EP3601739B1 - Turbocompresseur pour un moteur à combustion interne ainsi que roue de turbine - Google Patents

Turbocompresseur pour un moteur à combustion interne ainsi que roue de turbine Download PDF

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Publication number
EP3601739B1
EP3601739B1 EP18718704.2A EP18718704A EP3601739B1 EP 3601739 B1 EP3601739 B1 EP 3601739B1 EP 18718704 A EP18718704 A EP 18718704A EP 3601739 B1 EP3601739 B1 EP 3601739B1
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EP
European Patent Office
Prior art keywords
turbine
axtip
turbocharger
housing
turbine wheel
Prior art date
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EP18718704.2A
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German (de)
English (en)
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EP3601739A1 (fr
Inventor
Ivo Sandor
Sebastian WITTWER
Michael Klaus
Ralf Böning
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Vitesco Technologies GmbH
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Vitesco Technologies GmbH
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F05D2240/54—Radial bearings

Definitions

  • the invention relates to a turbocharger for an internal combustion engine.
  • Exhaust gas turbochargers are increasingly being used to increase the performance of motor vehicle internal combustion engines. This is happening more and more frequently with the aim of reducing the size and weight of the internal combustion engine with the same or even increased performance and at the same time reducing consumption and thus CO 2 emissions in view of the increasingly strict legal requirements in this regard.
  • the operating principle consists in using the energy contained in the exhaust gas flow in order to increase a pressure in an intake tract of the internal combustion engine and thus bring about better filling of a combustion chamber of the internal combustion engine with air-oxygen. This means that more fuel, such as petrol or diesel, can be converted per combustion process, i.e. the performance of the combustion engine can be increased.
  • the exhaust gas turbocharger has an exhaust gas turbine arranged in the exhaust tract of the internal combustion engine, a fresh air compressor arranged in the intake tract and a rotor bearing arranged in between.
  • the exhaust gas turbine has a turbine housing and a turbine impeller which is arranged therein and is driven by the exhaust gas mass flow.
  • the fresh air compressor has a compressor housing and a compressor impeller which is arranged therein and builds up boost pressure.
  • the turbine impeller and the compressor impeller are arranged in a rotationally fixed manner on the opposite ends of a common shaft, the so-called rotor shaft, and thus form the so-called turbocharger rotor.
  • the rotor shaft extends axially between the turbine rotor and the compressor rotor through the rotor bearing arranged between the exhaust gas turbine and the fresh air compressor and is rotatably mounted in it radially and axially with respect to the rotor shaft axis.
  • the turbine impeller driven by the exhaust gas mass flow drives the compressor impeller via the rotor shaft, which increases the pressure in the intake tract of the combustion engine, based on the fresh air mass flow behind the fresh air compressor, and thus causes better filling of the combustion chamber with air-oxygen.
  • Such an exhaust gas turbocharger for an internal combustion engine is, for example, in document EP 3 144 541 A1 disclosed.
  • This has a bearing housing which is arranged between an exhaust gas turbine with a turbine impeller and a centrifugal compressor with a compressor impeller and in which a rotor shaft is mounted so that it can rotate about a rotor axis of rotation on which the turbine impeller and the compressor impeller are each arranged in a rotationally fixed manner.
  • the turbine wheel has wheel blading and is arranged in the turbine housing, which is mechanically fixed to the bearing housing.
  • the turbine wheel includes turbine blades each having a flow leading edge and a flow trailing edge that define an entry radius and an exit radius of the turbine wheel.
  • the turbine blades have an outer contour facing the turbine housing, which extends from the flow inlet edge to the flow outlet edge.
  • the turbine housing has a housing contour that is opposite the outer contour of the turbine blades, with a radial distance being formed between the housing contour and the outer contour, which enables contact-free rotation of the turbine impeller in the turbine housing.
  • An object on which the invention is based is to specify a concept for a turbocharger that contributes to safe operation of a turbocharger.
  • the turbine housing and the turbine wheel are designed and matched to one another in such a way that the following condition or equation is met: L covers L axTip > 1 ⁇ hint clr R in ⁇ 3 ⁇ 4 ⁇ 1 1 ⁇ R out R in .
  • damage to the turbocharger can occur during operation of the turbocharger, for example during test bench runs for the design of the turbocharger or components of the turbocharger such as the rotor. For example, a component failure of the rotor shaft or the impellers, such as a broken shaft, can occur.
  • the turbine wheel can no longer be held in its intended position axially by an axial bearing.
  • the turbine wheel would be moved in the direction of a turbine housing outlet for the exhaust gas mass flow primarily by aerodynamic forces, for example due to prevailing gas pressures.
  • the portion of the turbine blades of the turbine wheel that has a larger diameter than an outlet diameter of the turbine housing at the downstream end of the turbine wheel abuts the turbine housing and hinders the turbine wheel in its axial movement in the direction of the turbine housing outlet. It was also recognized that if this proportion of the turbine wheel blades is not sufficiently large, the turbine blades are plastically deformed in the event of a shaft breakage in such a way that the turbine wheel can carry out a further, unwanted axial displacement.
  • the turbocharger described provides that the turbine wheel and turbine housing are designed and arranged according to the condition (equation) formulated above.
  • the condition stipulates that a contour profile of the turbine housing and/or the at least one turbine wheel blade are specifically redesigned compared to known turbines.
  • a length portion (L cover ) of the turbine wheel blade, in which a diameter of the turbine wheel is larger than a smallest diameter DA of the turbine housing at the turbine blade outlet, is increased in such a way that in the event of a shaft breakage, a larger proportion of the turbine wheel blades would be plastically deformed in the event of an axial displacement , so that further axial movement of the turbine wheel with respect to the rotor axis of rotation is impeded or limited.
  • the length portion of the turbine wheel blade in which a diameter of the turbine wheel is larger than a smallest diameter DA of the turbine housing at the turbine blade outlet is increased simply by the redesign.
  • the condition defines a minimum value of said length portion of the turbine wheel blade.
  • Such a design based on the given equation contributes to the fact that the turbine wheel, after a shaft breakage, i.e. in the event of damage to the turbocharger, one provides greater resistance to further axial displacement upon collision with the housing.
  • the equation thus enables an optimal design for the turbine wheel and turbine housing on the basis of various parameters.
  • certain parameters of the like can be specified, with one or more remaining parameters being able to be determined using the equation. In this way, a reasonable adjustment of the parameters can always be achieved according to the framework conditions.
  • using the equation it is possible to easily determine the axial cover length L cover necessary for the above advantages and functions.
  • a turbocharger designed according to the conditions helps to avoid the disadvantages mentioned at the outset in the event of damage, in particular the shaft breakage mentioned, in particular when the turbine wheel is only mounted radially.
  • it is not absolutely necessary to constructively reinforce a back disk and/or the turbine wheel blades.
  • it is not necessary to correspondingly thicken the turbine wheel blades.
  • it is not necessary to provide a low trim ratio, ie a ratio between the maximum exit radius R out and the maximum entry radius R in .
  • Material costs among other things, can be saved as a result. Both such measures would be disadvantageous with regard to the performance of the turbocharger, for example due to higher mass inertia.
  • a meridional view means, for example, a flat, two-dimensional view in which an outermost contour of the turbine wheel is shown, which the turbine wheel traces during a rotation about the rotor axis of rotation, which also corresponds to an axis of rotation of the turbine wheel.
  • the view can also relate to or include at least parts of the turbine housing, with an inner contour with a minimal radius in relation to the axis of rotation in the area of the turbine wheel being shown in particular, which the turbine housing would traverse when rotating about the axis of rotation.
  • the housing contour of the turbine housing (English: shroud) opposite the outer contour is designed to correspond to the outer contour.
  • the smallest radial distance Tip clr with respect to the axis of rotation of the rotor can be a distance that is constant over the entire axial area between the leading edge and the trailing edge. However, it is also conceivable for the distance to be present only in sections, in a single area or point with respect to the axis of rotation.
  • the axial length component (L cover ) means that axial extent of the outer contour in which a radius or a diameter of the turbine wheel with respect to the rotor axis of rotation is larger than a minimum diameter/radius of the turbine housing in the region of a downstream end of the turbine wheel. In other words, in this area the diameter of the turbine wheel is larger than a smallest diameter of the turbine housing. In other words, it is that axial area of a turbine wheel which, if the turbine wheel and the turbine housing were projected into a plane normal to the rotor axis of rotation, is covered or overlapped by the turbine housing. In other words, this is the area that lies in the shadow of the turbine housing in relation to the rotor axis of rotation.
  • the outer contour of the at least one blade has an axial overlap section that corresponds to the axial length component L cover of the axial extension L axTip .
  • the ratio Tip clr to R in is : hint clr R in ⁇ 2.5 % .
  • the ratio Tip clr to R in is : hint clr R in ⁇ 2.0 % .
  • the ratio Tip clr to R in is : hint clr R in ⁇ 1.5 % .
  • the ratio of L cover to L axtip is : L covers L axTip > 0.2 .
  • the ratio of L cover to L axtip is : L covers L axTip > 0.25 .
  • the ratio of L cover to L axtip is: L covers L axTip > 0.3 .
  • the ratio of R out to R in is : R out R in > 0.8 .
  • the ratio of R out to R in is : R out R in ⁇ 0.95 .
  • the ratio of R out to R in is : R out R in ⁇ 0.93 .
  • the ratio of R out to R in is : R out R in ⁇ 0.92 .
  • the ratio of R out to R in is : R out R in ⁇ 0.91 .
  • the ratio of R out to R in is : R out R in ⁇ 0.90 .
  • the ratio R out to R in is also referred to as the trim or trim ratio.
  • the trim ratio is between 0.8 and one of the other limits specified above.
  • a turbine wheel for a turbocharger according to one of the previous embodiments is disclosed.
  • the turbine wheel has impeller blading with a plurality of turbine blades.
  • the turbine wheel is designed in such a way that the following condition is met: L covers L axTip > 1 ⁇ hint clr R in ⁇ 3 ⁇ 4 ⁇ 1 1 ⁇ R out R in
  • the turbine wheel enables the advantages and functions mentioned above.
  • the method enables the advantages and functions mentioned above.
  • FIG 1 shows a schematic of an exemplary exhaust gas turbocharger 1 in a sectional view, which has an exhaust gas turbine 20 , a fresh air compressor 30 and a rotor bearing 40 .
  • the exhaust gas turbine 20 is equipped with a wastegate valve 29 and an exhaust gas mass flow AM is indicated with arrows.
  • the fresh air compressor 30 has an overrun air recirculation valve 39 and a fresh air mass flow FM is also indicated with arrows.
  • a so-called turbocharger rotor 10 of the exhaust gas turbocharger 1 has a turbine wheel 12 (also called turbine wheel), a compressor wheel 13 (also called compressor wheel) and a rotor shaft 14 (also called shaft).
  • turbocharger rotor 10 rotates about a rotor axis of rotation 15 of the rotor shaft 14.
  • the rotor axis of rotation 15 and at the same time the turbocharger axis 2 are represented by the center line drawn in and characterize the axial alignment of the exhaust gas turbocharger 1.
  • a common exhaust gas turbocharger 1 As shown in figure 1 shown, a multi-part structure.
  • a turbine housing 21 that can be arranged in the exhaust tract of the internal combustion engine, a compressor housing 31 that can be arranged in the intake tract of the internal combustion engine, and a bearing housing 41 between the turbine housing 21 and the compressor housing 31 are arranged next to one another with respect to the common turbocharger axis 2 and are connected to one another in terms of assembly.
  • the bearing housing 41 is arranged axially between the turbine housing 21 and the compressor housing 31 .
  • the bearing housing 41 accommodates the rotor shaft 14 of the turbocharger rotor 10 and the bearing arrangement required for the axial bearing and for the rotary bearing of the rotor shaft 14 .
  • turbocharger rotor 10 Another assembly of the exhaust gas turbocharger 1 is the turbocharger rotor 10, the rotor shaft 14, which is arranged in the turbine housing 21 turbine impeller 12 with a Impeller blading 121 and arranged in the compressor housing 31 compressor impeller 13 having an impeller blading 131.
  • the turbine wheel 12 as well as the compressor wheel 13 have a plurality of blades which are arranged on a corresponding hub.
  • the turbine wheel 12 and the compressor wheel 13 are arranged on the opposite ends of the common rotor shaft 14 and are non-rotatably connected thereto.
  • the rotor shaft 14 extends axially through the bearing housing 41 in the direction of the turbocharger axis 2 and is rotatably mounted in it axially and radially about its longitudinal axis, the rotor axis of rotation 15 , with the rotor axis of rotation 15 coinciding with the turbocharger axis 2 .
  • the turbocharger rotor 10 is mounted with its rotor shaft 14 by means of two radial bearings 42 and an axial bearing disk 43 . Both the radial bearing 42 and the axial bearing disk 43 are supplied with lubricant via oil supply channels 44 of an oil connection 45 .
  • the turbine housing 21 has one or more exhaust gas annular ducts, so-called exhaust gas flows 22 , arranged in a ring shape around the turbocharger axis 2 and the turbine impeller 12 , tapering helically towards the turbine impeller 12 .
  • These exhaust gas flows 22 have a respective or common, tangentially outwardly directed exhaust gas supply channel 23 with a manifold connecting piece 24 for connection to an exhaust manifold (not shown) of an internal combustion engine, through which the exhaust gas mass flow AM flows into the respective exhaust gas flow 22 and then onto the turbine impeller 12 flows.
  • the turbine housing 21 also has an exhaust gas discharge channel 26 which runs away from the axial end of the turbine impeller 12 in the direction of the turbocharger axis 2 and has an exhaust connection piece 27 for connection to the exhaust system (not shown) of the internal combustion engine.
  • the exhaust gas mass flow AM emerging from the turbine impeller 12 is discharged into the exhaust system of the internal combustion engine via this exhaust gas discharge channel 26 .
  • turbocharger 1 Further details of the turbocharger 1 are not explained in more detail at this point. It should be noted that the in figure 1 described turbocharger 1 is to be understood as an example and alternatively can also have other configurations, without there being any restrictions for the following description of exemplary embodiments of the invention with reference to FIG Figures 4 to 6 result.
  • Figures 2 and 3 each show a meridional view of exhaust gas turbines 20 of a turbocharger 1, each of which has a turbine housing 21 and a turbine wheel 12 with a plurality of turbine blades 122.
  • FIG 2 is a radial-axial turbine wheel and in figure 3 a radial turbine wheel is shown in a schematic half section.
  • the turbine wheel 12 has an upstream, axial end 124 and a downstream, axial end 125.
  • the turbine blade 122 shown like all other turbine blades, has a flow inlet edge 126 for the exhaust gas mass flow AM and a flow outlet edge 127 for the exhaust gas mass flow AM after exiting the turbine wheel 12 or the turbine blades 122.
  • the flow inlet edge 126 and/or the flow outlet edge 127 can run obliquely or otherwise, approximately parallel, to the rotor axis of rotation 15, as shown in FIG Figures 2 and 3 is evident.
  • the flow inlet edge 126 and the flow outlet edge 127 are connected via an outer contour 128 (English tip).
  • the outer contour 128 lies directly opposite a housing contour 211 of the turbine housing 21 which surrounds the turbine wheel 12 .
  • the housing contour 211 is designed to correspond to the outer contour 128, with a course of the two contours 128 and 211 in the view shown running essentially parallel to one another with respect to FIG Axis of rotation 123.
  • the other turbine housing 21 is not shown for reasons of clarity.
  • the flow entry edge 126 has a maximum entry radius R in and the flow exit edge 127 has a maximum exit radius R out .
  • the outer contour 128 has an axial extension length L axTiP in relation to the axis of rotation 123 or the axis of rotation 15 of the rotor.
  • Outer contour 128 has an axial length portion L cover of axial extent L axTiP , in which a diameter of turbine wheel 12 is greater than a smallest diameter DA of turbine housing 21 at turbine blade outlet 129 for exhaust gas mass flow AM.
  • the housing contour 211 and the outer contour 128 are spaced apart from one another in such a way that a minimal gap is formed, with a smallest radial distance Tip clr between the housing contour 211 and the outer contour 128 prevailing.
  • turbochargers can be damaged with various adverse consequences. Based on Figures 4 to 6 exemplary embodiments of turbines 20 are described which, in the event of damage to the turbocharger 1, enable the functions and advantages mentioned at the outset.
  • figure 4 shows a turbine 20, which is essentially the turbine of Figures 2 and 3 is equivalent to.
  • the above parameter definitions apply analogously.
  • the turbine 20 is designed in such a way that the figure 5 equation shown is satisfied.
  • the condition is: L covers L axTip > 1 ⁇ hint clr R in ⁇ 3 ⁇ 4 ⁇ 1 1 ⁇ R out R in . This achieves the advantages and functions mentioned at the outset. It should be mentioned at this point that the ratio R out to R in can be called the trim (see Fig. figure 5 ) .
  • the turbine 20 is designed and manufactured, for example, in such a way that certain parameters are specified and the remaining parameters are determined using the conditions in order to obtain a necessary minimum value for L Cover .
  • the axial length portion L cover is increased and matched to the turbine housing 21 .
  • the turbine wheel 12 has an enlarged portion that is covered by the turbine housing 21 .
  • figure 6 shows a diagram in which the trim value is plotted on the x-axis and the ratio of L cover to L axTip is plotted on the y-axis.
  • Three curves according to the equation are exemplary figure 5 shown, which are distinguished by the percentage values shown on the right next to the diagram, which result from the ratio Tip clr to R in .

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Claims (10)

  1. Turbocompresseur (1) pour un moteur à combustion interne, présentant
    - un logement de palier (41) dans lequel un arbre de rotor (14) est monté en rotation autour d'un axe de rotation de rotor (15) ; et
    - une turbine à gaz d'échappement (20) pourvue d'une roue de turbine (12) qui est disposée de manière solidaire en rotation sur l'arbre de rotor (14) et qui présente un aubage de roue à aubes (121) pourvu de plusieurs aubes de turbine (122), et pourvue d'un carter de turbine (21) qui est immobilisé mécaniquement sur le logement de palier (41) et qui entoure la roue de turbine (12) ;
    dans lequel, en se référant à une vue méridienne de la turbine à gaz d'échappement (20),
    - au moins une aube de turbine (122) de la roue de turbine (12) présente un bord d'attaque d'écoulement (126) et un bord de fuite d'écoulement (127) pour le débit massique de gaz d'échappement (AM),
    - le bord d'attaque d'écoulement (126) présente un rayon d'entrée maximal Rin et le bord de fuite d'écoulement (127) présente un rayon de sortie maximal Rout, respectivement par rapport à l'axe de rotation de rotor (15) ;
    - ladite au moins une aube de turbine (122) présente un contour extérieur (128) tourné vers le carter de turbine (21), qui s'étend du bord d'attaque d'écoulement (126) au bord de fuite d'écoulement (127) et présente une longueur d'extension axiale LaxTip ;
    - le carter de turbine (21) présente un contour de carter (211) qui fait face au contour extérieur (128) ;
    - le contour extérieur (128) de ladite au moins une aube de turbine (122) présente une part de longueur axiale Lcover de l'extension axiale LaxTip dans laquelle un diamètre de la roue de turbine est supérieur à un diamètre le plus petit DA du carter de turbine à la sortie d'aube de turbine pour le débit massique de gaz d'échappement AM ; et
    - une distance radiale la plus faible Tipclr est réalisée entre le contour de carter (211) et le contour extérieur (128) par rapport à l'axe de rotation de rotor (15) ;
    et dans lequel la turbine à gaz d'échappement est caractérisée en ce que le carter de turbine (21) et la roue de turbine (12) sont réalisés et adaptés l'un à l'autre de façon à satisfaire la condition suivante : L cover L axTip > 1 − Tip clr R in × 3 π 4 × 1 1 − R out R in
    Figure imgb0041
  2. Turbocompresseur (1) selon la revendication 1, dans lequel pour le rapport entre Tipclr et Rin : Tip clr R in ≤
    Figure imgb0042
     2,5%.
  3. Turbocompresseur (1) selon l'une quelconque des revendications précédentes, dans lequel pour le rapport entre Tipclr et Rin : Tip clr R in ≤ 2,0 %
    Figure imgb0043
    .
  4. Turbocompresseur (1) selon l'une quelconque des revendications précédentes, dans lequel pour le rapport entre Tipclr et Rin : Tip clr R in ≤ 1,5 %
    Figure imgb0044
    .
  5. Turbocompresseur (1) selon l'une quelconque des revendications précédentes, dans lequel pour le rapport entre Lcover et LaxTip : L cover L axTip > 0,2
    Figure imgb0045
    .
  6. Turbocompresseur (1) selon l'une quelconque des revendications précédentes, dans lequel pour le rapport entre Lcover et LaxTip : L cover L axTip > 0,25
    Figure imgb0046
    .
  7. Turbocompresseur (1) selon l'une quelconque des revendications précédentes, dans lequel pour le rapport entre Lcover et LaxTip : L cover L axTip > 0,3
    Figure imgb0047
    .
  8. Turbocompresseur (1) selon l'une quelconque des revendications précédentes, dans lequel pour le rapport entre Rout et Rin : R out R in > 0,8
    Figure imgb0048
    , de préférence R out R in < 0,95
    Figure imgb0049
    , de manière particulièrement préférée 0,8 < R out R in < 0,95
    Figure imgb0050
    .
  9. Roue de turbine (12) pour un turbocompresseur (1) selon l'une quelconque des revendications précédentes, présentant un aubage de roue à aubes (121) pourvu de plusieurs aubes de turbine (122),
    caractérisée en ce que la roue de turbine (12) est réalisée de façon à satisfaire la condition suivante : L cover L axTip > 1 − Tip clr R in × 3 π 4 × 1 1 − R out R in
    Figure imgb0051
    dans lequel, par rapport à une vue méridienne de la roue de turbine (12),
    - au moins une aube de turbine (122) de la roue de turbine (12) présente un bord d'attaque d'écoulement (126) et un bord de fuite d'écoulement (127) pour le débit massique de gaz d'échappement (AM) ;
    - Rin décrit un rayon d'entrée maximal du bord d'attaque d'écoulement (126) et Rout décrit un rayon de sortie maximal du bord de fuite d'écoulement (127), respectivement par rapport à un axe de rotation (123) de la roue de turbine (12) ;
    - LaxTip décrit une longueur d'extension axiale d'un contour extérieur (128) de ladite au moins une aube de turbine (122), le contour extérieur (128) s'étendant du bord d'attaque d'écoulement (126) au bord de fuite d'écoulement (127) et est tourné vers un carter de turbine (21) environnant en cas de fonctionnement conforme ;
    - Lcover décrit une part de longueur axiale de l'extension axiale LaxTip du contour extérieur (128) dans laquelle un diamètre de la roue de turbine est supérieur à un diamètre le plus petit DA du carter de turbine à la sortie d'aube de turbine pour le débit massique de gaz d'échappement AM ;
    - Tipclr décrit une distance radiale la plus faible entre un contour de carter (211) du carter de turbine (21), qui fait face au contour extérieur (128) en cas de fonctionnement conforme, et le contour (128) par rapport à l'axe de rotation (123).
  10. Procédé de fabrication d'un turbocompresseur (1) selon l'une quelconque des revendications 1 à 8, caractérisé en ce qu'il comprend les étapes suivantes consistant à :
    - établir et/ou déterminer les paramètres du rayon d'entrée maximal Rin, du rayon de sortie maximal Rout, de la longueur d'extension axiale LaxTip, de la part de longueur axiale Lcover et de la plus faible distance radiale Tipclr de façon à satisfaire la condition suivante pour la roue de turbine (12) et le carter de turbine (21) : L cover L axTip > 1 − Tip clr R in × 3 π 4 × 1 1 − R out R in
    Figure imgb0052
    - fabriquer la roue de turbine (12) et le carter de turbine (21) à l'aide des paramètres établis au moyen de la condition.
EP18718704.2A 2017-03-30 2018-03-22 Turbocompresseur pour un moteur à combustion interne ainsi que roue de turbine Active EP3601739B1 (fr)

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PCT/EP2018/057247 WO2018177864A1 (fr) 2017-03-30 2018-03-22 Turbocompresseur pour un moteur à combustion interne ainsi que carter de turbine

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EP3940203A1 (fr) 2020-07-16 2022-01-19 BMTS Technology GmbH & Co. KG Turbine de gaz d'échappement

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DE102017205457A1 (de) 2018-10-04

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