WO2012126493A1 - Turbine pour un turbocompresseur sur gaz d'échappement - Google Patents

Turbine pour un turbocompresseur sur gaz d'échappement Download PDF

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Publication number
WO2012126493A1
WO2012126493A1 PCT/EP2011/006095 EP2011006095W WO2012126493A1 WO 2012126493 A1 WO2012126493 A1 WO 2012126493A1 EP 2011006095 W EP2011006095 W EP 2011006095W WO 2012126493 A1 WO2012126493 A1 WO 2012126493A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
adjusting device
exhaust gas
turbine wheel
adjusting
Prior art date
Application number
PCT/EP2011/006095
Other languages
German (de)
English (en)
Inventor
Nils Brinkert
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 JP2014500259A priority Critical patent/JP2014511962A/ja
Publication of WO2012126493A1 publication Critical patent/WO2012126493A1/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
    • 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
    • F01D17/143—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 the shiftable member being a wall, or part thereof of a radial diffuser
    • 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 a turbine for an exhaust gas turbocharger specified in the preamble of claim 1. Art.
  • exhaust gas turbocharger with a turbine driven by exhaust gas of the internal combustion engine.
  • the turbine can have at least one adjusting device, which
  • the turbine is arranged for example in the flow direction of the exhaust gas upstream of a turbine wheel of the turbine and by means of which flow conditions in particular upstream of the turbine wheel can be influenced.
  • the turbine can be adapted to a variety of different operating points of the internal combustion engine, so that the turbine so that the internal combustion engine particularly efficient, that can be operated with low fuel consumption and thus low C0 2 emissions.
  • the adjusting device thus represents a variability, which allows an advantageous thermodynamic adaptation of the turbine to an operating point. With this variability, there are possibilities of acting on the so-called degree of reaction of the turbine, which is a main variable for a
  • WO 2006-133838 A1 discloses an exhaust gas turbine in an exhaust gas turbocharger, with a turbine wheel rotatably mounted in a housing, via an inlet flow Exhaust gas can be supplied, which can be discharged via an outlet channel from the exhaust gas turbine.
  • the exhaust gas turbine has a turbine inlet cross section, which is formed in the transition from the inlet flow to the turbine between two lateral boundary walls and in which a guide grid and cooperating with the guide grid, are arranged in the axial direction adjustable axial slide, wherein one of
  • Turbine inlet cross-section is mounted fixed to the housing, that the axial slide is arranged on the side facing the outlet channel and that the outlet channel facing away from the outlet, the housing-fixed boundary wall of the turbine inlet cross-section axially flush with the turbine blades of the turbine wheel.
  • the known turbines with a corresponding adjusting device have further potential to reduce their space requirement. In addition, they have further potential to make the operation more efficient.
  • Such a turbine for an exhaust gas turbocharger comprises a turbine housing and a turbine wheel.
  • the turbine wheel is at least partially received in the turbine housing and rotatable about an axis of rotation.
  • the turbine wheel has at least one at least one leading edge and at least one trailing edge
  • Impeller blade which can be flowed over by the leading edge for driving the turbine wheel of the turbine housing by flowing exhaust gas and can be flowed off via the trailing edge of the exhaust gas.
  • an adjusting device is provided, by means of which the
  • the adjusting device of the turbine according to the invention which is, for example, a radial turbine, makes it possible for the turbine to meet a large number of different requirements as required and in a particularly large operating range
  • a turbine associated with the unit in particular an internal combustion engine or a fuel cell, from the exhaust gas, the turbine is driven to adapt. This is accompanied by a more efficient operation of the turbine and thus of the unit, so that the unit can be operated with low energy consumption. For example, if the unit is the
  • the turbine according to the invention in which the adjusting device is arranged, for example, at least partially downstream of the turbine wheel, a reduced space requirement, which contributes to the avoidance and solution of package problems, especially in a space-critical area such as an engine compartment of a motor vehicle.
  • the turbine according to the invention may be due to the corresponding
  • Arrangement and design of the adjusting device are made particularly small in terms of their weight, which keeps the weight of the motor vehicle low. This results in a more efficient operation of the unit, by means of which the motor vehicle is driven, for example. Furthermore, the flow conditions in the
  • Turbinenradaustritts Symposium be set particularly advantageous by the rotatable about the axis of rotation adjusting device, resulting in a more efficient operation of the turbine according to the invention.
  • the adjusting device of the turbine according to the invention provides a
  • Turbine wheel outlet variability is, which has only a small number of parts and thus a low complexity, which is associated with a high functional performance security. This is the life of the adjusting device and thus the entire turbine benefit.
  • the adjusting device is particularly mechanically reliable and has only a very low cost.
  • a throughput of the turbine is variably adjustable by the discharge edge fluidly released or, in contrast, at least partially fluidly blocked.
  • a particularly large throughput spread of the turbine can thus be represented so that the turbine can be adapted to a large number of different operating points of the unit assigned to it.
  • the turbine and its associated unit can be operated more efficiently.
  • At low speed and load ranges can be adjusted by the adjusting a relatively high Maustau Sign with only a small flow rate parameter, while at high speed and load ranges of the internal combustion engine, a contrast high flow rate parameter is adjustable with only a small Aufstau Titan.
  • the turbine also has a reduced space requirement and only a very small weight, since the adjusting device is arranged space-saving.
  • the adjusting device is rotatable about the axis of rotation of the turbine wheel and at least partially, in particular completely, tts Suite arranged in the Turbinenradaust.
  • flow conditions in the turbine wheel outlet region can be variably adjusted. This keeps the space requirement turbine particularly low.
  • the turbine has thereby a high robustness against mechanical and / or thermal loads, which is associated with a very good functional performance safety even over a long service life,
  • a contour of the turbine wheel By releasing and obstructing the trailing edge, a contour of the turbine wheel can be varied and thus an outflow surface of the turbine wheel, via which the turbine can be flowed from the exhaust gas, variably adjusted and thus adapted to different operating points.
  • the turbine throughput parameter can be
  • the turbine thus has an optimized operating range by adjusting the degree of reaction due to the adjustability of the flow rate parameter. Furthermore, there are turbine efficiency advantages and improved charge pressure build-up by a associated with the turbine and driven by this compressor for compressing the aggregate air to be supplied and a concomitant lower
  • a further adjusting device which is arranged at least partially in a turbine wheel inlet region, is provided by means of which flow conditions in the turbine wheel inlet region upstream of the turbine
  • Turbine are variably adjustable. As a result, a fully variable turbine is created, which can be adapted particularly advantageous and in a particularly large range of different operating points. This leads to a particularly efficient and thus low-energy consumption, especially low fuel consumption, operation of the unit associated with the turbine, which is associated with low C0 2 emissions.
  • the further adjusting device comprises, for example, a locking body
  • VersperrSystem is connected for example with an adjusting ring, which is about the axis of rotation of the
  • Turbine is rotatable and over which the VersperrAvem for variable adjustment of the effective flow cross-section movable, in particular rotatable.
  • the turbine according to the invention is thus designed as a so-called tongue slider turbine, which is particularly flexible adaptable to different operating points and has a low complexity, which benefits the functional performance and thus the reliability of the turbine.
  • the first and the further adjusting device are coupled together and, in particular, only actuated by an actuator of the turbine common to the adjusting devices, in particular can be moved.
  • the coupling of the adjusting devices thus makes it possible to use only one actuator, for example an actuator, in particular an electric motor, to adjust the adjusting devices for setting the effective
  • Variability in the turbine wheel inlet region allows full variability of a flow rate and reaction characteristics of the turbine according to the invention and thus a particularly good possibility of influencing the efficiency curve.
  • This full variability is in the turbine of the invention with particularly simple and inexpensive means in the form of the tongue slider as the further adjusting device and the first
  • the adjusting devices are, for example, electrically and / or pneumatically and / or hydraulically and / or mechanically coupled to each other.
  • the electrical coupling has the advantage that this reacts very quickly to changing operating points of the unit associated with the turbine and the adjusting devices can be adjusted accordingly quickly. Furthermore, this represents a particularly cost-effective coupling.
  • the pneumatic and / or hydraulic coupling has the advantage that particularly high actuating forces can be achieved by contrast with particularly low actuation forces, in order to set the effective flow cross section and / or to free or obstruct the trailing edge or the
  • the mechanical coupling has the advantages of particularly low cost and a particularly high robustness and reliability, what the high
  • the guide vane of the turbine wheel has an outer contour with at least one substantially parallel to the axis of rotation extending length range as the leading edge and with a substantially radially extending length range as the trailing edge, wherein extending between the substantially parallel to the axis of rotation Length range and a further wavelength range is provided as a further trailing edge said substantially radially extending length range at least, which includes ⁇ ⁇ with the rotation axis an angle which is in the range 20 ° ⁇ ⁇ ⁇ 90 0th
  • the at least substantially radially extending trailing edge (length range) provides a
  • the further outflow edge represents a Mauabström edge, which is at least partially fluidly releasable by means of the first adjusting device and in contrast at least fluidly locked. This is the
  • Outflow edge at least partially covered or covered by the first adjusting device said cover or cover is variably adjustable, thus more or less free or block the trailing edge.
  • the angle a "or the corresponding angular range represents a very significant possibility of influencing the optimization of the turbine wheel, since through the angle ⁇ ⁇ both throughflow conditions and in particular outflow conditions of the turbine wheel can be influenced. Accordingly, extremely favorable throughflow conditions are present in said angular range, by means of which the turbine wheel permits a particularly efficient and efficient operation of the turbine and thus of the turbine associated with the unit.
  • Verstellell issues fluidly releasable and in contrast fluidly at least in
  • Adjustment device is more or less covered or covered, for example, only the further trailing edge and not the first trailing edge is fluidically releasable or in contrast fluidly blocked.
  • first trailing edge by means of the first adjusting device fluidly releasable and fluidly lockable, wherein advantageously the further trailing edge relative to the first trailing edge predominantly by means of the first adjusting device correspondingly adjustable, that is fluidically releasable and in contrast fluidly lockable, is.
  • first adjusting device comprise a first adjusting element which is rotationally fixed relative to the turbine housing, in particular a first adjusting ring, and at least one second adjusting element which can rotate about the axis of rotation relative to the first adjusting element, In particular, a second adjusting ring, this is a particularly uncomplex, cost-effective and reliable way created to adjust the flow conditions in the turbine wheel outlet, for example, the trailing edge is fluidly blocked by covering or releasing or released in contrast.
  • the first adjustment device has, for example, an adjustment range, in particular an adjustment angle range, with a first end position and a second end position.
  • the first adjusting device is movable in the adjustment range between the end positions, in particular rotatable about the axis of rotation.
  • the first adjusting device is movable in the end positions and in at least one intermediate position in the adjustment between the end positions.
  • the first adjusting device in the adjustment is continuously adjustable, whereby a plurality of different positions of the first adjusting device can be displayed in order to adapt the turbine particularly favorable to different operating points can. It is also possible to adjust the first adjusting device stepped in the adjustment, which is associated with particularly low cost of the turbine.
  • the first adjusting device in an adjustment range of 20 0 adjustable about the rotational axis, that is, the first adjusting device an adjustment angle of 20 °, so this is advantageous in that the turbine can be more easily and inexpensively adapted to different operating points, while simultaneously The space requirement of the turbine and their costs can be kept low.
  • Fig. 1 is a schematic diagram of an internal combustion engine with a
  • Exhaust gas turbocharger which one of exhaust gas of the internal combustion engine flow-through turbine comprising a rotatable about an axis of rotation of a turbine wheel of the turbine and at least partially disposed downstream of the turbine wheel in a turbine wheel outlet region
  • Has adjustment means by means of which flow conditions, in particular in the Turbinenradauseries Complex are variably adjustable;
  • FIG. 3 shows a detail of a schematic sectional view of the turbine according to FIG.
  • FIG. 2 Fig. 2 along a section line A-B shown in FIG. 2.
  • Fig. 1 shows a trained as a reciprocating engine
  • Internal combustion engine 10 which is designed for example as a diesel engine, gasoline engine, diesel engine or other internal combustion engine.
  • the internal combustion engine 10 is used, for example, a motor vehicle,
  • Internal combustion engine 10 can be supplied with fuel, which at least one combustion chamber, in particular a cylinder, the internal combustion engine 10 is supplied.
  • the combustion chamber of the internal combustion engine 10 is also supplied with air, which sucks the internal combustion engine 10 from the environment, which is indicated by a directional arrow 12.
  • Internal combustion engine 10 arranged air filter 16, whereby the air is purified. Following the air filter 16, the air by means of appropriate
  • Intake piping passed to a arranged in the intake manifold 14 compressor 20 of an exhaust gas turbocharger 22, which is indicated by a directional arrow 18 in FIG. 1.
  • the air is compressed by means of a compressor wheel of the compressor 20, whereby it is heated.
  • a charge air cooler 24 is arranged in the intake tract 14 downstream of the compressor 20, which is flowed through by the compressed air and which cools the compressed air, before finally fed to the at least one combustion chamber of the internal combustion engine 10 by means of Ansaugverrohrung becomes. This is represented by a directional arrow 26.
  • Auto-ignition ignites or is ignited by means of an ignition device and thereby burns.
  • the combustion results in an exhaust gas, which flows out of the combustion chamber and flows into exhaust gas piping of an exhaust tract 28 of the internal combustion engine 10, which is indicated by a directional arrow 30.
  • the exhaust gas is passed to a turbine 32 of the exhaust gas turbocharger 22, which is drivable by the exhaust gas.
  • the turbine 32 in this case comprises a turbine housing 76 (FIG. 2), in which a turbine wheel 74 is rotatably received about an axis of rotation.
  • the turbine wheel 74 is rotatably connected to a shaft 34 of the exhaust gas turbocharger 22 and acted upon by the exhaust gas and thereby driven.
  • the compressor wheel of the compressor 20 is also rotatably connected, so that the compressor wheel and thus the compressor 20 can be driven by the turbine wheel 74 and the turbine 32.
  • a branch point 36 is arranged in the exhaust tract 28, which a
  • Exhaust gas recirculation device 38 is assigned. At the branch point 36 is a
  • Exhaust gas recirculation line 40 of the exhaust gas recirculation device 38 fluidly with the
  • Exhaust piping of the exhaust tract 28 connected.
  • the exhaust gas recirculation line 40 is fluidly connected to the intake passages of the intake tract 14 at an introduction point 42.
  • exhaust gas from the exhaust tract 28 to the intake tract 14 can be traced and introduced into the intake tract 14.
  • Combustion engine 10 acted upon, so that nitric oxide and
  • Particle emissions of the internal combustion engine 10 can be kept low.
  • the exhaust gas recirculation device 38 comprises an exhaust gas recirculation valve 44 which is located in the exhaust gas recirculation valve 44
  • Exhaust gas recirculation line 40 is arranged and by means of which a flow cross-section, which is traversed by the recirculated exhaust gas, is variably adjustable.
  • an exhaust gas recirculation cooler 46 is disposed in the exhaust gas recirculation line 40 between the inlet 42 and the branch point 36 downstream of the exhaust gas recirculation valve 44, by means of which to be recirculated exhaust gas to cool. Since the branch point 36 is located upstream of the turbine 32, a high-pressure exhaust gas recirculation is shown, by means of which particularly large amounts of exhaust gas are traceable.
  • the internal combustion engine 10 includes a control device 48, by means of which the internal combustion engine 10 and the exhaust gas recirculation valve 44 can be regulated, which is indicated by arrows 50 and 52 in FIG. 1.
  • the turbine 32 has an adjusting device 54, which is arranged in the flow direction of the exhaust gas through the turbine 32 at least partially upstream of the turbine wheel 74. Furthermore, the turbine 32 comprises an adjusting device 56, which is arranged in the flow direction of the exhaust gas through the turbine 32 at least partially downstream of the turbine wheel 74.
  • flow conditions upstream and downstream of the turbine wheel 74 are variably adjustable, so that the turbine 32 can be adapted to a plurality of different operating points of the internal combustion engine 10. In this way, the turbine 32 is particularly efficient and efficient operation operable, which is associated with efficient operation of the internal combustion engine 10. This results in a particularly low fuel consumption and thus low CO 2 emissions of
  • the adjusting devices 54 and 56 are coupled to one another by means of a coupling device 58, so that the adjusting devices 54 and 56 can be actuated only by means of an actuator which is common to the adjusting devices 54 and 56.
  • the coupling device 58 comprises an actuating part 60, which can interact with the actuator, for example an electric motor.
  • the actuating part 60 is for example rotatable by means of the actuator, which is indicated by a directional arrow 62, and / or by means of the actuator translationally movable, which is indicated by a directional arrow 64.
  • An arrow 66 indicates that the actuator can be regulated by means of the control device 48 so as to be able to adapt the turbine 32 as needed to a present operating point of the internal combustion engine 10.
  • the exhaust aftertreatment device 68 comprises for example, a catalyst, in particular an oxidation catalyst, and a particulate filter, by means of which the exhaust gas is purified before it is discharged to the environment, which is represented by a directional arrow 72.
  • the adjusting device 54 of the turbine 32 is, for example, a so-called tongue slide, which has an adjusting ring which is arranged around an axis of rotation
  • the axis of rotation 73 is also the compressor wheel and the turbine wheel
  • the compressor wheel, the turbine wheel 74 and the shaft 34 rotate about the rotation axis 73 during operation of the exhaust gas turbocharger 22.
  • At least one so-called tongue is connected to the adjusting ring, which is rotatable about the adjusting ring about the axis of rotation 73 and by means of which an effective
  • Flow cross-section upstream of the turbine wheel 74 is variably adjustable.
  • the adjusting device 56 is designed for example as a so-called rotary valve, which is explained in conjunction with FIGS. 2 and 3.
  • Adjusting device 56 is a Radaustrittsquerrough the turbine wheel 74 variably adjustable.
  • FIG. 2 it comprises a rotary slide valve
  • Turbine housing 76 and to the turbine wheel 74 about the rotation axis 73 is rotatable. Furthermore, the adjusting device 56 comprises an adjusting ring 80 which is fixed relative to the housing 76.
  • the turbine wheel 74 has a plurality of impeller vanes 82, which in
  • Circumferential direction of the turbine wheel 74 which is indicated by a directional arrow 84, are arranged distributed uniformly over the circumference of the turbine wheel 74.
  • the impeller vanes 82 have an outer contour 86 which has a first longitudinal region 88 extending at least substantially parallel to the axis of rotation 73. Through the length region 88, a leading edge 90 of the impeller blade 82 is formed, via which the guide vane 32 for driving the turbine wheel 74 can be flowed by the exhaust gas.
  • the exhaust gas is supplied via an annular nozzle 92 turbine wheel 74.
  • the outer contour 86 has a length region 94, through which an outflow edge 96 of the impeller blade 82 is formed.
  • the trailing edge 96 is the impeller blade 82 and the impeller blades 82 of the exhaust gas abströmbar.
  • the length region 94 and thus the trailing edge 96 extend at least substantially in the radial direction of the turbine wheel, which is indicated by a directional arrow 98. The at least substantially extending in the radial direction
  • Length range 94 may, for example, include an angle with the axis of rotation 73 that is within a range of 80 degrees to and including 00 degrees.
  • a length range 100 is provided between the length regions 88 and 94, which adjoins the length region 88 and to which the length region 94 of the impeller blade 82 connects.
  • a further outflow edge 102 of the impeller blade 82 is formed, via which the
  • Turbine 74 and the impeller blade 82 can be flowed from the exhaust gas.
  • the length region 100 and thus the trailing edge 102 include, for example with the rotation axis 73 at an angle a ", which is for example greater than 20 degrees and less than or at least substantially equal to 90 degrees.
  • a " is for example greater than 20 degrees and less than or at least substantially equal to 90 degrees.
  • the adjusting ring 78 comprises cover elements 104, by means of which the respective
  • the adjusting ring 78 can be rotated in a respective end position about the axis of rotation 73 according to a directional arrow 106.
  • the adjusting ring 78 in a plurality of
  • Abströmkanten 102 of the impeller blades 82 at least partially release or partially cover or cover. Due to the different positions of the adjusting ring 78, it is possible different
  • Adjustment device 54 is given.
  • the turbine 32 is designed as a fully variable turbine 32, which is particularly flexible at different operating points of the internal combustion engine 10
  • Turbine wheel exit area 108 illustrated by a variability only very small space requirement, whereby the entire turbine 32 and thus the entire exhaust gas turbocharger 22 have only a very small space requirement, in particular in the axial direction. Furthermore, the complexity of this and number of parts, the weight and the costs are kept low by the trained as a rotary valve adjusting device 56, which contributes to a high functional performance security of the turbine 32.
  • FIG. 3 shows one of the end positions of the adjusting ring 78, in which the outflow edges 102 of the impeller blades 82 are completely fluidically released.
  • the turbine 32 In this end position designed as an open position, the turbine 32 has a maximum throughput parameter.
  • Outflow edges 102 at least substantially completely covered or covered and thus at least substantially completely fluidly blocked, so a minimum flow rate parameter of the turbine 32 is shown.
  • the turbine 32 then has a particularly high Aufstau Titan, which is an efficient operation especially at low load and / or speed ranges of the internal combustion engine 10 beneficial.
  • the representation of the high throughput parameter is conducive to efficient operation of the turbine 32 at high load and / or speed ranges.
  • Circumferential direction (directional arrow 84) spaced from each other and arranged distributed over the circumference of the turbine wheel 74 at least substantially evenly.
  • a respective flow channel 1 12 is formed, which is at least partially possible in positions of the adjusting ring 78, in which an outflow of the exhaust gas from the impeller blades 82 via the trailing edges 102, is flowed through by the exhaust gas.
  • the flow-through channels 102 are, for example, of diffuser-like design, so that they represent diffuser channels.
  • diffuser channels 102 are, for example, of diffuser-like design, so that they represent diffuser channels.
  • Flow channels 1 12 have a respective outflow edge 1 14, which is very thin.
  • Internal combustion engine 10 can be adjusted.
  • a contour of the turbine wheel 74 is set variably, and trailing edges 102 are added or removed, so that outflow areas are increased or decreased.
  • the turbine has a particularly high throughput spread, whereby they both in low speed and / or
  • Load ranges and in high speed and / or load ranges and also in between speed and / or load ranges can be operated efficiently.
  • the adjusting device 56 has nine so-called Versperrsektoren, which are formed by the cover 102.
  • the adjusting ring 78 is in one
  • Adjusting angle range of 20 degrees adjustable This means that it can be rotated relative to the directional arrow 84 by 20 degrees in total relative to the adjusting ring 80. This allows complete coverage and complete release of the trailing edges 102. In the full release position, a maximum cross-sectional aperture of 50% of the projected annular area is achieved, as shown in FIG. In this position, the turbine 32 has a maximum possible flow cross section over the flow edges 102.
  • the fixed adjusting ring 80 is formed with a relatively small thickness, so sector pockets 1 16 over the trailing edge 102 do not make too large loss sources for the flow of the exhaust gas.
  • FIGS. 2 and 3 Refinements, not shown, are possible in FIGS. 2 and 3, in which the cover elements 104 or corresponding locking surfaces of the adjusting ring 78 are increasingly immersed in the free sector pockets 16 by a particularly small axial movement when the adjusting ring 78 is rotated Position in which the outflow edges 102 are completely covered, interference edges for slit flows of the outflow edges 102 and the outer contour 86 are at least substantially avoided.
  • the turbine 32 according to FIG. 2 does not comprise an adjusting device arranged at least partially upstream of the turbine wheel 74, such as FIG
  • Adjusting means 54 for variably setting the flow conditions upstream of the turbine wheel 74. It is understood, however, that such adjusting means as the adjusting means 54 may be provided to variably adjust the flow conditions at least substantially upstream of the turbine wheel 74.
  • the turbine 32 is assigned to the internal combustion engine 10. It is understood, however, that the turbine 32 can also be associated, for example, with a fuel cell, wherein the turbine 32 or the turbine wheel 74 can then be driven by the exhaust gas of the fuel cell and the turbine 32 can then be adapted to different operating points of the fuel cell in a particularly efficient and flexible manner. Furthermore, the turbine 32 can be assigned to other exhaust-emitting units and can be driven by the exhaust gas of these units.

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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 une turbine (32) pour un turbocompresseur sur gaz d'échappement (22), comprenant un carter de turbine (76) et une roue de turbine (74) qui est contenue au moins par endroits dans le carter de turbine (76), qui peut tourner autour d'un axe de rotation (73) et qui présente au moins une aube de rotor (82) présentant au moins un bord d'attaque (90) et au moins un bord de fuite (96, 102). Pour l'entraînement de la roue de turbine (74), cette aube peut être attaquée au bord d'attaque (90) et en sortant au bord de fuite (96, 102) par les gaz d'échappement qui traversent le carter de turbine (76). Ladite turbine comporte également un dispositif de redressement (56) au moyen duquel le bord de fuite (96, 102) de l'aube de rotor (82) de la roue de turbine (74) peut être dégagé fluidiquement au moins par endroits dans une première position et, au contraire, occulté fluidiquement au moins par endroits et au moins sensiblement en totalité dans au moins une deuxième position du dispositif de redressement (56).
PCT/EP2011/006095 2011-03-19 2011-12-06 Turbine pour un turbocompresseur sur gaz d'échappement WO2012126493A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2014500259A JP2014511962A (ja) 2011-03-19 2011-12-06 排気ターボチャージャのタービン

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE201110014458 DE102011014458A1 (de) 2011-03-19 2011-03-19 Turbine für einen Abgasturbolader
DE102011014458.7 2011-03-19

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WO2012126493A1 true WO2012126493A1 (fr) 2012-09-27

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DE (1) DE102011014458A1 (fr)
WO (1) WO2012126493A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012023408B4 (de) * 2012-11-30 2016-12-29 Siegfried Sumser Turbine für einen Abgasturbolader und Verbrennungsmaschine, insbesondere für Kraftwagen

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3355878A (en) * 1965-08-30 1967-12-05 Birmann Rudolph Turbocompressor system
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WO2006105804A1 (fr) * 2005-04-04 2006-10-12 Honeywell International Inc. Turbocompresseur a debit variable
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