WO2012136234A1 - Turbine pour un turbocompresseur sur gaz d'échappement, ainsi que moteur à combustion interne équipé d'une telle turbine - Google Patents

Turbine pour un turbocompresseur sur gaz d'échappement, ainsi que moteur à combustion interne équipé d'une telle turbine Download PDF

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Publication number
WO2012136234A1
WO2012136234A1 PCT/EP2011/006094 EP2011006094W WO2012136234A1 WO 2012136234 A1 WO2012136234 A1 WO 2012136234A1 EP 2011006094 W EP2011006094 W EP 2011006094W WO 2012136234 A1 WO2012136234 A1 WO 2012136234A1
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WO
WIPO (PCT)
Prior art keywords
turbine
exhaust gas
internal combustion
combustion engine
flow
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/EP2011/006094
Other languages
German (de)
English (en)
Inventor
Siegfried Sumser
Thomas Streule
Paul Löffler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mercedes Benz Group AG
Original Assignee
Daimler AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Daimler AG filed Critical Daimler AG
Publication of WO2012136234A1 publication Critical patent/WO2012136234A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/02—Gas passages between engine outlet and pump drive, e.g. reservoirs
    • F02B37/025—Multiple scrolls or multiple gas passages guiding the gas to the pump drive
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
    • 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
    • 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

  • the invention relates to a turbine for an exhaust gas turbocharger
  • EP 1 866 534 B1 discloses a turbocharger with a variably adjustable
  • the turbocharger further includes an inlet passage arranged to introduce exhaust gas into the turbine chamber around the turbine chamber.
  • the at least one wall component has a movable
  • Wall member whose position is adjustable relative to the turbine to change the geometry of the turbine chamber. It is further provided that the position of the movable wall member is adjustable to expose a diameter of the turbine on an outlet side of the turbine, whereby the surface and thus the
  • Patent claim 9 solved.
  • Advantageous embodiments with expedient and non-trivial developments of the invention are specified in the remaining claims.
  • Such a turbine for an exhaust gas turbocharger of an internal combustion engine comprises a turbine housing through which exhaust gas of the internal combustion engine can flow.
  • a turbine housing In the turbine housing is a turbine wheel about an axis of rotation relative to the
  • Turbine housing rotatably received at least partially.
  • a receiving space is at least partially limited by the turbine housing, for example, in which, the turbine wheel is arranged at least partially.
  • Turbine housing has at least two, each of at least a portion of the exhaust gas flowed through and at least partially fluidly separated flooding.
  • the floods are, for example, by an intermediate wall, which by the
  • Turbine housing are formed, fluidly separated from each other and divided from each other.
  • Each of the floods is associated with at least one nozzle via which the exhaust gas flowing through the respective flood is supplied to the exhaust gas for supplying the turbine wheel with exhaust gas
  • the respective nozzles are, for example, on the one hand by a wall of the
  • Turbine housing and on the other hand by the intermediate wall (which may also be formed by the turbine housing) limited.
  • At least one first of the nozzles which are also referred to as partial nozzles, is associated with a first adjusting device.
  • a flow cross-section through which the exhaust gas flowing through the exhaust gas flowing through the first nozzle is variably adjustable.
  • the first adjusting device which for example is associated with at least one first adjusting element
  • the first adjusting element for example, relative to the turbine housing or relative to the first nozzle movable.
  • a second, at least partially disposed in a turbine wheel outlet region of the turbine wheel adjusting device is provided, by means of which
  • the second adjusting device comprises, for example, at least one second adjusting element, which is movable relative to the turbine housing at least partially in the turbine wheel outlet region, in particular rotatable about an axis of rotation and / or translationally movable in the axial direction of the turbine.
  • the first adjusting element can be rotatably and / or translationally movable in the axial direction of the turbine for variably setting the flow cross section of the first nozzle about an axis of rotation.
  • the adjusting means is a Turbinenradeinlingersvariabiltician in the form of the first adjusting device and a Turbinenradauseriesvariabiltician in the form of the second
  • the turbine according to the invention is adaptable to different operating points and exhaust gas mass flows of the internal combustion engine as required.
  • the turbine according to the invention can be adapted to at least substantially every operating point of the internal combustion engine in its entire map.
  • the turbine according to the invention can be operated particularly efficiently, which results in efficient operation of the turbine
  • Combustion engine is accompanied.
  • the fuel consumption and the C0 2 - emissions of the internal combustion engine can be kept very low.
  • an inlet pressure level of the turbines is optionally increased by a back pressure of an exhaust aftertreatment device, in particular a soot filter, whereby the geometry and in particular the dimensions of the turbines are again designed to smaller values in order to meet performance requirements for a compressor performance on the intake side.
  • a sufficient amount or mass of combustion air can be provided, so that the internal combustion engines required high
  • the turbine according to the invention makes it possible on the one hand to display a high Aufstautrust for the realization of high amounts of recirculating exhaust gas.
  • the adjusting devices offer the possibility of compensating or even overcompensating the negative effects on the turbine's efficiency associated with the geometric reduction of the turbines, so that the
  • Turbine according to the invention can be operated particularly efficiently.
  • their twin-flow design allows the representation of very high amounts of recirculating exhaust gas, so that the internal combustion engine has only very low nitrogen oxide (NO x -) and low soot emissions.
  • both flow cross sections of the nozzles and flow cross sections in the turbine wheel exit region can be quantified such that a gradient distribution of an overall gradient of the turbine is set such that at least substantially half the exergy gradient upstream of the turbine wheel is converted into speed energy.
  • the second half of the Exergiege devices is in a turbine wheel, for example, by two impeller blades of the
  • Turbine is limited, so in the relative system, in speed energy
  • the slope is divided such that upstream of the turbine wheel relative to the wheel channel, the greater Exergiebetrag the total gradient is converted into speed.
  • the degree of reaction of the turbine whose definition is the quotient of the
  • Speed conversion from the turbine wheel to the nozzle means is thus at least substantially below the turbines at least 0.5.
  • the degree of reaction at which maximum turbine efficiencies can be achieved has been in the range of. For most turbines, which are designed in particular as radial turbines
  • the turbine according to the invention makes it possible to act on the degree of reaction of the turbine from the turbine wheel side. So the throughput capability of the turbine according to the invention
  • Turbine of the invention of the turbine wheel ago increased and the turbine at high throughputs with favorable degrees of reaction and relatively low
  • the internal combustion engine with the turbine according to the invention which has the described geometry reduction, can be operated with only low fuel consumption, the turbine offering particularly good transient behavior and / or a possibility of representing large amounts of exhaust gas to be recirculated, especially at high loads.
  • the turbine makes it possible to effect a sufficient supply of air to the internal combustion engine via the corresponding drive of the compressor while driving, even at high speeds.
  • blowdown rate refers to the proportion of the total exhaust gas of the
  • Turbine is guided around, so that the turbine wheel is not driven by the exhaust gas to the turbine wheel.
  • the adjusting devices of the turbine according to the invention also have the advantage that the twin-flow turbine, in particular if the floods are formed asymmetrically to each other, for each flood quasi own own degree of reaction, which one from the side of the turbine wheel to the satisfaction of Kraftstoffvers- and
  • Fig. 1 is a schematic diagram of an internal combustion engine with a
  • twin-flow turbine which has two adjusting devices, by means of which the turbine to different operating points of
  • Internal combustion engine is variably adjustable
  • FIG. 3 in fragmentary form a schematic longitudinal sectional view of another
  • Embodiment of the turbine of FIG. 2; 4 shows a diagram with a profile of the throughput parameter of the turbine according to FIGS. 1 to 3 when adjusting one of the adjusting devices;
  • FIG. 5 shows a diagram with three profiles of the throughput parameter of the turbine according to FIGS. 1 to 3 when adjusting one of the adjusting devices.
  • FIG. 6 is a graph with three curves of the flow rate parameter of the turbine according to FIGS. 1 to 3 over the turbine pressure ratio of the turbine according to FIGS. 1 to 3.
  • Fig. 1 shows an internal combustion engine 10 with six cylinders 12 of a motor vehicle. During operation of the internal combustion engine 10, this draws in air from the environment. The air first flows through an air intake 16 in an intake tract 14 of the internal combustion engine 10, by means of which the air is purified. In the intake tract and a compressor 18 of an exhaust gas turbocharger 20 is arranged. The compressor 18 includes a rotatable about a rotation axis 22
  • Compressor 24 by means of which the sucked air is compressed.
  • a charge air cooler 26 is arranged in the intake tract 14, which cools the compressed and thus heated air again.
  • the thus compressed and cooled air flows to a charge air distributor 28 arranged in the intake tract 14, from which the compressed air is distributed to the cylinders 12 and from which the air flows into the cylinders 12.
  • the compressed air is supplied with fuel. Additionally and alternatively it can be provided that fuel is injected at least substantially directly into the cylinder 12. In any case, in the cylinders 12, there is a fuel-air mixture which is compressed by cylinders 2 received and translationally movable relative to the cylinders 12 piston and
  • the combustion of the fuel-air mixtures in the cylinders 12 results in an exhaust gas which is expelled from the cylinders 12 by the pistons.
  • the exhaust flows to arranged in an exhaust tract 34 of the internal combustion engine
  • the exhaust manifold 36 collects the exhaust gas from three of the six cylinders 12 while the exhaust manifold 38 collects the exhaust of the other three of the six cylinders 12.
  • the exhaust manifold 36 is fluidly connected via corresponding exhaust casings 40 to a first flow 42 of a turbine 44 of the exhaust gas turbocharger 20.
  • the exhaust manifold 38 is fluidly connected via respective exhaust casings 46 to a second flood 48 of the turbine 44.
  • the turbine 44 comprises a turbine housing 50, through which the floods 42 and 48 are formed.
  • the floods 42 and 48 are at least partially fluidly separated from one another by an intermediate wall 52 of the turbine housing 50.
  • Exhaust manifolds 36 and 38 the exhaust gas from three of the six cylinders 12, the flood 42 to flow through, while the exhaust gas of the other three of the cylinder 12 can flow through the flood 48.
  • the internal combustion engine 10 includes an exhaust gas recirculation device 54, which comprises a return line 56.
  • the return line 56 is on the one hand at a
  • Branching point 58 fluidly connected to the exhaust pipes 40 of the flood 42.
  • Intake tract 14 connected.
  • exhaust gas can be diverted from the three of the cylinder 12 at the branch point 58 from the exhaust pipes 40, recycled to the intake manifold 14 and introduced at the discharge point 60 in the intake manifold 14.
  • the intake air 14 flowing through the air can be acted upon with exhaust gas.
  • the nitrogen oxide (NO x ) and soot emissions of the internal combustion engine 10 can be kept low.
  • the exhaust gas recirculation device 54 comprises an exhaust gas recirculation valve 62, by means of which an amount of recirculating exhaust gas is variably adjustable. Furthermore, the exhaust gas recirculation device 54 comprises an exhaust gas recirculation cooler 64, by means of which the exhaust gas to be recirculated can be cooled.
  • the flood 42 is designed as a so-called EGR flood (EGR - exhaust gas recirculation).
  • EGR flood EGR - exhaust gas recirculation
  • the tide 42 has the task of providing a desired and correspondingly high damming behavior of the turbine 44, so that particularly large amounts of exhaust gas to be recirculated can be displayed.
  • amounts of gurterndem exhaust gas are advantageous, which 50% of
  • the flood 48 is formed as a so-called ⁇ -flood.
  • the flood 48 is in particular the task, a desired and advantageous air supply of
  • Internal combustion engine 10 to provide side of the intake manifold 14 so that a desired combustion air ratio ( ⁇ ) is present in the cylinders 12, so that the internal combustion engine 10 can provide high power and torque.
  • a receiving space 65 is at least partially limited by the turbine housing 50, in which a turbine wheel 66 of the turbine 44 is received at least in some areas.
  • the turbine wheel 66 is rotatable about the axis of rotation 22 relative to the turbine housing 50 and rotatably connected to a shaft 68 of the exhaust gas turbocharger 20. With the shaft 68 and the compressor 24 is rotatably connected, so that the compressor 24 can be driven by the turbine 66 via the shaft 68.
  • the exhaust gas is guided via the floods 42 and 48 to the turbine wheel 66.
  • the exhaust gas flowing through the tide 42 flows out via a first nozzle 70 assigned to the tide 42 and the turbine wheel 66.
  • the exhaust gas flowing through the flood 48 flows out of the latter through a nozzle 72 and out of the latter 48 and the turbine wheel 66.
  • the turbine 44 according to FIG. 1 now comprises an adjusting device 74, which is assigned only to the nozzle 70 of the flood 42.
  • a flow cross-section S AGR of the nozzle 70 is variably adjustable.
  • the turbine 44 according to FIG. 1 further comprises a further adjusting device 76, by means of which flow conditions in a turbine wheel outlet region 78 are variably adjustable.
  • the adjusting device 76 is, for example, a conical slide which can be seen in FIGS. 2 and 3 and which comprises an adjusting element 80 which is at least essentially conical in shape.
  • the cone-shaped adjusting element 80 is displaceable in the axial direction of the turbine 44 in accordance with a directional arrow 82 relative to the turbine housing 50. By moving the adjusting element 80, a downstream of the
  • Turbine wheel 66 arranged, narrowest flow cross-section of the turbine 44 are variably adjusted, wherein the arranged downstream of the turbine wheel, narrowest flow cross-section is in the rotating relative system of the turbine wheel outlet region 78.
  • Turbine wheel 66 variably adjustable, while by means of the adjusting device 76 of the turbine wheel arranged downstream of the narrowest flow cross-section is variably adjustable.
  • the narrowest flow cross-section arranged downstream of the turbine wheel is referred to as S Kon us.
  • the nozzle 72 that is, the ⁇ -flood, is associated with the turbine 44 of FIG. 1, no such adjusting device. If the turbine 44 is designed with reference to the flood 42 as a so-called Varioturbine (due to the adjusting device 74), the turbine 44 is relative to the flood 48 and the nozzle 72 as
  • the internal combustion engine 0 comprises a regulating device 84, by means of which the adjusting device 74 and 76 can be controlled or regulated.
  • the adjusting device 76 can be controlled, for example, via a simple control, for example via the boost pressure of the exhaust gas turbocharger 20. This keeps costs low.
  • an exhaust aftertreatment device 86 is arranged downstream of the turbine 44, by means of which to clean the exhaust gas flowing through the exhaust tract 34 is before it is released to the environment.
  • the exhaust aftertreatment device 86 includes, for example, a particulate filter, by means of which soot particles can be retained so as to keep the soot emissions of the motor vehicle particularly low.
  • the nozzle 72 may be assigned a guide grid 88.
  • the guide grid comprises a plurality of guide vanes 90, by means of which the exhaust 48 flowing through the exhaust gas is deflected accordingly.
  • the turbine wheel 66 can be flowed with a particularly favorable flow angle.
  • 2 bearing housing 92 of the exhaust gas turbocharger 20 is also shown, on which the shaft 68 and the shaft 68, the compressor 24 and the turbine 66 are rotatably mounted about the axis of rotation 22.
  • the nozzle 72 is also a guide grid 88 'with a plurality of guide vanes 90'.
  • a die 93 of the adjusting device 74 is provided for variable adjustment of the flow cross section S AGR of the nozzle 70.
  • the die 93 is according to the
  • Hub body 98 of the turbine 66 is connected.
  • an at least substantially in the axial direction according to the directional arrow 82 extending leading edge 100 is formed, via which the turbine wheel 66 can be flowed by the exhaust gas.
  • trailing edges 102 and 104 are formed, via which the turbine wheel 36 and the impeller blade 96 can be flowed from the exhaust gas.
  • the outflow edge 104 which is referred to as the main exit edge, extends at least essentially in the radial direction of the turbine wheel in accordance with a directional arrow 106.
  • the outflow edge 102 which is referred to as the "vario exit edge” runs both obliquely to the leading edge 100 and obliquely to the trailing edge 104 and thus extends obliquely to the axial direction of the turbine wheel 66th
  • the narrowest flow cross-section S Kon us can fluidly blocked, or at least substantially be released other hand, by means of the adjusting element 80, the Vario trailing edge. 2
  • the trailing edge 102 includes an angle ⁇ with the radial direction of the turbine wheel according to the directional arrow 106, which ranges from at least substantially 45 degrees to at least substantially 60 degrees lies.
  • Trained as a radial turbine turbine 44 can thus both the return of exhaust gas and the supply of the internal combustion engine 10 with a
  • the ⁇ -flood (flood 48) and the adjusting device 76 which a
  • Turbinenradaustrittsvariabiltician are developed to an optimal charge change out, so that particularly advantageous and low-efficiency reaction rates of the turbine 44 for high turbine efficiencies on the adjustability of
  • the control device 84 will control or set control variables or control variables of the adjusting devices 74 and 76 for an emission and fuel consumption-optimal operation of the internal combustion engine such that a desired EGR rate, that is to say a desired amount of exhaust gas to be recirculated, as well as an optimal airflow. Fuel ratio ⁇ result.
  • Component temperatures causes. This can be an effective and efficient
  • the particle filter of the Exhaust after-treatment device 36 burned off and so absorbed by
  • a particular advantage of the turbine 44 according to FIG. 2 is that the guide vane 90 'of the guide grid 88' can be displaced at least substantially completely fluidically by means of the die 93. In this case, an end face 108 of the die 93 touches the through the
  • Turbine housing formed intermediate wall 52, so that the flow cross section SAG is at least substantially 0. As a result, the die 98 is in her
  • Exhaust rates of at least substantially and at least nearly 50% can be represented. This means that at least substantially 50% of the total exhaust gas of the internal combustion engine 10 can be returned from the exhaust tract 34 to the intake tract 14 and introduced into it.
  • the adjustability of these high EGR rates with nearly complete closure of the EGR flood nozzle 70 is at low part load operating points and in thermal management phases
  • Internal combustion engine 10 advantageously usable.
  • Fig. 2 shows the die 93 in its maximum opening position. It is the
  • Flow cross section S AGR set to its maximum value S AG, max.
  • the influence of the ⁇ -flood (flood 48) on the air-fuel ratio ⁇ is in the turbine 44 from the flow cross section S Ko nu S , which is adjustable by the adjusting device 76.
  • Adjustment element 80 is the adjusting device 76, which also as
  • Taper slider is called, in a position in which between the trailing edge 102 and the konusformige adjustment 80, a narrowest gap is formed.
  • the outflow of the turbine wheel 66 is at least substantially only over the
  • FIG. 3 shows an alternative embodiment of the turbine 44 according to FIG. 2.
  • the nozzle 72 of the ⁇ -flood (flood 48) is not a guide grid
  • a flow cross section S x of the nozzle 72 is bounded on one side by the turbine housing 50 and on the other hand by the intermediate wall 52 formed by the turbine housing 50 between the floods 42 and 48.
  • the ⁇ -flood nozzle 72 is a free annular nozzle without a radial grid or the like.
  • a swirl characteristic of the ⁇ -flood for a significant turbine power fraction is thus accomplished by a spiral dimensioning of the ⁇ -flood.
  • the flood 42 and / or 48 may be formed at least substantially as a spiral channel, which extend at least substantially in the circumferential direction of the turbine wheel 66 over its circumference.
  • the adjusting devices 74 and 76 can be mechanically coupled to each other by a suitable coupling device, so that only one actuator, such as an electric motor or the like, is needed and can be provided to move the die 93 and the adjusting element 80 according to the directional arrows 82.
  • an actuator such as an electric motor or the like
  • Adjustment 80 is moved differs.
  • FIGS. 4 to 6 serve, in particular, to illustrate the throughput behavior of the turbine 44 with the adjusting devices 74 and 76.
  • FIG. 4 shows a diagram 110, on the abscissa 112 of which the ratio of the adjusted flow cross section S AGR and the maximum adjustable flow cross section S A GR, max is plotted.
  • the critical flow rate parameter of the turbine 44 is plotted.
  • Plot 110 illustrates a plot 116 showing a linear opening behavior by means of the turbine 44 critical flow rate parameter versus the ratio S AGR / EGR .max of the variable blade height of the vanes 90 'of the EGR flood grid 88' (flood 42) ,
  • the ratio S AGR / S AGR ⁇ X represents a relative manipulated variable of the turbine 44.
  • the ratio S A GR SAGRmmax thus represents the relative blade height of
  • Turbinenradaustritts Design S K o n _s, max is, for example, at least in
  • the turbine pressure ratio is n T. s greater than the critical turbine pressure ratio 7i Ts , krit- Furthermore, it is assumed that the ⁇ - flood is at least substantially fluidly blocked and is not traversed by exhaust gas.
  • the flow cross section S A GR increases according to a
  • FIG. 5 shows a diagram 120, on the abscissa 122 of which a ratio of the turbine wheel outlet surface S 'onus to be set or set to the maximum possible turbine wheel outlet surface S K onus, ma is plotted.
  • the ratio SKonus S K0 nus, max is thus a relative path around which the cone slide is moved.
  • the flow rate parameter of the turbine 44 is plotted on the ordinate 124 of the graph 120.
  • the critical flow rate parameter plotted on the ordinate 14 and the flow rate parameter plotted on the ordinate 124 refer to the EGR flow rate parameter, which corresponds to the flow rate parameter of the entire turbine 44, as described , the ⁇ -flood fluidly at least substantially blocked.
  • Directional arrow 126 in diagram 120 indicates that the relative travel by which the cone slide is moved increases with the directional arrow 126.
  • the course 128 relates to an adjustment of the cone slide, starting from a closed position (relative travel equal to 0) to its maximum open position (relative travel equal to 1), wherein the relative blade height is maintained at least substantially constant at the value 1, 0.
  • the course 130 relates to a movement of the cone slide from the closed position to the maximum open position, wherein the relative blade height is maintained at least substantially constant at the value 0.5.
  • the curve 132 refers to an adjustment of the cone slide from the closed position to the open position, wherein the relative blade height is maintained at least substantially constant at the value 0.2.
  • the throughput parameter of the ⁇ -flood (in the case of a fluidically blocked EGR flood) is usually dimensioned substantially larger than the flow rate parameter of the EGR flood (in the case of a fluid-locked ⁇ -flood). This is the case in particular at the maximum relative blade height of 1.0. As a result, there is a desired, significant weight on the part of the ⁇ -flood
  • Internal combustion engine 10 can be moved. There are still enough degrees of freedom to set sufficient and desirable high EGR rates by means of the die 93 associated with the EGR flood.
  • the turbine 44 thus has the properties of an asymmetrical full-vario turbine, which can be applied to both passenger cars and commercial vehicles. This is advantageous insofar as a strong nitrogen oxide reduction in high load ranges is required in particular by future emission regulations.
  • FIG. 6 shows a diagram 134, on the abscissa 136 of which the turbine pressure ratio ⁇ -r-s is plotted. On the ordinate 138 of the diagram 134 is the
  • the region A refers to the turbine 44, with exhaust flow through the EGR flood and with fluidically obscured ⁇ -flood.
  • the region B refers to the turbine 44 when the EGR flood fluidly blocked and the ⁇ -flood is released.
  • the region C refers to the entire turbine 44, in which both the EGR flood and the ⁇ -flood of exhaust gas of the internal combustion engine 10 can be flowed through.
  • the area A is bounded by a course 140, in which the
  • Flow cross section S AG is set to 0. This means that the die 93 with its end face 108, the intermediate wall 52 touches.
  • the region A is limited by a profile 142, in which the flow cross-section S AGR is set to its maximum value S AGR , max.
  • the flow cross-section S Ko nus is set to its maximum value S K0 nus, max.
  • the EGR flood is the variably settable flood 42, which allows for a flow rate spread of the turbine 44 from almost completely fluidly sealed to the upper dimensioned open flow areas of the guide grid 88 '.
  • the degree of reaction of this turbine which is referred to as a partial turbine due to the fluidic obstruction of the ⁇ -flood and the release of the EGR flood is usually very low, whereby the stuffing point usually with complete opening of the guide grid 88 'and thus the vanes 90' usually even with closed turbine 66, that is, when setting the smallest
  • Turbine wheel exit surface usually in the region of an outlet of the guide grid 88 'upstream of the turbine wheel 66 sets.
  • the area B is bounded on the one hand by a course 144, in which the
  • the region B is limited by a profile 146, in which the flow cross-section S Ko nus to its maximum value S K0 nus, max is set.
  • the turbine 44 which is referred to as a sub-turbine in the area B, in which the EGR flood fluidly blocked and the ⁇ -flood is fluidly released, also has a relation to the area B due to larger, effective flow cross-sections upstream of the turbine 66 noticeably greater degree of reaction with respect to the sub-turbine according to region A.
  • the critical, throughput-determining flow cross-section is now in the turbine wheel outlet region 78 and that for positions of the
  • the area C shows the overall throughput behavior, in particular for an application for exhaust gas recirculation, wherein the turbine 44 is designed as a quasi-Vollvarioturbine.
  • the region C is limited on the one hand by a profile 148, in which the flow cross section SA GR is set to its maximum value S AG R, max, during the flow cross section S 0 nus is set to its minimum value S K onus, min.
  • the region C is limited by a profile 150, in which the flow cross-section S A GR is set to its maximum value, while the flow cross-section S cone is also set to its maximum value S Ko nus.max.
  • a total throughput spread AO GES max which results from the combination of the two adjusting devices 74 and 76, is shown in a diagram 134. It can be seen that the total throughput spread AO ges , ma x is a function of
  • the turbine 44 may also comprise a further, third adjusting device, which is associated with the ⁇ -flood (flood 48).
  • the flow cross-section ⁇ ⁇ of the flood 48 can also be set variably, so that the turbine 44 can be adapted and adjusted to different operating points of the internal combustion engine 10 in a particularly demand-oriented and efficient manner.

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

Abstract

L'invention porte sur une turbine (44) pour un turbocompresseur sur gaz d'échappement (20) appartenant à un moteur à combustion interne (10), comportant un carter de turbine (50) qui est parcouru par le gaz d'échappement d'un moteur à combustion interne (10), et dans lequel est logée au moins par endroits une roue de turbine (66) qui peut tourner autour d'un axe de rotation (22) et qui présente au moins deux passages (42, 48) qui peuvent être parcourus chacun par au moins une partie des gaz d'échappement, qui sont séparés fluidiquement l'un de l'autre au moins par régions, et à chacun desquels est associée au moins une buse (70, 72) par l'intermédiaire de laquelle les gaz d'échappement qui traversent les passages (42, 48) correspondants peuvent être amenés à la roue de turbine (66) pour alimenter la roue de turbine (66) avec les gaz d'échappement. A au moins une première des buses (70, 72), est associé un premier dispositif de réglage (74) au moyen duquel une section d'écoulement (Sλ,SAGR) de la première buse (70, 72) peut être réglée de façon variable, et un deuxième dispositif de réglage (76) est disposé au moins en partie dans une région de sortie (78) de la roue de turbine. Au moyen dudit deuxième dispositif de réglage (76), il est possible d'agir sur les conditions d'écoulement, au moins sensiblement dans la région de sortie (78) de la roue de turbine.
PCT/EP2011/006094 2011-04-08 2011-12-06 Turbine pour un turbocompresseur sur gaz d'échappement, ainsi que moteur à combustion interne équipé d'une telle turbine Ceased WO2012136234A1 (fr)

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DE102011016529A DE102011016529A1 (de) 2011-04-08 2011-04-08 Turbine für einen Abgasturbolader sowie Verbrennungskraftmaschine mit einer solchen Turbine
DE102011016529.0 2011-04-08

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US20140331667A1 (en) * 2013-05-08 2014-11-13 Ford Global Technologies, Llc Internal combustion engine with deactivatable cylinder, and method for operating an internal combustion engine of said type

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DE102011115251A1 (de) * 2011-09-28 2013-03-28 Daimler Ag Verbrennungskraftmaschine für einen Kraftwagen

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US4776168A (en) * 1987-05-21 1988-10-11 Woollenweber William E Variable geometry turbocharger turbine
EP1866534B1 (fr) 2005-04-04 2008-09-24 Honeywell International Inc. Turbocompresseur a debit variable
DE102008039086A1 (de) * 2008-08-21 2010-02-25 Daimler Ag Abgasturbolader für eine Brennkraftmaschine eines Kraftfahrzeugs
DE102008049782A1 (de) * 2008-09-30 2010-04-08 Daimler Ag Abgasturbolader für eine Brennkraftmaschine
DE102008063656A1 (de) * 2008-12-18 2010-06-24 Daimler Ag Abgasturbolader

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Publication number Priority date Publication date Assignee Title
US4776168A (en) * 1987-05-21 1988-10-11 Woollenweber William E Variable geometry turbocharger turbine
EP1866534B1 (fr) 2005-04-04 2008-09-24 Honeywell International Inc. Turbocompresseur a debit variable
DE102008039086A1 (de) * 2008-08-21 2010-02-25 Daimler Ag Abgasturbolader für eine Brennkraftmaschine eines Kraftfahrzeugs
DE102008049782A1 (de) * 2008-09-30 2010-04-08 Daimler Ag Abgasturbolader für eine Brennkraftmaschine
DE102008063656A1 (de) * 2008-12-18 2010-06-24 Daimler Ag Abgasturbolader

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140331667A1 (en) * 2013-05-08 2014-11-13 Ford Global Technologies, Llc Internal combustion engine with deactivatable cylinder, and method for operating an internal combustion engine of said type
CN104153873A (zh) * 2013-05-08 2014-11-19 福特环球技术公司 具有可失活汽缸的内燃发动机及用于运行所述类型内燃发动机的方法
US9624823B2 (en) 2013-05-08 2017-04-18 Ford Global Technologies, Llc Internal combustion engine with deactivatable cylinder, and method for operating an internal combustion engine of said type
CN104153873B (zh) * 2013-05-08 2019-01-04 福特环球技术公司 具有可失活汽缸的内燃发动机及用于运行所述类型内燃发动机的方法

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