EP3741960B1 - Procédé de fabrication d'un ensemble bague de buse à double aube pour un turbocompresseur - Google Patents

Procédé de fabrication d'un ensemble bague de buse à double aube pour un turbocompresseur Download PDF

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Publication number
EP3741960B1
EP3741960B1 EP20165134.6A EP20165134A EP3741960B1 EP 3741960 B1 EP3741960 B1 EP 3741960B1 EP 20165134 A EP20165134 A EP 20165134A EP 3741960 B1 EP3741960 B1 EP 3741960B1
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EP
European Patent Office
Prior art keywords
vane
ring
side wall
vanes
passages
Prior art date
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Active
Application number
EP20165134.6A
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German (de)
English (en)
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EP3741960A1 (fr
Inventor
Filip ECKL
Petr PRIBYL
Petr SKARA
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Garrett Transportation I Inc
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Garrett Transportation I Inc
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Priority claimed from US16/421,703 external-priority patent/US11248488B2/en
Application filed by Garrett Transportation I Inc filed Critical Garrett Transportation I Inc
Publication of EP3741960A1 publication Critical patent/EP3741960A1/fr
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Publication of EP3741960B1 publication Critical patent/EP3741960B1/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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 present disclosure relates to turbochargers in which a turbine of the turbocharger is driven by exhaust gas from a reciprocating engine.
  • the invention relates more particularly to methods for making twin-vaned nozzle ring assemblies for a turbine nozzle of a turbocharger.
  • An exhaust gas-driven turbocharger is a device used in conjunction with an internal combustion engine for increasing the power output of the engine by compressing the air that is delivered to the air intake of the engine to be mixed with fuel and burned in the engine.
  • a turbocharger comprises a compressor wheel mounted on one end of a shaft in a compressor housing and a turbine wheel mounted on the other end of the shaft in a turbine housing.
  • the turbine housing is formed separately from the compressor housing, and there is yet another center housing connected between the turbine and compressor housings for containing bearings for the shaft.
  • the turbine housing defines a generally annular chamber that surrounds the turbine wheel and that receives exhaust gas from an engine.
  • the turbine assembly includes a nozzle that leads from the chamber into the turbine wheel.
  • the exhaust gas flows from the chamber through the nozzle to the turbine wheel and the turbine wheel is driven by the exhaust gas.
  • the turbine thus extracts power from the exhaust gas and drives the compressor.
  • the compressor receives ambient air through an inlet of the compressor housing and the air is compressed by the compressor wheel and is then discharged from the housing to the engine air intake.
  • the scroll or chamber that surrounds the turbine wheel and into which the exhaust gases are fed is divided into a plurality of scrolls that succeed one another in the axial direction, each scroll occupying substantially a full circumference, such as shown in Figure 4 of U.S. Patent No. 4,027,994 .
  • Meridional division of the turbine housing is advantageous from a shaft motion point of view, but the exhaust gas flow from each scroll impinges on less than the full axial width of the turbine blade leading edges, which negatively affects turbine efficiency because of mixing losses.
  • Documents cited during prosecution include EP2025897A2 and US2013/000300 A1 .
  • the present disclosure relates to turbochargers having turbine housings of the meridionally divided type.
  • the present invention relates to a turbocharger having a meridionally divided scroll, and particularly relates to methods for making a twin-vaned nozzle ring that allows the separate exhaust gas streams from the two scrolls to be blown onto the turbine wheel in an interleaved fashion about the circumference of the wheel.
  • a method for making a twin-vaned nozzle ring according to claim 1 is presented.
  • nozzle ring assemblies made in accordance with the method of the invention can mitigate the shaft motion and mixing-loss issues that can affect some prior-art turbines of the sector-divided and meridionally divided types.
  • Nozzle ring assemblies made in accordance with the invention can maintain good flow isolation between the two streams of exhaust gas all the way to the turbine wheel, thereby taking full advantage of utilization and separation of exhaust manifold pressure pulses.
  • first and second vane passages there can be symmetry between the first and second vane passages in terms of them having substantially equal respective flow areas.
  • the flow area of the first vane passages can differ from the flow area of the second vane passages so that one scroll contributes a greater fraction of the total exhaust gas flow than does the other scroll, while at the same time the volumes of the first and second scrolls optionally can be equal.
  • first vane passages can be configured so that each first exhaust gas jet impinges on a full extent of the turbine blade leading edges, and similarly the second vane passages can be configured so that each second exhaust gas jet impinges on the full extent of the turbine blade leading edges. In other examples, each of the first and second vane passages can be configured so that the first as well as the second exhaust gas jets impinge on less than the full extent of the leading edges.
  • the second side wall can include a plurality of depressed vane receptacles in a face of the second side wall that confronts the distal face of the second vane ring, each said depressed vane receptacle receiving a distal end of a respective second vane.
  • the nozzle ring can be made by an injection molding process, one embodiment of which is a metal injection molding (MIM) process.
  • MIM metal injection molding
  • each side wall and the two opposite distal faces of the nozzle ring are provided to have pin receptacles, the pin receptacles in each side wall being aligned with corresponding pin receptacles in the respective face of the nozzle ring. Pins are press-fit into the pin receptacles in each face of the nozzle ring and into the pin receptacles of each side wall to complete the assembly.
  • a method of making a twin-vaned nozzle ring assembly according to claim 7 is presented.
  • a method for making a twin-vaned nozzle ring assembly according to claim 9 is presented. The pins are inserted into the pin receptacles in the side walls and then are affixed therein, such as by riveting.
  • FIG. 1 A turbocharger 10 suitable for employing a nozzle ring assembly made in accordance with the present invention is shown in FIG. 1 .
  • the turbocharger includes a compressor wheel or impeller 14 disposed in a compressor housing 16 and mounted on one end of a rotatable shaft 18.
  • the shaft is supported in bearings 19 mounted in a center housing 20 of the turbocharger.
  • the shaft 18 is rotated by a turbine wheel 22 mounted on the other end of the shaft 18 from the compressor wheel, thereby rotatably driving the compressor wheel, which compresses air drawn in through the compressor inlet and delivers the compressed air to a volute 21, which collects the compressed air for supply to the intake of an internal combustion engine (not shown) for boosting the performance of the engine.
  • the turbocharger also includes a turbine housing 24 that houses the turbine wheel 22.
  • a turbine housing 24 that houses the turbine wheel 22.
  • Pulse separation wherein the cylinders of the engine are divided into a plurality of groups, and the pulses from each group of cylinders are substantially isolated from those of the other groups by having independent exhaust passages for each group.
  • pulse separation it is desired to minimize the communication or "cross talk" between the separate groups of cylinders.
  • the turbine housing typically has a divided scroll, comprising two separate scrolls that respectively receive separate streams of exhaust gas.
  • the turbine housing 24 defines a meridionally divided scroll comprising a first scroll 26a and a second scroll 26b, which are separated from each other by a divider wall 27.
  • the second scroll succeeds the first scroll in the axial direction of the turbocharger, and each scroll receives exhaust gas via a separate exhaust gas inlet defined by the turbine housing.
  • the two streams of exhaust gas are isolated from each other all the way to the turbine wheel 22, via a nozzle ring assembly 30 that separately directs the two streams of exhaust gas onto the turbine wheel.
  • the nozzle ring assembly is disposed within the turbine housing 24 adjacent to the center housing 20.
  • the nozzle ring assembly 30 defines a first vane ring 40 comprising first vanes 42 circumferentially spaced about a circumference of the nozzle ring, and a second vane ring 50 comprising second vanes 52 circumferentially spaced about the circumference of the nozzle ring.
  • the first ring 40 defines first vane passages 44 between circumferentially successive first vanes 42.
  • the second ring 50 defines second vane passages 54 between circumferentially successive second vanes 52.
  • the first vane passages 44 are circumferentially staggered relative to the second vane passages 54.
  • the array of second vanes 52 is "clocked" circumferentially about the nozzle ring axis relative to the array of first vanes 42, by an angular amount that is less than an angular spacing between adjacent first vanes.
  • the second vane passages are circumferentially staggered from the first vane passages by approximately half of a circumferential spacing between the leading edge of one first vane 42 and the leading edge of the next first vane 42 in the circumferential direction.
  • Fluid isolation of the two sets of vane passages 44 and 54 is accomplished by a partition 49 comprising a generally annular wall, wherein ends of the first vanes 42 are joined to one face of the partition 49 and ends of the second vanes 52 are joined to the opposite face of the partition.
  • the nozzle ring assembly 30 includes a first end wall 46 and a second end wall 56.
  • the first end wall 46 is axially spaced from the partition 49, and the opposite ends of the first vanes 42 from the partition are joined to the first end wall.
  • the second end wall 56 is axially spaced on the other side of the partition, and the opposite ends of the second vanes 52 from the partition are joined to the second end wall.
  • the nozzle ring can be provided with an anti-rotation feature, or a plurality of such features.
  • the anti-rotation feature can comprise one or more pins 32 ( FIG. 1 ).
  • the nozzle ring assembly can define receptacles in the second end wall 56 (or alternatively, or additionally, in the first end wall 46), which align with corresponding receptacle(s) in the turbine housing 24, and each pair of aligned receptacles can be kept in alignment by one of said anti-rotation pins 32.
  • Other types of anti-rotation features are possible in the practice of the invention, examples of which include but are not limited to radially oriented pins engaged in holes or slots in the turbine housing, integral features such as protuberances formed on the nozzle ring assembly for engaging corresponding slots or notches in the turbine housing, and the like.
  • the radially innermost extremity of the divider wall 27 of the turbine housing 24 is adjacent to a radially outer periphery of the partition 49 of the nozzle ring assembly 30 as best seen in FIG. 1 .
  • the interface between the divider wall and the nozzle ring can be sealed with a seal (e.g., an O-ring or any other suitable type of seal).
  • a seal e.g., an O-ring or any other suitable type of seal.
  • the first vane passages 44 are positioned to receive exhaust gas from only the first scroll 26a and an exit from each first vane passage 44 directs a first exhaust gas jet onto the turbine blade leading edges.
  • the second vane passages 54 are positioned to receive exhaust gas from only the second scroll 26b and an exit from each second vane passage 54 directs a second exhaust gas jet onto the turbine blade leading edges.
  • the turbine blade leading edges receive the first and second exhaust gas jets, respectively, from the first and second vane passages 44 and 54 in interleaved fashion about a circumference of the turbine wheel. That is, one circumferential sector of the wheel receives a first exhaust gas jet from a first vane passage, an adjacent circumferential sector receives a second exhaust gas jet from a second vane passage, the next circumferential sector receives a first exhaust gas jet from the next adjacent first vane passage, and so forth in alternating or interleaved fashion about the entire circumference of the wheel.
  • the nozzle ring assembly in accordance with embodiments of the invention is able to mitigate some of the drawbacks of both meridionally divided and sector-divided turbine housing designs according to the prior art.
  • the out-of-phase pulses directed against the turbine wheel from the two 180-degree sectors can induce undesired turbocharger shaft motion.
  • the nozzle ring assembly of the invention distributes the out-of-phase pulses evenly about the turbine wheel circumference, thereby tending to reduce or eliminate such excessive shaft motion.
  • meridionally divided turbine housings because each scroll feeds exhaust gas to only about half of the width of the turbine blade leading edges, substantial mixing losses can occur, adversely affecting turbine efficiency.
  • the nozzle ring assembly according to embodiments of the invention can mitigate both the shaft-motion issue and the mixing-loss issue because the two scrolls feed exhaust gas alternately (i.e., in interleaved fashion) about the entire circumference (and in some embodiments can also blow exhaust gas on the full extent of the turbine blade leading edges).
  • the nozzle ring assembly provides the ability to control the flow split between the two scrolls. For example, an uneven or asymmetric flow split can be achieved by sizing the vane passages for one scroll smaller than the vane passages for the other scroll. In such case, it may be advantageous for the scrolls to be of equal volume.
  • the shapes of the entrance and exit sides of the vane passages 44 and 54 can be selected by the designer.
  • the vane passage exits can be generally rectangular; in other embodiments they can be oval.
  • the entrance of a given vane passage does not necessarily have to have a shape like that of the exit of the passage.
  • a vane passage entrance can be rectangular and the exit can be round or oval, or vice versa.
  • the shapes of the vane passage exits can differ between the two scrolls.
  • the vane passage exits for one scroll can be rectangular and the vane passage exits for the other scroll can be oval and smaller in flow area than the rectangular exits.
  • the second vane passages 54 are circumferentially staggered relative to the first vane passages 44 such that there is no circumferential overlap between a given second exhaust gas jet and the neighboring first exhaust gas jet.
  • the invention is not limited in this sense, and in other (non-illustrated) embodiments the vanes can be configured such that there is some circumferential overlap between the respective first exhaust gas jets and second exhaust gas jets.
  • each of the first and second vane rings can blow exhaust gas on less than the full width or extent of the turbine blade leading edges, and in that case there can be overlap in the axial direction (and optionally in the circumferential direction also) between the first exhaust gas jets and the second exhaust gas jets.
  • the present invention relates particularly to methods for making the nozzle ring assembly 30 such as shown in FIG. 2 .
  • the nozzle ring assembly comprises three main components as shown in FIG. 3 : a nozzle ring 60 defining the vanes, a first side wall 46, and a second side wall 56. These three components are manufactured as separate parts, which are subsequently assembled to form the nozzle ring assembly 30 as described below.
  • the nozzle ring 60 can be made by an injection molding process, one embodiment of which is a metal injection molding (MIM) process.
  • MIM metal injection molding
  • the nozzle ring 60 includes the first vane ring 40 as previously described, comprising first vanes 42 circumferentially spaced about a circumference of the nozzle ring, and includes the second vane ring 50 comprising second vanes 52 circumferentially spaced about the circumference of the nozzle ring.
  • the first and second vane rings are axially spaced and integrally joined to each other (and to the intervening partition 49).
  • the first vanes 42 are circumferentially offset from the second vanes 52
  • the first vane passage entrances 44 are axially spaced apart from the second vane passage entrances 54 as shown in FIGS.
  • first vane passage exits are radially aligned with the second vane passage exits (i.e., the first and second vane passage exits are not axially spaced apart, but rather occupy substantially the same axial extent) as shown in FIG. 1 , and they are circumferentially interleaved with one another.
  • the first side wall 46 is an annular (or ring-shaped) part whose axially outer face is generally planar.
  • the outer diameter (OD) of the first side wall is substantially equal to a maximum diameter of the first vanes 42 at their leading edges (see FIG. 2 ), and the inner diameter (ID) of the first side wall is substantially equal to a minimum diameter of the first vanes at their trailing edges.
  • An axial thickness of the first side wall is relatively smaller at the OD and increases in the radially inward direction, having substantially a maximum thickness at the ID.
  • the inner face of the first side wall does not extend radially but rather is inclined with respect to the radial direction.
  • the inner face defines a plurality of depressed vane receptacles 47 therein, each said depressed vane receptacle being configured to receive a distal end of a respective one of the first vanes 42.
  • the depressed vane receptacles 47 mitigate or eliminate exhaust gas leakage between the distal ends of the first vanes and the inner face of the first end wall 46.
  • the second side wall 56 is substantially a mirror image of the first side wall, its inner face defining a plurality of depressed vane receptacles 57 for receiving distal ends of the second vanes 52, but the depressed vane receptacles 57 are circumferentially offset or "clocked" relative to the vane receptacles 47, corresponding to how the second vanes 52 are clocked relative to the first vanes 42 as previously described.
  • the depressed vane receptacles 57 mitigate or eliminate exhaust gas leakage between the distal ends of the second vanes and the inner face of the second end wall 56.
  • the nozzle ring 60 defines a first pin receptacle 61 in the distal end of each of a plurality of circumferentially spaced first vanes 42, the illustrated embodiment showing three such first pin receptacles 61 ( FIGS. 4A and 4B ).
  • Corresponding pin receptacles 48 are defined in the first side wall 46 ( FIGS. 5A and 5B ), each pin receptacle 48 in the first side wall being aligned with a corresponding pin receptacle 61 in the nozzle ring 60.
  • the nozzle ring defines a second pin receptacle 62 in the distal end of each of a plurality of circumferentially spaced second vanes 52, there being three such second pin receptacles 62 in the illustrated embodiment ( FIGS. 4A and 4B ).
  • Corresponding pin receptacles 58 are defined in the second side wall 56 ( FIGS. 5A and 5B ).
  • the first side wall 46 is affixed to one side of the nozzle ring 60 by first pins P1 that are press-fit into the pin receptacles 48 in the first side wall and into the first pin receptacles 61 in the nozzle ring as been seen in FIG. 8 .
  • the second side wall 56 is affixed to the other side of the nozzle ring by second pins P2 that are press-fit into the pin receptacles 58 in the second side wall and into the second pin receptacles 62 in the nozzle ring as best seen in FIG. 7 , thereby completing the assembly of the nozzle ring assembly 30 as shown in FIG. 2 .
  • FIGS. 9A, 9B , 10, 10A, 11, and 11A A second embodiment of the invention is illustrated in FIGS. 9A, 9B , 10, 10A, 11, and 11A .
  • the second embodiment is generally similar to the first embodiment, except that the first pins P1 and second pins P2 are integral formations of the nozzle ring 60, as illustrated in FIGS. 9A and 9B .
  • the first pins P1 are inserted into the pin receptacles 48 in the first side wall 46 ( FIG. 11 ) and then are affixed therein, such as by riveting ( FIG. 11A ).
  • the second pins P2 are inserted into the pin receptacles 58 in the second side wall 56 ( FIG. 10 ) and then are affixed therein, such as by riveting ( FIG. 10A ).

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Claims (10)

  1. Procédé de fabrication d'un ensemble bague de buse à double aube pour une buse de turbine d'un turbocompresseur, le procédé comprenant les étapes de :
    (a) fournir une première paroi latérale (46) en tant qu'une partie annulaire, dans lequel fournir la première paroi latérale en tant qu'une partie annulaire comprend de fournir la première paroi latérale pour inclure une pluralité de réceptacles d'aubes enfoncés (47) dans une face de la première paroi latérale qui confronte une face distale d'une première bague d'aubes, chaque dit réceptacle d'aube enfoncé étant configuré pour recevoir une extrémité distale d'une première aube respective ;
    (b) de fournir une seconde paroi latérale (56) en tant qu'une partie annulaire, la seconde paroi latérale étant formée séparément de la première paroi latérale ;
    (c) de fournir une bague de buse (60) séparément des première et seconde parois latérales, dans lequel la bague de buse est prévue pour avoir la première bague d'aubes (40) comprenant la pluralité de premières aubes (42) espacées de manière circonférentielle sur une circonférence de la bague de buse et est prévue pour avoir une seconde bague d'aubes (50) comprenant une pluralité de secondes aubes (52) espacées de manière circonférentielle sur la circonférence de la bague de buse, les première et secondes bagues d'aubes étant espacées axialement et jointes intégralement l'une à l'autre, la première bague d'aubes définissant une pluralité de premiers passages d'aube entre des premières aubes successives de manière circonférentielle, la seconde bague d'aubes définissant une pluralité de seconds passages d'aube entre des secondes aubes successives de manière circonférentielle, dans lequel chacun des premiers passages d'aube présente une entrée de premier passage d'aube et une sortie de premier passage d'aube, dans lequel chacun des seconds passages d'aube présente une entrée de second passage d'aube et une sortie de second passage d'aube, dans lequel la pluralité de premières aubes sont décalées de manière circonférentielle de la pluralité de secondes aubes, la pluralité d'entrées de premiers passages d'aube sont espacées axialement de la pluralité d'entrées de seconds passages d'aube, et la pluralité de premières sorties de passage d'aubes sont alignées radialement avec et intercalées de manière circonférentielle avec la pluralité de secondes sorties de passage d'aube, et dans lequel la pluralité de premiers et seconds passages d'aube sont isolés fluidiquement l'un de l'autre par une séparation (49), la séparation comprenant une paroi généralement annulaire, dans lequel des extrémités de la pluralité de premières aubes sont jointes à une face de la séparation et des extrémités de la pluralité de secondes aubes sont jointes à la face opposée de la séparation ; et
    (d) de joindre la première paroi latérale à une face distale de la première bague d'aubes, et de joindre la seconde paroi latérale à une face distale de la seconde bague d'aubes.
  2. Procédé selon la revendication 1, dans lequel l'étape (b) comprend de fournir la seconde paroi latérale pour inclure une pluralité de réceptacles d'aube enfoncés dans une face de la seconde paroi latérale qui confronte la face distale de la seconde bague d'aubes, chaque dit réceptacle d'aube enfoncé recevant une extrémité distale d'une seconde aube respective.
  3. Procédé selon l'une quelconque revendication précédente, dans lequel l'étape (c) comprend de fabriquer la bague de buse par un procédé de moulage par injection.
  4. Procédé selon la revendication 3, dans lequel le procédé de moulage par injection comprend un procédé de moulage par injection de métal (MIM).
  5. Procédé selon l'une quelconque revendication précédente, dans lequel la première paroi latérale et la première bague d'aubes sont prévues chacune pour définir une pluralité de réceptacles de broche (48) espacés de manière circonférentielle, les réceptacles de broche de la première paroi latérale étant alignés avec les réceptacles de broche de la première bague d'aubes, et dans lequel l'étape (d) comprend d'ajuster par serrage des broches dans les réceptacles de broches de la première bague d'aubes et dans les réceptacles de broche de la première paroi latérale.
  6. Procédé selon l'une quelconque revendication précédente, dans lequel la seconde paroi latérale et la seconde bague d'aubes sont prévues chacune pour définir une pluralité de réceptacles de broche (58) espacés de manière circonférentielle, les réceptacles de broche de la seconde paroi latérale étant alignés avec les réceptacles de broche de la seconde bague d'aubes, et dans lequel l'étape (d) comprend d'ajuster par serrage des broches dans les réceptacles de broches de la seconde bague d'aubes et dans les réceptacles de broche de la seconde paroi latérale.
  7. Procédé de fabrication d'un ensemble bague de buse à double aube pour une buse de turbine d'un turbocompresseur, le procédé comprenant les étapes de :
    (a) fournir une première paroi latérale (46) en tant qu'une partie annulaire ;
    (b) fournir une seconde paroi latérale (56) en tant qu'une partie annulaire, la seconde paroi latérale étant formée séparément de la première paroi latérale ;
    (c) fournir une bague de buse (60) séparément des première et seconde parois latérales, dans lequel la bague de buse est prévue pour avoir une première bague d'aubes (40) comprenant une pluralité de premières aubes (42) espacées de manière circonférentielle sur une circonférence de la bague de buse et est prévue pour avoir une seconde bague d'aubes (50) comprenant une pluralité de secondes aubes (52) espacées de manière circonférentielle sur la circonférence de la bague de buse, les première et secondes bagues d'aubes étant espacées axialement et jointes intégralement l'une à l'autre, la première bague d'aubes définissant une pluralité de premiers passages d'aube entre des premières aubes successives de manière circonférentielle, la seconde bague d'aubes définissant une pluralité de seconds passages d'aube entre des secondes aubes successives de manière circonférentielle, dans lequel chacun des premiers passages d'aube présente une entrée de premier passage d'aube et une sortie de premier passage d'aube, dans lequel chacun des seconds passages d'aube présente une entrée de second passage d'aube et une sortie de second passage d'aube, dans lequel la pluralité de premières aubes sont décalées de manière circonférentielle de la pluralité de secondes aubes, la pluralité d'entrées de premiers passages d'aube sont espacées axialement de la pluralité d'entrées de seconds passages d'aube, et la pluralité de premières sorties de passage d'aubes sont alignées radialement avec et intercalées de manière circonférentielle avec la pluralité de secondes sorties de passage d'aube, et dans lequel la pluralité de premiers et seconds passages d'aube sont isolés fluidiquement l'un de l'autre par une séparation (49), la séparation comprenant une paroi généralement annulaire, dans lequel des extrémités de la pluralité de premières aubes sont jointes à une face de la séparation et des extrémités de la pluralité de secondes aubes sont jointes à la face opposée de la séparation ; et
    (d) de joindre la première paroi latérale à une face distale de la première bague d'aubes, et de joindre la seconde paroi latérale à une face distale de la seconde bague d'aubes ;
    dans lequel la première bague aube inclut une pluralité de broches (P1) espacées de manière circonférentielle faisant saillie de la face distale de la première bague d'aubes, et la première paroi latérale est prévue pour inclure une pluralité de réceptacles de broche espacés de manière circonférentielle, et dans lequel l'étape (d) comprend d'insérer les broches de la première bague d'aubes dans les réceptacles de broche de la première paroi latérale et de fixer les broches à l'intérieur.
  8. Procédé selon la revendication 7, dans lequel l'étape de fixer les broches dans les réceptacles de broches comprend de riveter les broches.
  9. Procédé de fabrication d'un ensemble bague de buse à double aube pour une buse de turbine d'un turbocompresseur, le procédé comprenant les étapes de :
    (a) fournir une première paroi latérale (46) en tant qu'une partie annulaire,
    (b) fournir une seconde paroi latérale (56) en tant qu'une partie annulaire, la seconde paroi latérale étant formée séparément de la première paroi latérale ;
    (c) fournir une bague de buse (60) séparément des première et seconde parois latérales, dans lequel la bague de buse est prévue pour avoir une première bague d'aubes (40) comprenant une pluralité de premières aubes (42) espacées de manière circonférentielle sur une circonférence de la bague de buse et est prévue pour avoir une seconde bague d'aubes (50) comprenant une pluralité de secondes aubes (52) espacées de manière circonférentielle sur la circonférence de la bague de buse, les première et secondes bagues d'aubes étant espacées axialement et jointes intégralement l'une à l'autre, la première bague d'aubes définissant une pluralité de premiers passages d'aube entre des premières aubes successives de manière circonférentielle, la seconde bague d'aubes définissant une pluralité de seconds passages d'aube entre des secondes aubes successives de manière circonférentielle, dans lequel chacun des premiers passages d'aube présente une entrée de premier passage d'aube et une sortie de premier passage d'aube, dans lequel chacun des seconds passages d'aube présente une entrée de second passage d'aube et une sortie de second passage d'aube, dans lequel la pluralité de premières aubes sont décalées de manière circonférentielle de la pluralité de secondes aubes, la pluralité d'entrées de premiers passages d'aube sont espacées axialement de la pluralité d'entrées de seconds passages d'aube, et la pluralité de premières sorties de passage d'aubes sont alignées radialement avec et intercalées de manière circonférentielle avec la pluralité de secondes sorties de passage d'aube, et dans lequel la pluralité de premiers et seconds passages d'aube sont isolés fluidiquement l'un de l'autre par une séparation (49), la séparation comprenant une paroi généralement annulaire, dans lequel des extrémités de la pluralité de premières aubes sont jointes à une face de la séparation et des extrémités de la pluralité de secondes aubes sont jointes à la face opposée de la séparation ; et
    (d) de joindre la première paroi latérale à une face distale de la première bague d'aubes, et de joindre la seconde paroi latérale à une face distale de la seconde bague d'aubes ;
    dans lequel la seconde bague d'aubes inclut une pluralité de broches (P2) espacées de manière circonférentielle faisant saillie de la face distale de la seconde bague d'aubes, et la seconde paroi latérale est prévue pour inclure une pluralité de réceptacles de broche espacés de manière circonférentielle, et dans lequel l'étape (d) comprend d'insérer les broches de la seconde bague d'aubes dans les réceptacles de broche de la seconde paroi latérale et de fixer les broches à l'intérieur.
  10. Procédé selon la revendication 9, dans lequel l'étape de fixer les broches dans les réceptacles de broches comprend de riveter les broches.
EP20165134.6A 2019-05-24 2020-03-24 Procédé de fabrication d'un ensemble bague de buse à double aube pour un turbocompresseur Active EP3741960B1 (fr)

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US16/421,703 US11248488B2 (en) 2019-03-12 2019-05-24 Method for making a twin-vaned nozzle ring assembly for a turbocharger with twin-scroll turbine housing for directing exhaust gases from each scroll onto turbine wheel in interleaved fashion

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US11530615B1 (en) * 2022-03-01 2022-12-20 Garrett Transportation I Inc. Method for constructing a fixed-vane ring for a nozzle of a turbocharger turbine

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US4027994A (en) 1975-08-08 1977-06-07 Roto-Master, Inc. Partially divided turbine housing for turbochargers and the like
DE19918232C2 (de) 1999-04-22 2001-03-01 Daimler Chrysler Ag Mehrzylindriger Verbrennungsmotor mit einem Abgasturbolader
US7428814B2 (en) * 2006-03-08 2008-09-30 Melvin Hess Pedersen Turbine assemblies and related systems for use with turbochargers
US8123470B2 (en) * 2007-08-10 2012-02-28 Honeywell International Inc. Turbine assembly with semi-divided nozzle and half-collar piston
US8857178B2 (en) * 2011-06-28 2014-10-14 Caterpillar Inc. Nozzled turbocharger turbine and associated engine and method
DE102011120553A1 (de) * 2011-12-08 2013-06-13 Daimler Ag Turbine für einen Abgasturbolader
DE102012202907B4 (de) * 2012-02-27 2018-09-20 Continental Automotive Gmbh Abgasturbolader mit relativ zueinander verdrehbaren Leitgitterringen
DE112013006014T5 (de) * 2013-01-14 2015-09-03 Borgwarner Inc. Geteilter Düsenring zum Steuern von AGR und Abgasdurchsatz
US9157396B2 (en) * 2013-05-17 2015-10-13 Caterpillar Inc. Nozzled turbine
GB2562501B (en) * 2017-05-16 2021-12-29 Cummins Ltd Insert element for a turbine of a turbomachine

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