EP1337739A1 - Variable geometry turbocharger with sliding piston - Google Patents

Variable geometry turbocharger with sliding piston

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Publication number
EP1337739A1
EP1337739A1 EP00985372A EP00985372A EP1337739A1 EP 1337739 A1 EP1337739 A1 EP 1337739A1 EP 00985372 A EP00985372 A EP 00985372A EP 00985372 A EP00985372 A EP 00985372A EP 1337739 A1 EP1337739 A1 EP 1337739A1
Authority
EP
European Patent Office
Prior art keywords
turbine
piston
fins
heat shield
compressor
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.)
Granted
Application number
EP00985372A
Other languages
German (de)
French (fr)
Other versions
EP1337739B1 (en
Inventor
Jean-Luc Hubert Honeywell Garrett SA PERRIN
Olivier Honeywell Garrett SA ESPASA
Marylène Honeywell Garrett SA RUFFINONI
Alain René Honeywell Garrett SA LOMBARD
Philippe Joseph Honeywell Garrett SA MULLER
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.)
Garrett Motion France SAS
Original Assignee
Honeywell Garrett SA
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 Honeywell Garrett SA filed Critical Honeywell Garrett SA
Publication of EP1337739A1 publication Critical patent/EP1337739A1/en
Application granted granted Critical
Publication of EP1337739B1 publication Critical patent/EP1337739B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • 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
    • 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 invention relates generally to variable geometry turbochargers. More particularly, it relates to a turbocharger comprising a sliding piston which creates a variable-nozzle turbine inlet with fins extending across the nozzle in a closed position of the piston.
  • variable geometry systems for turbochargers employ variable geometry systems for the turbine inlet nozzles to increase performance and aerodynamic efficiency.
  • variable geometry systems for turbochargers are of two types, namely, pivoting and piston fins.
  • the type with pivoting fins illustrated for example by US Patent No. 5,947,681 entitled “Pressure Balanced Dual Axle Variable Nozzle Turbocharger”, comprises a plurality of individual fins placed in the turbine inlet nozzle and which can be rotate to decrease or increase the nozzle section and the volume of fluid.
  • the piston type which is illustrated for example by US Pat. Nos. 5,214,920 and 5,231,831 both entitled “Turbocharger" and US Patent No.
  • variable geometry turbochargers of the piston type of the prior art the problem has been to obtain maximum aerodynamic performance while admitting tolerances for the cooperating surfaces, in particular for the fins and the receiving grooves which are used. in most embodiments and which are subject to temperature variations and very high mechanical stresses, and also to provide means for controlling the piston in a configuration which is easy to manufacture.
  • a turbocharger using the present invention comprises a casing having a turbine body which receives exhaust gases from an exhaust manifold of an internal combustion engine at an inlet and which has an exhaust outlet, a body of compressor having an air inlet and a first scroll, and a central body placed between the turbine body and the compressor body.
  • a turbine wheel is mounted in the turbine body to extract energy from the exhaust gas.
  • the turbine wheel is coupled to a shaft which exits the turbine body and passes through a bore in the central body, the turbine wheel comprising a substantially solid rear disc and multiple vanes.
  • a bearing mounted in the shaft bore of the central body supports the shaft for a rotational movement, and a compressor wheel is coupled to the shaft, opposite the turbine wheel, and it is contained in the compressor body.
  • a substantially cylindrical piston is concentric with the turbine wheel and it is movable parallel to an axis of turbine wheel rotation.
  • a plurality of fins extend substantially parallel to the axis of rotation, starting from a heat shield which is mounted, at the location of its outer circumference, between the turbine body and the central body and which extends radially inward towards the axis of rotation.
  • An actuator is provided for moving the piston from a first position close to the heat shield to a second position remote from the heat shield. In the first position, a radial surface of the piston is in contact with the end of the fins. In the second position, the piston is spaced from the fins so as to create a nozzle of larger section with a partial flow of exhaust gases, coming from the turbine volute, through the fins and with a partial flow through a ring open directly in the turbine.
  • Figure 1 is an elevational and sectional view of a turbocharger employing an embodiment of the invention, the piston being in the closed position
  • Figure 2 is an elevational and sectional view of the turbocharger of Figure 1, the piston being in the open position
  • Figure 3 is an elevational view in partial section of a second embodiment of the invention with a seal with staggered seals for the piston, the piston being in the closed position
  • Figure 4 is an elevational view in partial section of the embodiment of Figure 3, the piston being in the open position.
  • FIG. 1 represents an embodiment of the invention for a turbocharger 10 which comprises a turbine body 12, a central body 14 and a compressor body 16.
  • a turbine wheel 18 is coupled by a shaft 20 to a compressor wheel 22.
  • the turbine wheel converts the energy of the gases d exhaust from an internal combustion engine brought by an exhaust reader neck (not shown) to a volute 24 in the turbine body.
  • the exhaust gases expand in the turbine and exit the turbine body via an outlet 26.
  • the compressor body includes an inlet 28 and an outlet volute 30.
  • a back plate 30 is connected by bolts 34 to the compressor body.
  • the rear plate is itself fixed to the central body by means of bolts (not shown) or cast integrally from the central body.
  • a V-shaped clamp 40 and alignment pins 42 connect the turbine body to the central body.
  • a bearing 50 mounted in the bore 52 of the central body supports the rotating shaft.
  • a sleeve 58 is held between the abutment surface and the compressor wheel.
  • a rotary lining 60 such as a piston ring, provides a seal between the sleeve and the rear plate.
  • the variable geometry mechanism of the present invention comprises a substantially cylindrical piston 70 received in the body of the coil in concentric alignment with the axis of rotation of the turbine.
  • the piston is movable longitudinally i nally via a crosspiece 72, comprising three branches in the embodiment shown, which is attached to the piston and attached to an operating rod 74.
  • the operating rod is received in a ma nchon 76 which crosses the reel body and is connected to an actuator 77.
  • the neur action is mo nted on bosses of the reel body by means of support 78.
  • the piston slides in the turbine body by means of a low friction insert 82.
  • a cylindrical seal 84 is inserted between the piston and the insert.
  • the piston is movable from a closed position shown in Figure 1, in which the section of the inlet nozzle to the turbine from the volute 24 is substantially reduced. In a fully open position, a radial projection 86 of the piston abuts against a face 88 of the insert to limit the displacement of the piston.
  • Nozzle fins 90 extend from a heat shield 92. In the closed position of the piston, the fins are in contact with the face of the radial projection of the piston.
  • the outer periphery of the heat shield is held between the turbine body and the central body. The shield is configured to enter the cavity of the turbine body from the interface between the central body and the turbine body and it forms an interior wall for the inlet nozzle of the turbine.
  • Figure 2 shows the turbocharger of Figure 1 when the piston 70 is in the open position.
  • An open annular channel 94 is created between the fins and the face of the radial projection.
  • the flow of exhaust gas through the fins and the annular channel which constitutes the open nozzle is stabilized in direction by the fins.
  • the modulation of the nozzle flow can be carried out by positioning the piston at desired points between the fully open position and the fully closed position.
  • the piston operating system in the embodiment shown, is a pneumatic actuator 77 fixed to a support 78 as shown in FIGS. 1 and 2.
  • Figure 3 shows a second embodiment of the invention incorporating a piston 70a which is made from a sheet of metal or by casting a thin wall having a cross-section substantially U-shaped so as to include an outer ring 94 parallel to the direction of translation of the piston and an inner ring 96 extending until it is fixed to a plate 98 for connection to the operating rod 74.
  • the outer ring of the piston is received in a groove 100 of the turbine body, and the inner ring is received tightly by the inner circumferential wall of the outlet of the turbine body, which creates a seal with staggered seals for the piston.
  • the core of the U-shape of the piston comes into contact with the fins to define the nozzle of minimum male section.

Abstract

The invention concerns a turbocharger with a variable geometry turbine comprising a mobile cylindrical piston (70) to modify the cross-section of the input nozzle to the turbine. Vanes (90) extending from a heat shield (92) for adjusting the flow of the nozzle are contacted by the piston in a first closed position. In a second open position, the piston is spaced apart from the vanes, thereby increasing the input nozzle cross-section.

Description

TURBOCOMPRESSEUR A GEOMETRIE VARIABLE AVEC PISTON COULISSANTVARIABLE GEOMETRIC TURBOCHARGER WITH SLIDING PISTON
ARRIERE-PLAN DE L'INVENTION Domaine de l'InventionBACKGROUND OF THE INVENTION Field of the Invention
La présente invention concerne d'une manière générale des turbocompresseurs à géométrie variable. Plus particulièrement, elle vise un turbocompresseur comportant un piston coulissant qui crée une entrée de turbine à tuyère variable avec des ailettes s'étendant en travers de la tuyère dans une position fermée du piston. Description de l'Art AntérieurThe present invention relates generally to variable geometry turbochargers. More particularly, it relates to a turbocharger comprising a sliding piston which creates a variable-nozzle turbine inlet with fins extending across the nozzle in a closed position of the piston. Description of the Prior Art
Les turbocompresseurs à haut rendement emploient des systèmes à géométrie variable pour les tuyères d'entrée de la turbine afin d'augmenter les performances et le rendement aérodynamique. De façon typique, les systèmes à géométrie variable pour turbocompresseurs sont de deux types, à savoir à ailettes pivotantes et à piston. Le type à ailettes pivotantes, illustré par exemple par le brevet US N°5 947 681 intitulé "Pressure Balanced Dual Axle Variable Nozzle Turbocharger", comporte une pluralité d'ailettes individuelles placées dans la tuyère d'entrée de turbine et qu'on peut faire pivoter pour diminuer ou augmenter la section de tuyère et le volume de fluide. Le type à piston, qui est illustré par exemple par les brevets US N°5214920 et 5231 831 tous deux intitulés "Turbocharger" et le brevet US N°5 441 383 intitulé "Variable Exhaust Driven Turbochargers", emploie un piston ou une paroi cylindrique qui est déplaçable concentriquement à l'axe de rotation de la turbine pour réduire la section de l'entrée de tuyère. Dans la plupart des cas, le turbocompresseur à géométrie variable du type à piston comprend des ailettes ayant un angle d'attaque fixe par rapport au flux d'air, qui sont montées sur le piston ou sur une paroi de tuyère fixe à l'opposé du piston et qui sont reçues dans des rainures ménagées dans la surface opposée pendant le mouvement du piston.High efficiency turbochargers employ variable geometry systems for the turbine inlet nozzles to increase performance and aerodynamic efficiency. Typically, variable geometry systems for turbochargers are of two types, namely, pivoting and piston fins. The type with pivoting fins, illustrated for example by US Patent No. 5,947,681 entitled "Pressure Balanced Dual Axle Variable Nozzle Turbocharger", comprises a plurality of individual fins placed in the turbine inlet nozzle and which can be rotate to decrease or increase the nozzle section and the volume of fluid. The piston type, which is illustrated for example by US Pat. Nos. 5,214,920 and 5,231,831 both entitled "Turbocharger" and US Patent No. 5,441,383 entitled "Variable Exhaust Driven Turbochargers", employs a piston or a cylindrical wall which is movable concentrically to the axis of turbine rotation to reduce the cross-section of the nozzle inlet. In most cases, the piston type variable geometry turbocharger includes fins having a fixed angle of attack with respect to the air flow, which are mounted on the piston or on a fixed nozzle wall opposite of the piston and which are received in grooves formed in the opposite surface during the movement of the piston.
Dans les turbocompresseurs à géométrie variable du type à piston de l'art antérieur, le problème a été d'obtenir les performances aérodynamiques maximales tout en admettant des tolérances pour les surfaces coopérantes, en particulier pour les ailettes et les rainures de réception qui sont employées dans la plupart des réalisations et qui sont soumises à des variations de température et des contraintes mécaniques très élevées, et également de prévoir des moyens de commande du piston dans une configuration facile à fabriquer. RESUME DE L'INVENTIONIn variable geometry turbochargers of the piston type of the prior art, the problem has been to obtain maximum aerodynamic performance while admitting tolerances for the cooperating surfaces, in particular for the fins and the receiving grooves which are used. in most embodiments and which are subject to temperature variations and very high mechanical stresses, and also to provide means for controlling the piston in a configuration which is easy to manufacture. SUMMARY OF THE INVENTION
Un turbocompresseur utilisant la présente invention comprend un carter ayant un corps de turbine qui reçoit les gaz d'échappement d'un collecteur d'échappement d'un moteur à combustion interne à une entrée et qui comporte une sortie d'évacuation, un corps de compresseur ayant une entrée d'air et une première volute, et un corps central placé entre le corps de turbine et le corps de compresseur. Une roue de turbine est montée dans le corps de turbine pour extraire l'énergie du gaz d'échappement. La roue de turbine est accouplée à un arbre qui sort du corps de turbine et passe dans un alésage du corps central, la roue de turbine comprenant un disque arrière sensiblement plein et des aubes multiples. Un palier monté dans l'alésage d'arbre du corps central supporte l'arbre pour un mouvement de rotation, et une roue de compresseur est accouplée à l'arbre, à l'opposé de la roue de turbine, et elle est contenue dans le corps de compresseur.A turbocharger using the present invention comprises a casing having a turbine body which receives exhaust gases from an exhaust manifold of an internal combustion engine at an inlet and which has an exhaust outlet, a body of compressor having an air inlet and a first scroll, and a central body placed between the turbine body and the compressor body. A turbine wheel is mounted in the turbine body to extract energy from the exhaust gas. The turbine wheel is coupled to a shaft which exits the turbine body and passes through a bore in the central body, the turbine wheel comprising a substantially solid rear disc and multiple vanes. A bearing mounted in the shaft bore of the central body supports the shaft for a rotational movement, and a compressor wheel is coupled to the shaft, opposite the turbine wheel, and it is contained in the compressor body.
Un piston sensiblement cylindrique est concentrique à la roue de turbine et il est déplaçable parallèlement à un axe de rotation de la roue de turbine. Une pluralité d'ailettes s'étendent sensiblement parallèlement à l'axe de rotation, à partir d'un bouclier thermique qui est monté, à l'endroit de sa circonférence extérieure, entre le corps de turbine et le corps central et qui s'étend radialement vers l'intérieur, vers l'axe de rotation. Un actionneur est prévu pour déplacer le piston d'une première position proche du bouclier thermique à une deuxième position éloignée du bouclier thermique. Dans la première position, une surface radiale du piston est en contact avec l'extrémité des ailettes. Dans la deuxième position, le piston est espacé des ailettes de façon à créer une tuyère de plus grande section avec un écoulement partiel des gaz d'échappement, venant de la volute de turbine, à travers les ailettes et avec un écoulement partiel à travers un anneau ouvert directement dans la turbine.A substantially cylindrical piston is concentric with the turbine wheel and it is movable parallel to an axis of turbine wheel rotation. A plurality of fins extend substantially parallel to the axis of rotation, starting from a heat shield which is mounted, at the location of its outer circumference, between the turbine body and the central body and which extends radially inward towards the axis of rotation. An actuator is provided for moving the piston from a first position close to the heat shield to a second position remote from the heat shield. In the first position, a radial surface of the piston is in contact with the end of the fins. In the second position, the piston is spaced from the fins so as to create a nozzle of larger section with a partial flow of exhaust gases, coming from the turbine volute, through the fins and with a partial flow through a ring open directly in the turbine.
BREVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS
Les détails et aspects de la présente invention seront mieux compris à la lumière de la description détaillée ci-après et des dessins dans lesquels : la figure 1 est une vue en élévation et en coupe d'un turbocompresseur employant un mode de réalisation de l'invention, le piston étant dans la position fermée ; la figure 2 est une vue en élévation et en coupe du turbocompresseur de la figure 1, le piston étant dans la position ouverte ; la figure 3 est une vue en élévation et en coupe partielle d'un deuxième mode de réalisation de l'invention avec une étanchéité à joints décalés pour le piston, le piston étant dans la position fermée ; et la figure 4 est une vue en élévation et en coupe partielle du mode de réalisation de la figure 3, le piston étant dans la position ouverte. DESCRIPTION DETAILLEE DE L'INVENTIONThe details and aspects of the present invention will be better understood in the light of the detailed description below and of the drawings in which: Figure 1 is an elevational and sectional view of a turbocharger employing an embodiment of the invention, the piston being in the closed position; Figure 2 is an elevational and sectional view of the turbocharger of Figure 1, the piston being in the open position; Figure 3 is an elevational view in partial section of a second embodiment of the invention with a seal with staggered seals for the piston, the piston being in the closed position; and Figure 4 is an elevational view in partial section of the embodiment of Figure 3, the piston being in the open position. DETAILED DESCRIPTION OF THE INVENTION
On se reporte aux dessins. La figure 1 représente un mode de réalisation de l'invention pour un turbocompresseur 10 qui comprend un corps de turbine 12 , un corps central 14 et un corps de com presseur 16. Une roue de turbine 18 est accouplée par un arbre 20 à une roue de com presseur 22. La roue de turbine convertit l'énergie des gaz d'échappement d'un moteur à combustion interne amenés par u n col lecteur d'échappement (non représenté) à une volute 24 dans le corps de turbine. Les gaz d'échappement se détendent d ans la turbi ne et sortent du corps de turbine par une sortie 26.We refer to the drawings. FIG. 1 represents an embodiment of the invention for a turbocharger 10 which comprises a turbine body 12, a central body 14 and a compressor body 16. A turbine wheel 18 is coupled by a shaft 20 to a compressor wheel 22. The turbine wheel converts the energy of the gases d exhaust from an internal combustion engine brought by an exhaust reader neck (not shown) to a volute 24 in the turbine body. The exhaust gases expand in the turbine and exit the turbine body via an outlet 26.
Le corps de compresseur co mprend une entrée 28 et une volute de sortie 30. U ne plaque arrière 30 est reliée par des boulons 34 au corps de compresseur. La plaque arrière est elle- même fixée au corps central au moyen de boulons (non représentés) ou coulée solidairement du corps central . U n collier de serrage en V 40 et des broches d'alignement 42 relient le corps de turbi ne au corps central .The compressor body includes an inlet 28 and an outlet volute 30. A back plate 30 is connected by bolts 34 to the compressor body. The rear plate is itself fixed to the central body by means of bolts (not shown) or cast integrally from the central body. A V-shaped clamp 40 and alignment pins 42 connect the turbine body to the central body.
U n palier 50 monté dans l'alésage 52 d u corps central supporte l'arbre en rotation . U n manchon 58 est tenu entre la surface de butée et la roue de compresseur. U ne garniture rotative 60 , telle qu'un anneau de piston , assure une étanchéité entre le manchon et la plaq ue arrière.A bearing 50 mounted in the bore 52 of the central body supports the rotating shaft. A sleeve 58 is held between the abutment surface and the compressor wheel. A rotary lining 60, such as a piston ring, provides a seal between the sleeve and the rear plate.
Le mécanisme à géométrie va ri able de la présente invention comprend un piston sensi blement cyl indrique 70 reçu dans le corps de tu rbine en alignement concentrique avec l'axe de rotation de la turbine. Le piston est déplaçable longitud i nalement par l'intermédiaire d'u n croisillon 72, comportant trois branches dans le mode de réalisation représenté, q ui est attaché au piston et attaché à une tige de m anœuvre 74. La tige de manœuvre est reçue dans un ma nchon 76 qui traverse le corps de tu rbine et el le est reliée à u n actionneur 77. Dans le mode de réalisation représenté, l'action neur est mo nté sur des bossages du corps de tu rbine par l'intermédiaire d'u n support 78.The variable geometry mechanism of the present invention comprises a substantially cylindrical piston 70 received in the body of the coil in concentric alignment with the axis of rotation of the turbine. The piston is movable longitudinally i nally via a crosspiece 72, comprising three branches in the embodiment shown, which is attached to the piston and attached to an operating rod 74. The operating rod is received in a ma nchon 76 which crosses the reel body and is connected to an actuator 77. In the embodiment shown, the neur action is mo nted on bosses of the reel body by means of support 78.
Le piston coulisse dans le corps de turbine par l'intermédiaire d'un insert à faible frottement 82. Une garniture d'étanchéité cylind rique 84 est insérée entre le piston et l'insert. Le piston est déplaçable à partir d'une position fermée représentée sur la figure 1, dans laquelle la section de la tuyère d'entrée à la turbine à partir de la volute 24 est sensiblement réduite. Dans une position d'ouverture totale, une saillie radiale 86 du piston bute contre une face 88 de l'insert pour limiter le déplacement du piston.The piston slides in the turbine body by means of a low friction insert 82. A cylindrical seal 84 is inserted between the piston and the insert. The piston is movable from a closed position shown in Figure 1, in which the section of the inlet nozzle to the turbine from the volute 24 is substantially reduced. In a fully open position, a radial projection 86 of the piston abuts against a face 88 of the insert to limit the displacement of the piston.
Des ailettes de tuyère 90 s'étendent à partir d'un bouclier thermique 92. Dans la position fermée du piston, les ailettes sont en contact avec la face de la saillie radiale du piston. La périphérie extérieure du bouclier thermique est tenue entre le corps de turbine et le corps central. Le bouclier est configuré de manière à pénétrer dans la cavité du corps de turbine à partir de l'interface entre le corps central et le corps de turbine et il constitue une paroi intérieure pour la tuyère d'entrée de la turbine.Nozzle fins 90 extend from a heat shield 92. In the closed position of the piston, the fins are in contact with the face of the radial projection of the piston. The outer periphery of the heat shield is held between the turbine body and the central body. The shield is configured to enter the cavity of the turbine body from the interface between the central body and the turbine body and it forms an interior wall for the inlet nozzle of the turbine.
La figure 2 représente le turbocompresseur de la figure 1 lorsque le piston 70 est dans la position ouverte. Un canal annulaire ouvert 94 est créé entre les ailettes et la face de la saillie radiale. Le flux de gaz d'échappement à travers les ailettes et le canal annulaire qui constitue la tuyère ouverte est stabilisé en direction par les ailettes. La modulation du flux de tuyère peut être effectuée par positionnement du piston à des points désirés entre la position d'ouverture totale et la position de fermeture totale. Le système de manœuvre du piston, dans le mode de réalisation représenté, est un actionneur pneumatique 77 fixé à un support 78 comme représenté sur les figures 1 et 2.Figure 2 shows the turbocharger of Figure 1 when the piston 70 is in the open position. An open annular channel 94 is created between the fins and the face of the radial projection. The flow of exhaust gas through the fins and the annular channel which constitutes the open nozzle is stabilized in direction by the fins. The modulation of the nozzle flow can be carried out by positioning the piston at desired points between the fully open position and the fully closed position. The piston operating system, in the embodiment shown, is a pneumatic actuator 77 fixed to a support 78 as shown in FIGS. 1 and 2.
La figure 3 représente un deuxième mode de réalisation de l'invention incorporant un piston 70a qui est fabriqué à partir d'une feuille de métal ou par coulée d'une paroi mince ayant une section transversale sensiblement en U de manière à comprendre un anneau extérieur 94 parallèle à la direction de translation du piston et un anneau intérieur 96 s'étendant jusqu'à une fixation à une plaque 98 pour connexion à la tige de manœuvre 74. L'anneau extérieur du piston est reçu dans une rainure 100 du corps de turbine, et l'anneau intérieur est reçu étroitement par la paroi circonférentiel le intérieure de la sortie du corps de turbine, ce qui crée u ne étanchéité à joints décalés pour le piston . Dans la position fermée, l'âme de la forme en U du piston vient en contact avec les ailettes pour définir la tuyère de section mini male.Figure 3 shows a second embodiment of the invention incorporating a piston 70a which is made from a sheet of metal or by casting a thin wall having a cross-section substantially U-shaped so as to include an outer ring 94 parallel to the direction of translation of the piston and an inner ring 96 extending until it is fixed to a plate 98 for connection to the operating rod 74. The outer ring of the piston is received in a groove 100 of the turbine body, and the inner ring is received tightly by the inner circumferential wall of the outlet of the turbine body, which creates a seal with staggered seals for the piston. In the closed position, the core of the U-shape of the piston comes into contact with the fins to define the nozzle of minimum male section.
La figure 4 représente le mode de réalisation de la figure 3 , le piston étant dans la position ouverte et l'âme du U étant éloignée des ailettes pour obtenir l'espace annulaire l ibre précédemment décrit pour la tuyère ouverte produisant une section maximale d'entrée de tuyère . Le contact du bord de l'anneau extérieur 84 avec l'extrémité de la rain ure 100 ou , en variante, le contact de l'âme du U avec la face adjacente 88a du corps de turbine limite la course du piston . L'invention ayant été décrite en détail comme req uis par les règles de protection , des mod ifications et des substitutions aux modes de réalisation spécifiques décrits ici apparaîtront aux hommes de l'art. Ces modifications et su bstitutions entrent dans le cadre de la présente invention comme défini dans les revend ications annexées. 4 shows the embodiment of Figure 3, the piston being in the open position and the core of the U being distant from the fins to obtain the annular space ibre previously described for the open nozzle producing a maximum section of nozzle inlet. The contact of the edge of the outer ring 84 with the end of the groove 100 or, alternatively, the contact of the core of the U with the adjacent face 88a of the turbine body limits the stroke of the piston. The invention having been described in detail as received by the protection rules, modifications and substitutions to the specific embodiments described here will appear to those skilled in the art. These modifications and su bstitutions fall within the scope of the present invention as defined in the appended claims.

Claims

REVENDICATIONS
1. Turbocompresseur (10) à géométrie variable de tuyère de turbine, comprenant : un carter qui inclut un corps de turbine (12) recevant les gaz d'échappement d'un collecteur d'échappement d'un moteur à combustion interne à une entrée (24) et ayant une sortie d'échappement (26), un corps de compresseur (16) ayant une entrée d'air (28) et une première volute (30), et un corps central (14) entre le corps de turbine et le corps de compresseur ; une roue de turbine (18) montée dans le corps de turbine et extrayant l'énergie des gaz d'échappement, la dite roue de turbine étant accouplée à un arbre (20) qui sort du corps de turbine et passe dans un alésage (52) du corps central ; un palier (50) monté dans l'alésage du corps central, le dit palier supportant l'arbre en rotation ;: une roue de compresseur (22) accouplée à l'arbre à l'opposé de la roue de turbine et contenue dans le corps de compresseur ; un piston sensiblement cylindrique (70), concentrique à la roue de turbine et déplaçable parallèlement à l'axe de rotation de la roue de turbine ; un bouclier thermique (92) pris à sa circonférence extérieure entre le corps de turbine et le corps central et s'étendant radialement vers l'intérieur, vers l'axe de rotation, le dit bouclier thermique ayant une pluralité d'ailettes (90) qui sont sensiblement parallèles à l'axe de rotation ; et des moyens pour déplacer le piston (70) d'une première position proche du bouclier thermique (92) et en contact avec les ailettes (90) à une deuxième position éloignée du bouclier thermique.1. Turbocharger (10) with variable geometry of turbine nozzle, comprising: a casing which includes a turbine body (12) receiving exhaust gases from an exhaust manifold of an internal combustion engine at an inlet (24) and having an exhaust outlet (26), a compressor body (16) having an air inlet (28) and a first volute (30), and a central body (14) between the turbine body and the compressor body; a turbine wheel (18) mounted in the turbine body and extracting energy from the exhaust gases, said turbine wheel being coupled to a shaft (20) which exits the turbine body and passes through a bore (52 ) the central body; a bearing (50) mounted in the bore of the central body, the said bearing supporting the rotating shaft;: a compressor wheel (22) coupled to the shaft opposite the turbine wheel and contained in the compressor body; a substantially cylindrical piston (70), concentric with the turbine wheel and movable parallel to the axis of rotation of the turbine wheel; a heat shield (92) taken at its outer circumference between the turbine body and the central body and extending radially inwards, towards the axis of rotation, said heat shield having a plurality of fins (90) which are substantially parallel to the axis of rotation; and means for moving the piston (70) from a first position close to the heat shield (92) and in contact with the fins (90) to a second position remote from the heat shield.
2. Turbocompresseur selon la revendication 1, dans lequel le piston (70a) a une section en forme de U à paroi mince formant un anneau extérieur (94) et un anneau intérieur (96) reliés par une âme, le dit anneau extérieur étant étroitement reçu dans une rainure cylindrique (100) du corps de turbine ( 12) et le dit anneau intérieur étant en contact étroit avec une surface circonférentielle intérieure de la sortie d'échappement, les dits anneaux intérieur et extérieur agissant comme des joints d'étanchéité décalés, et la dite âme étant en contact avec les ailettes (90) lorsque le piston est dans la première position . 2. The turbocharger according to claim 1, wherein the piston (70a) has a thin-walled U-shaped section forming an outer ring (94) and an inner ring (96) connected by a core, said outer ring being closely received in a cylindrical groove (100) of the turbine body (12) and said inner ring being in close contact with an inner circumferential surface of the exhaust outlet, said rings inside and outside acting as offset seals, and said core being in contact with the fins (90) when the piston is in the first position.
EP00985372A 2000-11-30 2000-11-30 Variable geometry turbocharger with sliding piston Expired - Lifetime EP1337739B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/FR2000/003350 WO2002044527A1 (en) 2000-11-30 2000-11-30 Variable geometry turbocharger with sliding piston

Publications (2)

Publication Number Publication Date
EP1337739A1 true EP1337739A1 (en) 2003-08-27
EP1337739B1 EP1337739B1 (en) 2006-12-20

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US (1) US7024855B2 (en)
EP (1) EP1337739B1 (en)
JP (1) JP2004514840A (en)
KR (1) KR100737377B1 (en)
CN (1) CN100340742C (en)
AU (1) AU2001221812A1 (en)
CA (1) CA2423755C (en)
DE (1) DE60032523T2 (en)
HU (1) HU225776B1 (en)
MX (1) MXPA03004873A (en)
WO (1) WO2002044527A1 (en)

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Publication number Publication date
HU225776B1 (en) 2007-08-28
CA2423755A1 (en) 2002-06-06
JP2004514840A (en) 2004-05-20
AU2001221812A1 (en) 2002-06-11
DE60032523T2 (en) 2007-11-22
DE60032523D1 (en) 2007-02-01
HUP0302896A2 (en) 2003-12-29
CA2423755C (en) 2009-02-03
EP1337739B1 (en) 2006-12-20
CN100340742C (en) 2007-10-03
WO2002044527A1 (en) 2002-06-06
CN1454285A (en) 2003-11-05
KR20030076979A (en) 2003-09-29
MXPA03004873A (en) 2005-02-14
KR100737377B1 (en) 2007-07-09
US20040025504A1 (en) 2004-02-12
US7024855B2 (en) 2006-04-11

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