel.
  • Turbine housing and the insert element may have an uncomplex and at least predominantly planar geometry to cover the spiral channel in regions. As a result of this uncomplex geometry, especially when the
  • Cover element is formed at least partially flat, the lid is distorted during operation of the exhaust gas turbocharger under possibly also changing temperature stress at least substantially uniformly.
  • low-efficiency leaks over which exhaust gas could flow out of the spiral channel are at least substantially avoided or the risk of such leaks is very low.
  • the lid member to hold under application of force at least indirectly to the insert element to cover the spiral channel very tight.
  • the cover element is supported at least indirectly on the one hand on the insert element and on the other hand on the bearing housing.
  • the manufacturing costs for the exhaust gas turbocharger of the second aspect of the invention low holding embodiment is that the insert element formed as a separate element from the turbine housing and during assembly of the Exhaust gas turbocharger is partially used in the turbine housing. This allows the turbocharger to be installed in a timely and cost-effective manner.
  • the third aspect of the invention relates to a turbine for an exhaust gas turbocharger, comprising a turbine housing having a receiving space for receiving a turbine wheel, which at least one through the turbine exhaust flowing through and circumferentially of the receiving space at least partially extending over the circumference spiral channel with at least one inlet opening to allow an inflow of exhaust gas into the spiral channel, wherein via the spiral channel to the receiving space exhaust gas can be fed.
  • At least one channel part is provided, by means of which the at least one spiral channel is subdivided downstream of the inflow opening at least two spiral channels.
  • Advantageous embodiments of the first two aspects are to be regarded as advantageous embodiments of the second aspect of the invention and vice versa.
  • at least two spiral part channels are formed by the channel part, which during the operation of the turbine via the spiral partial channels common
  • Spiral channel to be supplied with exhaust gas.
  • An exhaust gas flow flowing through the spiral channel is divided by the spiral partial channels into respective partial flows, so that the turbine wheel accommodated in the receiving space flows particularly favorably with the exhaust gas and is therefore to be driven.
  • This enables a particularly efficient and efficient operation of the turbine.
  • this keeps the production costs and thus the manufacturing costs for the turbine and thus for the entire exhaust gas turbocharger very low.
  • the channel part of the third aspect of the invention is formed, for example, as an insert element and thus as a separate turbine element to the housing, which is at least partially, in particular completely, received in the turbine housing.
  • This allows a particularly cost-effective production of the channel part and the entire turbine.
  • the channel part is, for example, as a turned part and / or as a milled part, i. produced by turning and / or by milling or by any other, in particular cutting, manufacturing process. It is equally possible that the as
  • Insert element formed channel part is made by a precision casting process.
  • the channel part formed as an insert element is produced by a combination of manufacturing methods and / or the described manufacturing method.
  • the channel part is formed integrally with the turbine housing. In this case, the channel part is milled, for example, in the turbine housing. For the preparation of the turbine housing and the integrally formed with this channel part can be provided that a
  • Rough contour of the channel part is for example cast by a sand casting method and an exact final contour of the channel part, in particular the spiral part channels, by a mechanical processing, such as milling, is formed.
  • the channel portion of the third aspect of the invention may also include a plurality of, e.g. at least two, three or more, Spiralteilkanäle have, which are arranged for example in the circumferential direction of the channel part over its circumference one behind the other or in the axial direction at a common height or in the circumferential direction at a common height and / or in the axial direction next to each other.
  • a plurality of, e.g. at least two, three or more, Spiralteilkanäle have which are arranged for example in the circumferential direction of the channel part over its circumference one behind the other or in the axial direction at a common height or in the circumferential direction at a common height and / or in the axial direction next to each other.
  • At least one of the spiral part passages of the channel part is open at least in some areas in the axial direction of the turbine on at least one end face of the passage part.
  • Circumferentially circumferential direction of the channel part is formed completely open.
  • the region in which the spiral sub-channel of the channel part of the third aspect of the invention is designed to be open can be open, for example, in the direction of a turbine outlet of the turbine or in the direction of a bearing housing of the exhaust gas turbocharger with the turbine of the third aspect of the invention.
  • spiral part passages of the passage part of the third aspect of the invention in particular if this is designed as an insert element, to be circumferentially completely closed circumferentially in the axial direction of the turbine on the two-sided end faces.
  • This allows on the one hand a particularly streamlined guidance of the exhaust gas to the receiving space and on the other hand a particularly time-consuming and cost-effective installation and thus manufacture of the turbine of the exhaust gas turbocharger, since the particular designed as an insert channel part inexpensively and quickly at least partially introduced into the turbine housing and can be arranged there.
  • the fourth aspect of the invention relates to an exhaust gas turbocharger with a
  • Turbine according to the invention of the third aspect of the invention wherein in particular in the axial direction of the exhaust gas turbocharger or the turbine between a housing part, in particular a bearing housing, the exhaust gas turbocharger and the channel part from the channel part at least partially, in particular in the axial direction at least partially, limited space is formed , which is fluidly connected to the at least one spiral channel.
  • Advantageous embodiments of the first three aspects of the invention are to be regarded as advantageous embodiments of the fourth aspect of the invention and vice versa. This fluidic connection causes at least substantially equal pressure in the spiral channel and in the intermediate space.
  • This pressure can then act in particular at least substantially in the axial direction on a wall of the channel part, wherein the wall on the one hand limits the gap and on the other hand, at least one of the spiral part channels.
  • a lower pressure acts on the wall than on the sides of the gap, as in the individual
  • Spiral part channels a pressure, in particular a static pressure, prevails, which is less than the pressure, in particular the static pressure, in the intermediate space or in the at least one spiral channel.
  • Channel part which acts in a corresponding, in particular at least substantially in the axial direction.
  • This application of force can be used to press the channel part designed in particular as an insert element against a further component of the exhaust gas turbocharger or at least indirectly hold the channel part to the component while applying force.
  • this force application can be used to hold the passage part to the corresponding part, whereby the part can then tightly cover the open area of the spiral passage.
  • a corresponding gap may be provided according to the fourth aspect of the invention between the insert member and a housing part of the turbine or the exhaust gas turbocharger, wherein the intermediate space is fluidly connected to a further spiral channel, in particular a feed channel in that a higher pressure prevails in the intermediate space than in the at least one spiral channel formed by the insert element.
  • the insert element can then be subjected to force applied analogously to a component, for example the cover element, or a housing part, for example the turbine housing, in a manner substantially equivalent to the open area of the spiral channel formed by the insert element to cover tightly.
  • the fifth aspect of the invention relates to a turbine for an exhaust gas turbocharger, with a turbine housing, which has at least one spiral channel and a receiving space in which a turbine wheel is rotatably received.
  • the turbine wheel can be acted upon by the spiral channel with exhaust gas, wherein the turbine comprises an adjusting device by means of which a spiral inlet cross section and / or a nozzle cross section of the at least one spiral channel to the receiving space is adjustable.
  • Adjusting device for adjusting the spiral inlet cross-section and / or the
  • Nozzle cross-section has at least two intermeshing teeth.
  • Advantageous embodiments of the first four aspects of the invention are to be regarded as advantageous embodiments of the fifth aspect of the invention and vice versa. Adjusting the spiral inlet cross section and / or the
  • Nozzle cross section over the teeth allows a particularly large
  • Spiraleintrittsquerites and / or the nozzle cross section are variably adjustable.
  • a particularly high throughput spread of the variable turbine of the fifth aspect of the invention is made possible, whereby the turbine is particularly efficient adapted to a plurality of operating points of the exhaust gas turbocharger associated internal combustion engine.
  • the turbine in particular due to the adjustability of the teeth, which are advantageously arranged in the turbine housing, only a small space requirement, which contributes to the solution or to avoid package problems, especially in a space-critical area such as an engine compartment.
  • the adjusting device For adjusting the spiral cross section and / or the nozzle cross section, the adjusting device comprises at least one locking element associated with the spiral channel, for example a tongue, which is movable in the circumferential direction of the receiving space or the turbine wheel.
  • Another advantage of the gearing is that a harmonious translation between an actuator for moving the Versperritess and the VersperrAvem itself can be achieved over the adjustment.
  • the adjusting body is arranged for example on an adjusting ring, which is arranged on the teeth and the actuator about an axis of rotation rotatable in the turbine housing.
  • the obturator When the ring is rotated, the obturator also moves so that the volute inlet cross-section and / or the nozzle cross-section are variably adjusted, i. can be increased or decreased.
  • Adjustment device is rotatably connected.
  • the adjusting ring is connected via the adjusting shaft with the actuator.
  • the actuator is, for example, an electric motor having an output shaft which is rotatable about a rotation axis for moving the blocking body.
  • the adjusting shaft is connected to the output shaft or formed by the output shaft, so that a rotation of the output shaft of
  • Electric motor causes a rotation of the adjusting and thus causes a movement of the Versperr stressess.
  • FIG. 1 in fragmentary form a schematic longitudinal sectional view of a
  • Exhaust gas turbocharger for an internal combustion engine with a turbine with a turbine housing, in which a multi-segment insert is used;
  • Fig. 2 is a schematic perspective view of the multi-segment insert of
  • FIG. 3 shows a schematic cross-sectional view of the turbine of the exhaust-gas turbocharger according to FIG. 1;
  • Fig. 5 is a schematic perspective view of a multi-segment insert a
  • FIG. 6 shows a schematic cross-sectional view of the turbine of the exhaust gas turbocharger according to FIG. 4;
  • Embodiment of the exhaust gas turbocharger according to FIG. 7 Embodiment of the exhaust gas turbocharger according to FIG. 7;
  • Embodiment of the exhaust gas turbocharger according to FIGS. 7 and 8; 10 shows a detail of a schematic longitudinal sectional view of another
  • FIG. 11 in fragmentary form a schematic longitudinal sectional view of another
  • FIG. 12 in fragmentary form a schematic longitudinal sectional view of another
  • FIG. 13 a detail of a schematic front view of the exhaust gas turbocharger according to FIG. 12.
  • Fig. 1 shows an exhaust gas turbocharger 10 with a turbine 12, which a
  • Turbine housing 14 and a bearing housing 16 includes. Through the turbine housing 14, a receiving space 18 is formed, in which a turbine wheel 20 of a rotor 22 of the exhaust gas turbocharger 10 is rotatably received.
  • the rotor 22 further comprises a shaft 24 with which the turbine wheel 20 is rotatably connected.
  • the exhaust gas turbocharger 10 further comprises a compressor, not shown in FIG. 1, with a compressor housing, through which a receiving space is formed, in which a compressor wheel of the rotor 22 is accommodated. Also, the compressor is rotatably connected to the shaft 24 so that the compressor via the shaft 24 and the turbine 20 is driven.
  • the rotor 22 is mounted in the bearing housing 16 and can rotate about a rotation axis 26.
  • a spiral channel 28 is partially formed, which serves as a feed channel.
  • the spiral channel 28 can via an inlet opening 30 of the
  • Spiral channels 28 exhaust gas in the exhaust gas turbocharger 10 associated
  • a multi-segment insert 36 which is shown perspectively and schematically in FIG. 2, is also arranged by means of which the spiral channel 28 is formed in regions by means of a wall 68.
  • the multi-segment insert 36 of the exhaust gas turbocharger 10 according to FIGS. 1 to 3 is designed as a separate to the turbine housing 14 insert element and has four spiral channels 38, 40, 42 and 44, which in the circumferential direction of the Mehrsegments hostedes 36 according to a directional arrow 46 in regions over the circumference of Multi-segment insert 36 run.
  • the spiral channels 38, 40, 42 and 44 are arranged in the circumferential direction one behind the other and in the axial direction of the multi-segment insert 36 and thus of the exhaust gas turbocharger according to a direction arrow 49 at a common height.
  • the spiral channels 38, 40, 42 and 44 are fluidly connected to the spiral channel 28 and are thus supplied by the spiral channels 38, 40, 42 and 44 common spiral channel 28 with exhaust gas.
  • the turbine wheel 20 is at least substantially flowed in the radial direction desselbigen particularly favorable flow of the exhaust gas and acted upon by this, so that the exhaust gas turbocharger 10 has a particularly efficient and low-efficiency operation.
  • the spiral channels 38, 40, 42 and 44 on respective outlet openings 50, 51, 52 and 53, via which the spiral channels 38, 40, 42 and 44 open into the receiving space 18 and through which the exhaust gas at least substantially in the radial direction of the Turbine wheel 20 and the multi-segment insert 36 according to a direction arrow 54, the turbine wheel 20 can flow.
  • the turbine 12 is thus a radial turbine.
  • the exhaust gas turbocharger 10 further comprises an adjusting device 56 having respective tongues 58, 60, 62 and 64 associated with the spiral channels 38, 40, 42 and 44 and the respective outlet openings 50, 51, 52 and 53.
  • the tongues 58, 60, 62 and 64 are connected to an adjusting ring 66 which is rotatable about the axis of rotation 26.
  • a rotation of the adjusting ring 66 which is also referred to as a tongue slider, causes an adjustment, in particular a displacement, the tongues 58, 60, 62 and 64 in
  • Spiral channel 38 is representative of the nozzle cross-sections of the A R of the spiral channels 38, 40, 42 and 44 is shown) can be variably adjusted.
  • the multi-segment insert 36 may be integrally formed, for example, by a precision casting process. It is equally possible that the multi-segment insert 36 as
  • Sheet metal component is formed with a plurality of sheet metal parts, which form, for example, the walls 68, 70 and 72, and which are welded together.
  • the multi-segment insert 36 can also have more or fewer spiral channels or segments.
  • the multi-segment insert 36 is in the axial direction according to the directional arrow 49 by means of the bearing housing 16 in the
  • Bearing housing 16 supported via respective contact surfaces 74, wherein the bearing housing 16 connected to the turbine housing 14, for example screwed, is.
  • the segment insert 36 is supported on the turbine housing 14 via respective contact surfaces 76.
  • the bearing housing 16 presses the multi-segment insert 36 in the axial direction according to the directional arrow 49 in the direction of a turbine outlet 78 according to a directional arrow 80 against the turbine housing 14 and holds the Multi-segment insert 36 in the axial direction in this. This is the result
  • Multi-segment insert 36 is pressed into the turbine housing 14.
  • FIGS. 4 to 6 show an alternative embodiment of the exhaust gas turbocharger 10 according to the preceding FIGS. 1 to 3, which is denoted by 10 1 .
  • a multi-segment insert 36 In the turbine housing 14 of the turbine 12 of the exhaust gas turbocharger 10 1 is a multi-segment insert 36 first
  • the multi-segment insert 36 ' permits a particularly simple and cost-effective installation and production of the exhaust-gas turbocharger 10 and particularly efficient operation, the multi-segment insert 36' is itself particularly cost-effective to produce as a result of the open design of the spiral channels 38, 40, 42 and 44.
  • the multi-segment insert 36 ' is for example as a turned part and / or as a milled part, by a precision casting process or by a combination of manufacturing processes, in particular the described manufacturing process produced.
  • the multi-segment insert 36 In order to avoid efficiency-effective leaks and thus an overflow of exhaust gas from one of the spiral channels 38, 40, 42 and 44 in one of the other spiral channels 38, 40, 42 and 44, the multi-segment insert 36 'on its open end 82 against the turbine housing 14 by means held the bearing housing 16, so that the
  • Turbine housing 14 with a corresponding portion of a wall 86 of the
  • Turbine housing 14 the spiral channels 38, 40, 42 and 44 of the multi-segment insert 36 'completely and tightly covers.
  • the multi-segment insert 36 ' is supported on the bearing housing 16 via a plate spring 75.
  • the bearing housing 16 is not partially supported only on the plate spring 75 on the multi-segment insert 36 ', but also partially on the turbine housing 14. This causes the multi-segment insert 36 'below
  • Multi-segment insert 36 ' is pressed into the turbine housing 14.
  • FIG. 7 shows a further alternative embodiment of the exhaust gas turbocharger 10 and 10 1 which is denoted by 10.sup.
  • a multi-segment insert 36" is accommodated, which differs from the multi-segment insert 36 in that
  • FIG. 5 shows that the end face 84 of the end face 82 is arranged opposite in the axial direction. It can be seen from FIG. 7 that the open front side 84 of the multi-segment insert 36 "thus extends in the direction of the
  • the exhaust gas turbocharger 10 comprises a cover 86, which is also received in the turbine housing 14.
  • the lid 86 has a flat wall 89, by means of which the spiral channels 38, 40, 42 and 44 circumferentially completely covered circumferentially.
  • the cover 86 is supported on the multi-segment insert 36 "via respective contact surfaces 74" and abuts on the multi-segment insert 36 ".
  • the multi-segment insert 36" and the cover 86 are held in the axial direction by the bearing housing 16 which contacts respective contact surfaces 74 ' the lid 86 abuts.
  • the bearing housing 16 is located under the intermediary of the lid 86 at the
  • Multi-segment insert 36 " which in turn abuts and is supported on the turbine housing 14 via the contact surfaces 76.
  • the cover 86 is pressed by means of the bearing housing 16 to the multi-segment insert 36" according to the directional arrow 80, whereby leakage between the spiral channels 38th , 40, 42 and 44 of the multi-segment insert 36 "are at least substantially avoided, as a result of which the multi-segment insert 36" is above the cover 86 and the cover 86 also pressed into the turbine housing 14.
  • Fig. 8 shows an alternative embodiment of the turbocharger 10, 10 1 and 10 "according to the preceding Fig., which is designated by the reference numeral 10 1 ".
  • the channel part 37 differs from the multi-segment inserts 36, 36 'and 36 "to the effect that the channel part 37 is formed integrally with the turbine housing 14 of the turbine 12 of the exhaust gas turbocharger 10 1 ". 7, which is formed integrally with the turbine housing 14.
  • the spiral channels 38, 40, 42 and 44 of the channel part 37 are in FIG axial direction according to the
  • Channel part 37 circumferentially formed completely open.
  • the lid 86 is provided, which is pressed by means of the bearing housing 16 in the axial direction according to the directional arrow 80 against the turbine housing 14, is held thereon and extends over contact surfaces 74 As a result, the cover 86 is pressed into the turbine housing 14.
  • Turbine housing 14 milled, wherein the spiraling walls 68, which bound the spiral channels 38, 40, 42 and 44 in the radial direction according to the directional arrow 54, are formed.
  • FIG. 9 shows, based on a further embodiment of an exhaust gas turbocharger 10, a possibility of holding a multi-segment insert 36 "in the turbine housing 14 of the turbine 12 of the exhaust gas turbocharger 10 IV .
  • the multi-segment insert 36 '" is, for example, the
  • the multi-segment insert 36 '" has the spiral channels 38, 40, 42 and 44 and the same function as the multi-segment insert 36.
  • the multi-segment insert 36 '" is by means of the
  • Bearing housing 16 held in the turbine housing 14 by the bearing housing 16 is connected to the turbine housing 14, for example screwed, and presses the multi-segment insert 36 '' in the axial direction according to the directional arrow 49 to the turbine housing 14 according to the directional arrow 80.
  • Directional arrows 88 indicate a leakage path from acting as a feed channel spiral channel 28 to the
  • Leakage paths are at least substantially avoided.
  • Multi-segment insert 36 '"sealing elements 94 may be arranged.
  • FIG. 10 shows, with reference to a further embodiment of an exhaust-gas turbocharger 10 v, a further possibility of holding and pressing in a multi-segment insert 36 IV of the exhaust-gas turbocharger 10 in its turbine housing 14 of the turbine 12.
  • the multi-segment insert 36 IV is, for example, the
  • Multi-segment insert 36 IV also has the spiral channels 38, 40, 42 and 44 and the same function as the multi-segment insert 36.
  • the bearing housing 16 is supported on the turbine housing 14 via respective contact surfaces 74 ".
  • the plate spring 75 is arranged, which is thus supported on the one hand on the multi-segment insert 36 I and on the other hand on the bearing housing 16.
  • the plate spring 75 is biased so that this pushes the multi-segment insert 36 I in the axial direction according to the directional arrow 80 against the turbine housing 14, so that the spiral channels 38, 40, 42 and 44 tightly through the turbine housing 14 are covered.
  • a force acts on the bearing housing 16 according to the direction arrow 80, which, for example, by screwing the bearing housing 16 with the
  • Turbine housing 14 is effected by means of several screws, so that the
  • Bearing housing 16 is pressed against the turbine housing 14 via the contact surfaces 74 ".
  • plate spring 75 for example in the exhaust gas turbochargers 10, 10 "and 10 1 " and in the axial direction between the bearing housing 16 and the lid 86 and / or between the lid 86 and the corresponding
  • Possible leakage paths are also indicated in FIG. 10 by the directional arrows 88 and 90, which are characterized by the particularly firm holding and pressing in of the
  • the plate spring 75 has the advantage that, even with thermal expansion of the assembly of the turbine housing 14, the multi-segment insert 36, 36 ', 36 ", 36'", 36 IV , the bearing housing 16 and optionally the lid 86 at least almost always the multi-segment insert 36, 36 ', 36 ", 36'", 36 IV at least indirectly acted upon by a desired high force to the spiral channels 38, 40, 42 and 44, for example, by the turbine housing 14 and / or the cover 86 tight cover.
  • the exhaust gas turbocharger 10 VI comprises a multi-segment insert 36 v , which may be, for example, the multi-segment insert 36 I or 36 '. Also, the multi-segment insert 36 v has the spiral channels 38, 40, 42 and 44 and the same function as the multi-segment inserts 36 IV and 36 '.
  • the intermediate space 92 is fluidically connected to the spiral channel 28 acting as a feed channel.
  • a plurality of through holes 96 here provided in the form of a bore, of which a through hole 96 is shown as representative in FIG. 11. Because of this fluidic connection prevails in the intermediate space 92, at least substantially the same pressure as in the spiral channel 28. This particular static pressure in
  • Gap 92 is greater than a total applied static pressure in the individual spiral channels 38, 40, 42, 44 of the multi-segment insert 36 v .
  • This pressure difference acts on corresponding surfaces of the wall 72 a force F on the multi-segment insert 36 v , which is directed at least substantially in the axial direction according to the direction arrow 49 in the direction of the turbine housing 14 according to the directional arrow 80.
  • the multi-segment insert 36 v is pressed against the turbine housing 14 of the turbine 12 via the contact surfaces 76 and pressed into it, so that the spiral channels 38, 40 and 42 and 44 are at least substantially separated by the
  • Turbine housing 14 are covered.
  • the lid 86 can also be subjected to the force F in order to at least substantially cover the spiral channels 38, 40, 42 and 44. This is a particularly advantageous method of at least substantially preventing any leaks, such as the leakage paths indicated by the directional arrows 88 and 90.
  • FIGS. 12 and 13 show another alternative embodiment of the invention
  • Exhaust gas turbocharger 10 according to the exhaust gas turbochargers 10, 10 1 , 10 “, 10 1 ", 10 IV , 10 v and 10 VI .
  • the exhaust gas turbocharger 10 v includes a multi-segment insert 36 I , which is for example the multi-segment insert 36 or 36 '".
  • the adjusting device 56 comprises, in addition to the adjusting ring 66 and the tongues 58, 60, 62 and 64, an adjusting wheel 98, an adjusting shaft 100 and an adjusting lever 102.
  • the adjusting ring 66 and the adjusting wheel 98 are provided with respective toothings 104 and 106, which within the turbine housing 14 of the turbine 12 of the
  • Exhaust gas turbocharger 10 "are arranged and engaged with each other
  • Adjusting wheel 98 is rotatably connected to the adjusting shaft 100 which is rotatably held about a rotational axis 108 in the bearing housing 16.
  • the adjusting shaft 100 which is rotatably held about a rotational axis 108 in the bearing housing 16.
  • the adjusting lever acts with an actuator of Exhaust gas turbocharger 10 together, which is, for example, a vacuum box, an electric motor to another actuator or the like.
  • the actuator can move the adjusting lever 102 in accordance with a directional arrow 110, in particular rotate, resulting in a rotation of the adjusting shaft 100 about the axis of rotation 108 according to a directional arrow 112.
  • Nozzle cross section A R is or will be set. This adjustment over the
  • Gears 104 and 106 has the advantages that particularly high
  • thereby one over the Verstellwinkel Scheme harmonic Translation starting from a displacement angle of the actuator to a displacement of the Verstellrads 66 (tongue slide) achieve.

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  • 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)
  • Control Of Turbines (AREA)

Abstract

L'invention porte sur un élément rapporté (36, 36I, 36II, 36III, 36IV, 36V, 36VI) pour une turbine (12) d'un turbocompresseur à gaz d'échappement (10, 10I, 10II, 10III, 10IV, 10V, 10VI, 10VI), qui peut être inséré au moins par endroits dans un corps (14) de la turbine (12) et qui présente, au moins un canal en spirale (38, 40, 42, 44) s'étendant dans la direction circonférentielle (48) de l'élément rapporté (36, 36I, 36II, 36III, 36IV, 36V, 36VI) au moins par endroits sur la circonférence, et qui peut être parcouru par les gaz d'échappement qui traversent la turbine (12), ledit élément étant ouverte au moins par endroits dans la direction axiale (49) sur au moins un côté frontal (82, 84) de l'élément rapporté (36, 36I, 36II, 36III, 36IV, 36V, 36VI).
PCT/EP2011/005309 2010-11-13 2011-10-21 Elément rapporté pour une turbine d'un turbocompresseur à gaz d'échappement, turbocompresseur à gaz d'échappement ainsi que turbine pour un turbocompresseur à gaz d'échappement WO2012062407A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
JP2013538088A JP6025737B2 (ja) 2010-11-13 2011-10-21 排気ガスターボチャージャーのタービン、排気ガスターボチャージャー、排気ガスターボチャージャー用のタービンのための挿入部品
US13/893,278 US20130330178A1 (en) 2010-11-13 2013-05-13 Insert element for a turbine of an exhaust gas turbocherger, exhaust gas turbocharger and turbine for an exhaust gas turbocharger

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102010051359.8 2010-11-13
DE102010051359A DE102010051359A1 (de) 2010-11-13 2010-11-13 Einsatzelement für eine Turbine eines Abgasturboladers, Abgasturbolader sowie Turbine für einen Abgasturbolader

Related Child Applications (1)

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US13/893,278 Continuation-In-Part US20130330178A1 (en) 2010-11-13 2013-05-13 Insert element for a turbine of an exhaust gas turbocherger, exhaust gas turbocharger and turbine for an exhaust gas turbocharger

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WO2012062407A1 true WO2012062407A1 (fr) 2012-05-18

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US (1) US20130330178A1 (fr)
JP (1) JP6025737B2 (fr)
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DE112015004613T5 (de) * 2014-10-08 2017-06-22 Borgwarner Inc. Turbolader mit variabler Turbinengeometrie mit einer Stromsteuervorrichtung mit fixierten Schaufeln
US10526954B2 (en) * 2015-08-06 2020-01-07 Garrett Transportation I Inc. Turbocharger assembly
DE202018101699U1 (de) * 2018-03-27 2019-07-02 Borgwarner Inc. Turbine mit Verstellring
DE102018221554A1 (de) * 2018-12-12 2020-06-18 BMTS Technology GmbH & Co. KG Abgasturbolader

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WO2015022592A1 (fr) * 2013-08-16 2015-02-19 Wescast Industries, Inc. Carter de turbine
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US20130330178A1 (en) 2013-12-12
JP6025737B2 (ja) 2016-11-16
DE102010051359A1 (de) 2012-05-16

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