EP1301689A1 - Sliding vane turbocharger with graduated vanes - Google Patents

Sliding vane turbocharger with graduated vanes

Info

Publication number
EP1301689A1
EP1301689A1 EP00954699A EP00954699A EP1301689A1 EP 1301689 A1 EP1301689 A1 EP 1301689A1 EP 00954699 A EP00954699 A EP 00954699A EP 00954699 A EP00954699 A EP 00954699A EP 1301689 A1 EP1301689 A1 EP 1301689A1
Authority
EP
European Patent Office
Prior art keywords
turbine
piston
casing
fins
heat shield
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
EP00954699A
Other languages
German (de)
French (fr)
Other versions
EP1301689B1 (en
Inventor
Alain René AlliedSignal Turbo SA LOMBARD
Jean-Luc Hubert AlliedSignal Turbo SA PERRIN
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 EP1301689A1 publication Critical patent/EP1301689A1/en
Application granted granted Critical
Publication of EP1301689B1 publication Critical patent/EP1301689B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • 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 generally relates to turbochargers with variable geometry. More specifically, a turbocharger is provided having a variable nozzle turbine inlet with sliding fins, with the fins entering through a slotted sheet heat shield suspended in the turbine housing and the fins having a stepped shape to ensure hermetic closure against the surface of the heat shield. Description of related art:
  • High efficiency turbochargers use variable geometry systems for turbine nozzle inlets to increase performance and efficiency aerodynamic.
  • Variable geometry systems for turbochargers have typically been of two types: rotary vane and piston.
  • the rotary vane type exemplified in US Patent Number 5,947,681, titled PRESSURE BALANCED DUAL AXLE VARIABLE NOZZLE TURBOCHARGER provides a plurality of individual vanes placed in the turbine inlet nozzle which can rotate to reduce or increase the area of the nozzle and the flow volume.
  • the piston type which is exemplified in US patents 5,214,920 and 5,231,831 both titled TURBOCHARGER APPARATUS, and U.S.
  • patent number 5,441,383 titled VARIABLE EXHAUST DRIVEN TURBOCHARGERS uses a cylindrical piston or wall which is displaceable concentrically with the axis of rotation of the turbine to reduce the area of the nozzle inlet.
  • the piston type variable geometry turbocharger incorporates fins having a fixed angle of attack with respect to the air flow, which are mounted either on the piston or on a fixed nozzle wall opposite the piston and which enter slots in the opposite surface during the movement of the piston.
  • variable geometry turbochargers of. piston type of the prior art the challenge has been to maximize the aerodynamic performance balanced by the tolerancing of the contact surfaces, especially the fins and receiving slots which are subjected to an extreme temperature variation and to mechanical stress, as well as providing, means for actuating the piston in a configuration which can be easily manufactured.
  • a turbocharger incorporating the present invention has a carcass having a turbine casing receiving exhaust gas from an exhaust manifold of an internal combustion engine at an intake and having an exhaust outlet, a casing compressor having an air intake and a first volute, and a central casing through the turbine casing and the compressor casing.
  • a turbine wheel is carried in the turbine casing to extract energy from the exhaust gas.
  • the turbine wheel is connected to a shaft which extends from the turbine housing through a shaft bore in the central housing and the turbine wheel has a substantially complete rear disc and multiple blades.
  • a bearing mounted in the shaft bore of the central casing supports the shaft for the rotary movement and a paddle wheel is connected to the shaft opposite the turbine wheel and enclosed in the compressor casing.
  • a substantially cylindrical piston is concentric with the turbine wheel and displaceable parallel to an axis of rotation of the turbine wheel.
  • a plurality of fins extend substantially 'parallel to the axis of rotation from a first end of the piston close to the rear disc.
  • a heat shield is engaged at its outer circumference between the turbine casing and the central casing and extends radially inward towards the axis of rotation.
  • the heat shield has a plurality of slots receiving the fins.
  • An actuator is provided to move the piston from a first position in which the first end is near the heat shield to a second position in which the first end is away from the screen thermal.
  • the vanes have a first portion sized to be 'received in the slots and a second portion or step, between the first piston and dimensioned to engage the surface of the heat shield and cover the slot with the piston in the first position.
  • FIG.l is an elevational view in cross section of a turbocharger using an embodiment of the invention
  • FIG.2 is a top view of the heat shield
  • FIG.3 is a bottom view of the piston with the fins attached
  • FIG.4 is a side view of one of the fins
  • FIG.5a is a partial side view of the turbocharger incorporating the present invention showing the detail of the step engagement of the fins of the heat shield with the piston in the closed position
  • FIG.5b is a partial side view of the turbocharger incorporating the present invention showing the detail of the step engagement of the fins of the heat shield with the piston in the open position
  • FIG. ⁇ a is a bottom view of the heat shield showing in broken lines the imprint of the step on the fins which closes the slots
  • FIG. ⁇ b is a detailed view of an alternative embodiment of the blade imprint . , and. of a step with the line of the step cord at an angle with respect to the line of the blade of the blade.
  • FIG. 1 shows an embodiment of the invention for a turbocharger 10 which incorporates a turbine casing 12, a central casing 14 and a compressor casing 16.
  • a turbine wheel 18 is connected by a shaft 20 to a compressor wheel 22.
  • the turbine wheel converts the energy of the exhaust gas from an internal combustion engine supplied from an exhaust manifold (not shown) to a volute 24 in the turbine casing
  • the exhaust gas is expanded through the turbine and leaves the turbine casing via an outlet 26.
  • the compressor casing incorporates an inlet 28 and an outlet volute 30.
  • a rear plate 32 is connected by bolts 34 to the compressor casing.
  • the backplate is, in turn, attached to the center shell with bolts (not shown).
  • a first ring seal 36 is engaged between the rear plate and the compressor casing and a second ring seal 38 is engaged between the rear plate and the central casing.
  • Bolts 40 and fixing washers 42 connect the turbine housing to the central housing.
  • Trunnion bearings 50 mounted in the shaft bore 52 of the central envelope support the rotating shaft.
  • a hose clamp 54 mounted on the shaft adjacent to the compressor wheel engages a forced thrust bearing 56 between the central casing and the rear plate in the illustrated embodiment.
  • a sleeve 58 is engaged between the clamp and the compressor wheel.
  • a rotary seal 60 such as a piston ring, provides a seal between the sleeve and the back plate.
  • a circlip 62 forces the journal bearing into the bore and a nut 64 forces the compressor wheel and bearing components on the shaft.
  • the variable geometry mechanism of the present invention includes a substantially cylindrical piston 70 entering the concentric turbine casing aligned with the rotary axis of the turbine.
  • the piston is longitudinally displaceable by a crosspiece 72, having three branches in the illustrated embodiment, attaching to the piston and attaching to an actuation shaft 74.
  • the actuation shaft enters a socket 76 extending to through the turbine housing and connects to an actuating device 77.
  • the actuating device is mounted on projections on the turbine housing using a support 78 and bolts 80.
  • the piston slides in the turbine housing by 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 illustrated in FIG. 1, substantially reducing the area of the intake nozzle towards the turbine from the volute 24. In the fully open position, a radial projection 86 on the piston between in a count 88 which limits the stroke of the piston.
  • the fins 90 of the nozzle extend from the radial projection on the piston. In the closed position of the piston, the fins are housed in a stripped portion of the molded part of the central envelope.
  • a heat shield 92 is engaged between the turbine casing and the central casing.
  • the screen is of a shape adapted to extend into the cavity of the turbine casing from the interface between the central casing and the turbine casing and provides an internal wall to the intake nozzle of the turbine.
  • FIG. 2 shows the heat shield incorporating closed slots 96 to receive the fins 90. As shown in FIGS. 3 and 4, the fins have a first part 98 which is received in the slots and a second part 100 in the form step which is longer in rope and depth -to exceed the size of the slot. As shown in FIG.
  • FIG. 6b shows an alternative embodiment of the step vane with the step chord, represented by the line 106, established at an angle with respect to the dawn chord, represented by the line 104. This arrangement provides a modified angle of attack on the blade relative to the air flow in the open and closed positions of the piston for enhanced aerodynamic control.
  • the piston actuation system in the embodiment illustrated in the drawings is a pneumatic actuator 77 having a housing bottom 102 fixed to a support 78 as it is. illustrated in FIG.l.

Abstract

The invention concerns a turbocharger with variable turbine intake nozzle comprising a mobile cylindrical piston to vary the area of the intake nozzle in the turbine. Vanes mounted on the piston to control the flow into the nozzle penetrate through a slotted heat baffle which supplies a smooth aerodynamic flow into the turbine vanes. The vanes further comprise a stepped portion having greater chord and depth which engage the surface of the heat baffle and hermetically close the slots with the piston in closed position. An axial actuating device is attached to operate the piston.

Description

TURBOCOMPRESSEUR A AILETTES COULISSANTES AVEC SLIDING VANE TURBOCHARGER
AILETTES GRADUEESGRADUATED FINS
ARRIERE-PLAN DE L'INVENTIONBACKGROUND OF THE INVENTION
Domaine de 1 ' invention :Field of the invention:
La présente invention se rapporte généralement à des turbocompresseurs à géométrie variable. Plus particulièrement, un turbocompresseur est fourni ayant une admission de turbine à tuyère variable à ailettes coulissantes, avec les ailettes entrant par un écran thermique en tôle à fentes suspendu dans l'enveloppe de la turbine et les ailettes ayant une forme en gradin pour assurer une fermeture hermétique contre la surface de l'écran thermique. Description de l'art apparenté :The present invention generally relates to turbochargers with variable geometry. More specifically, a turbocharger is provided having a variable nozzle turbine inlet with sliding fins, with the fins entering through a slotted sheet heat shield suspended in the turbine housing and the fins having a stepped shape to ensure hermetic closure against the surface of the heat shield. Description of related art:
Les turbocompresseurs à grand rendement utilisent des systèmes à géométrie variable pour les admissions de tuyère de turbine afin d'augmenter la performance et le rendement aérodynamique. Les systèmes à géométrie variable pour turbocompresseurs ont typiquement été de deux types : à ailettes rotatives et à piston. Le type à ailettes rotatives exemplifié dans le brevet américain numéro 5.947.681, intitulé PRESSURE BALANCED DUAL AXLE VARIABLE NOZZLE TURBOCHARGER fournit une pluralité d'ailettes individuelles placées dans la tuyère d'admission de la turbine qui peuvent tourner pour réduire ou augmenter l'aire de la tuyère et le volume d'écoulement. Le type à piston, qui est exemplifié dans les brevets américains numéros 5.214.920 et 5.231.831 intitulés tous les deux TURBOCHARGER APPARATUS, et le brevet américain numéro 5.441.383 intitulé VARIABLE EXHAUST DRIVEN TURBOCHARGERS, utilise un piston ou une paroi cylindrique qui est déplaçable de manière concentrique à l'axe de rotation de la turbine pour réduire l'aire de l'admission de la tuyère. Dans la plupart des cas, le turbocompresseur à géométrie variable du type à piston incorpore des ailettes ayant un angle d'attaque fixe par rapport à l'écoulement d'air, qui sont montées soit sur le piston, soit sur une paroi de tuyère fixe en face du piston et qui entrent dans des fentes dans la surface opposée durant le mouvement du piston.High efficiency turbochargers use variable geometry systems for turbine nozzle inlets to increase performance and efficiency aerodynamic. Variable geometry systems for turbochargers have typically been of two types: rotary vane and piston. The rotary vane type exemplified in US Patent Number 5,947,681, titled PRESSURE BALANCED DUAL AXLE VARIABLE NOZZLE TURBOCHARGER provides a plurality of individual vanes placed in the turbine inlet nozzle which can rotate to reduce or increase the area of the nozzle and the flow volume. The piston type, which is exemplified in US patents 5,214,920 and 5,231,831 both titled TURBOCHARGER APPARATUS, and U.S. patent number 5,441,383 titled VARIABLE EXHAUST DRIVEN TURBOCHARGERS, uses a cylindrical piston or wall which is displaceable concentrically with the axis of rotation of the turbine to reduce the area of the nozzle inlet. In most cases, the piston type variable geometry turbocharger incorporates fins having a fixed angle of attack with respect to the air flow, which are mounted either on the piston or on a fixed nozzle wall opposite the piston and which enter slots 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 défi a été de maximiser la performance aérodynamique équilibré par le tolérançage des surfaces de contact, surtout des ailettes et des fentes de réception qui sont soumises à une variation de température extrême et à une contrainte mécanique, ainsi que de fournir, un moyen pour actionner le piston selon une configuration pouvant être facilement fabriquée . RESUME DE L'INVENTIONIn the variable geometry turbochargers of. piston type of the prior art, the challenge has been to maximize the aerodynamic performance balanced by the tolerancing of the contact surfaces, especially the fins and receiving slots which are subjected to an extreme temperature variation and to mechanical stress, as well as providing, means for actuating the piston in a configuration which can be easily manufactured. SUMMARY OF THE INVENTION
Un turbocompresseur incorporant la présente invention a une carcasse ayant une enveloppe de turbine recevant un gaz d'échappement d'un collecteur d'échappement d'un moteur à combustion interne au niveau d'une admission et ayant une sortie d'échappement, une enveloppe de compresseur ayant une admission d'air et une première volute, et une enveloppe centrale à l'intermédiaire de l'enveloppe de turbine et de l'enveloppe de compresseur. Une roue de turbine est portée dans l'enveloppe de turbine pour extraire l'énergie du gaz d'échappement. La roue de turbine est connectée à un arbre qui s'étend de l'enveloppe de turbine à travers un alésage d'arbre dans l'enveloppe centrale et la roue de turbine a un disque arrière sensiblement complet et des aubes multiples. Un palier monté dans l'alésage d'arbre de l'enveloppe centrale soutient l'arbre pour le mouvement rotatif et une roue à aubes est connectée à l'arbre en face de la roue de turbine et enfermée dans l'enveloppe de compresseur. Un piston sensiblement cylindrique est concentrique à la roue de turbine et 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'une première extrémité du piston à proximité du disque arrière. Un écran thermique est engagé au niveau de sa circonférence externe entre l'enveloppe de turbine et l'enveloppe centrale et s'étend radialement vers l'intérieur vers l'axe de rotation. L'écran thermique a une pluralité de fentes recevant les ailettes. Un dispositif d'actionnement est fourni pour déplacer le piston d'une première position dans laquelle la première extrémité est à proximité de l'écran thermique vers une deuxième position dans laquelle la première extrémité est éloignée de l'écran thermique. Les ailettes ont une première partie dimensionnée pour être' reçue dans les fentes et une deuxième partie ou gradin, entre la première partie et le piston dimensionnée pour engager la surface de l'écran thermique et couvrir la fente avec le piston dans la première position.A turbocharger incorporating the present invention has a carcass having a turbine casing receiving exhaust gas from an exhaust manifold of an internal combustion engine at an intake and having an exhaust outlet, a casing compressor having an air intake and a first volute, and a central casing through the turbine casing and the compressor casing. A turbine wheel is carried in the turbine casing to extract energy from the exhaust gas. The turbine wheel is connected to a shaft which extends from the turbine housing through a shaft bore in the central housing and the turbine wheel has a substantially complete rear disc and multiple blades. A bearing mounted in the shaft bore of the central casing supports the shaft for the rotary movement and a paddle wheel is connected to the shaft opposite the turbine wheel and enclosed in the compressor casing. A substantially cylindrical piston is concentric with the turbine wheel and displaceable parallel to an axis of rotation of the turbine wheel. A plurality of fins extend substantially 'parallel to the axis of rotation from a first end of the piston close to the rear disc. A heat shield is engaged at its outer circumference between the turbine casing and the central casing and extends radially inward towards the axis of rotation. The heat shield has a plurality of slots receiving the fins. An actuator is provided to move the piston from a first position in which the first end is near the heat shield to a second position in which the first end is away from the screen thermal. The vanes have a first portion sized to be 'received in the slots and a second portion or step, between the first piston and dimensioned to engage the surface of the heat shield and cover the slot with the piston in the first position.
BREVE DESCRIPTION DES DESSINS Les détails et caractéristiques de la présente invention seront mieux compris en rapport avec la description détaillée et des dessins sur lesquels :BRIEF DESCRIPTION OF THE DRAWINGS The details and characteristics of the present invention will be better understood in relation to the detailed description and of the drawings in which:
La FIG.l est une vue en élévation en coupe transversale d'un turbocompresseur utilisant une réalisation de l'invention ; la FIG.2 est une vue de dessus de l'écran thermique ; la FIG.3 est une vue de dessous du piston avec les ailettes attachées ; la FIG.4 est une vue latérale d'une des ailettes ; la FIG.5a est une vue latérale partielle du turbocompresseur incorporant la présente invention montrant le détail de l'engagement à gradin des ailettes de l'écran thermique avec le piston dans la position fermée ; la FIG.5b est une vue latérale partielle du turbocompresseur incorporant la présente invention montrant le détail de l'engagement à gradin des ailettes de l'écran thermique avec le piston dans la position ouverte ; la FIG.βa est une vue de dessous de l'écran thermique montrant en lignes discontinues l'empreinte du gradin sur les ailettes qui ferme les fentes ; et la FIG.βb est une vue détaillée d'une variante de réalisation de l'empreinte d'aube., et .de gradin avec la ligne de corde de gradin à un certain angle par rapport à la ligne de corde d'aube. DESCRIPTION DETAILLEE DE L'INVENTIONFIG.l is an elevational view in cross section of a turbocharger using an embodiment of the invention; FIG.2 is a top view of the heat shield; FIG.3 is a bottom view of the piston with the fins attached; FIG.4 is a side view of one of the fins; FIG.5a is a partial side view of the turbocharger incorporating the present invention showing the detail of the step engagement of the fins of the heat shield with the piston in the closed position; FIG.5b is a partial side view of the turbocharger incorporating the present invention showing the detail of the step engagement of the fins of the heat shield with the piston in the open position; FIG.βa is a bottom view of the heat shield showing in broken lines the imprint of the step on the fins which closes the slots; and FIG.βb is a detailed view of an alternative embodiment of the blade imprint . , and. of a step with the line of the step cord at an angle with respect to the line of the blade of the blade. DETAILED DESCRIPTION OF THE INVENTION
En nous référant "aux dessins, la FIG.l montre une réalisation de l'invention pour un turbocompresseur 10 qui incorpore une enveloppe de turbine 12, une enveloppe centrale 14 et une enveloppe de compresseur 16. Une roue de turbine 18 est connectée par un arbre 20 à une roue de compresseur 22. La roue de turbine convertit l'énergie du gaz d'échappement d'un moteur à combustion interne fourni à partir d'un collecteur d'échappement (non illustré) à une volute 24 dans l'enveloppe de turbine. Le gaz d'échappement est expansé à travers la turbine et sort de l'enveloppe de turbine par une sortie 26.Referring " to the drawings, FIG. 1 shows an embodiment of the invention for a turbocharger 10 which incorporates a turbine casing 12, a central casing 14 and a compressor casing 16. A turbine wheel 18 is connected by a shaft 20 to a compressor wheel 22. The turbine wheel converts the energy of the exhaust gas from an internal combustion engine supplied from an exhaust manifold (not shown) to a volute 24 in the turbine casing The exhaust gas is expanded through the turbine and leaves the turbine casing via an outlet 26.
L'enveloppe de compresseur incorpore une admission 28 et une volute de sortie 30. Une plaque arrière 32 est connectée par des boulons 34 à l'enveloppe de compresseur. La plaque arrière est, à son tour, fixée à l'enveloppe centrale au moyen de boulons (non illustrés) . Un premier joint en anneau 36 est engagé entre la plaque arrière et l'enveloppe de compresseur et un deuxième joint en anneau 38 est engagé entre la plaque arrière et l'enveloppe centrale. Des boulons 40 et des rondelles de fixation 42 raccordent l'enveloppe de turbine à l'enveloppe centrale.The compressor casing incorporates an inlet 28 and an outlet volute 30. A rear plate 32 is connected by bolts 34 to the compressor casing. The backplate is, in turn, attached to the center shell with bolts (not shown). A first ring seal 36 is engaged between the rear plate and the compressor casing and a second ring seal 38 is engaged between the rear plate and the central casing. Bolts 40 and fixing washers 42 connect the turbine housing to the central housing.
Des paliers de tourillon 50 montés dans l'alésage d'arbre 52 de l'enveloppe centrale soutiennent l'arbre en rotation. Un. collier de serrage 54 monté sur l'arbre adjacent à la roue de compresseur engage un palier de butée 56 forcé entre l'enveloppe centrale et la plaque arrière dans la réalisation illustrée. Un manchon 58 est engagé entre le collier de serrage et la roue de compresseur. Un joint d'étanchéité rotatif 60, tel qu'un segment de piston, fournit un joint étanche entre le manchon et la plaque arrière. Un circlip 62 force le palier de tourillon dans l'alésage et un écrou 64 force la roue de compresseur et les composants de palier sur l'arbre.Trunnion bearings 50 mounted in the shaft bore 52 of the central envelope support the rotating shaft. A hose clamp 54 mounted on the shaft adjacent to the compressor wheel engages a forced thrust bearing 56 between the central casing and the rear plate in the illustrated embodiment. A sleeve 58 is engaged between the clamp and the compressor wheel. A rotary seal 60, such as a piston ring, provides a seal between the sleeve and the back plate. A circlip 62 forces the journal bearing into the bore and a nut 64 forces the compressor wheel and bearing components on the shaft.
Le mécanisme à géométrie variable de la présente invention inclut un piston sensiblement cylindrique 70 entrant dans l'enveloppe de turbine concentrique ent aligné sur l'axe rotatif de la turbine. Le piston est longitudinalement déplaçable par un croisillon 72, ayant trois branches dans la réalisation illustrée, s 'attachant au piston et s 'attachant à un arbre d'actionnement 74. L'arbre d'actionnement entre dans une douille 76 s 'étendant à travers l'enveloppe de turbine et se connecte à un dispositif d'actionnement 77. Sur la réalisation illustrée, le dispositif d'actionnement est monté sur des saillies sur l'enveloppe de turbine en utilisant un support 78 et des boulons 80. Le piston glisse dans l'enveloppe de turbine par une pièce rapportée à faible friction 82. Un joint d'étanchéité cylindrique 84 est inséré entre le piston et la pièce rapportée. Le piston est déplaçable à partir d'une position fermée illustrée à la FIG.l, réduisant sensiblement l'aire de la tuyère d'admission vers la turbine depuis la volute 24. En position complètement ouverte, une projection radiale 86 sur le piston entre dans un dépouillement 88 qui limite la course du piston.The variable geometry mechanism of the present invention includes a substantially cylindrical piston 70 entering the concentric turbine casing aligned with the rotary axis of the turbine. The piston is longitudinally displaceable by a crosspiece 72, having three branches in the illustrated embodiment, attaching to the piston and attaching to an actuation shaft 74. The actuation shaft enters a socket 76 extending to through the turbine housing and connects to an actuating device 77. In the illustrated embodiment, the actuating device is mounted on projections on the turbine housing using a support 78 and bolts 80. The piston slides in the turbine housing by 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 illustrated in FIG. 1, substantially reducing the area of the intake nozzle towards the turbine from the volute 24. In the fully open position, a radial projection 86 on the piston between in a count 88 which limits the stroke of the piston.
Les ailettes 90 de la tuyère s'étendent à partir de la projection radiale sur le piston. En position fermée du piston, les ailettes sont logées dans une portion dépouillée de la pièce moulée de l'enveloppe centrale. Un écran thermique 92 est engagé entre l'enveloppe de turbine et l'enveloppe centrale. L'écran est de forme adaptée pour s'étendre dans la cavité de 1 ' enveloppe .de turbine à partir de l'interface entre l'enveloppe centrale et l'enveloppe de turbine et fournit une paroi interne à la tuyère d'admission de la turbine. La FIG.2 montre l'écran thermique incorporant des fentes fermées- 96 pour recevoir les ailettes 90. Comme le montrent les figures 3 et 4, les ailettes ont une première partie 98 qui est reçue dans les fentes et une deuxième partie 100 en forme de gradin qui est plus longue en corde et profondeur -pour dépasser la taille de la fente. Comme le montre la FIG.5a, avec le piston dans la position ouverte, l'aire de tuyère de l'admission de turbine est dimensionnée pour un écoulement maximum dans la turbine. Avec le piston dans la position fermée, comme on le voit à la FIG.5b, la première partie des ailettes est reçue à l'intérieur des fentes et la deuxième partie ou gradin sur les ailettes engage la surface de l'écran thermique. Le gradin ferme hermétiquement la fente dans l'écran thermique pour éviter une perte excessive de l'écoulement d'admission de la turbine, comme on le voit mieux à la FIG.δa. La forme aérodynamique 'du gradin maintient un écoulement régulier du courant d'admission dans les deux positions fermée et ouverte du piston. La- FIG.6b démontre une variante de réalisation de l'aube à gradin avec la corde du gradin, représentée par la ligne 106, établie selon un angle par rapport à la corde de l'aube, représentée par la ligne 104. Cet agencement fournit un angle d'attaque modifié sur l'aube par rapport à l'écoulement d'air dans les positions ouverte et fermée du piston pour une commande aérodynamique rehaussée .The fins 90 of the nozzle extend from the radial projection on the piston. In the closed position of the piston, the fins are housed in a stripped portion of the molded part of the central envelope. A heat shield 92 is engaged between the turbine casing and the central casing. The screen is of a shape adapted to extend into the cavity of the turbine casing from the interface between the central casing and the turbine casing and provides an internal wall to the intake nozzle of the turbine. FIG. 2 shows the heat shield incorporating closed slots 96 to receive the fins 90. As shown in FIGS. 3 and 4, the fins have a first part 98 which is received in the slots and a second part 100 in the form step which is longer in rope and depth -to exceed the size of the slot. As shown in FIG. 5a, with the piston in the open position, the nozzle area of the turbine inlet is sized for maximum flow through the turbine. With the piston in the closed position, as seen in FIG.5b, the first part of the fins is received inside the slots and the second part or step on the fins engages the surface of the heat shield. The step hermetically closes the slot in the heat shield to avoid excessive loss of the turbine inlet flow, as best seen in FIG.δa. The aerodynamic shape 'of the step maintains a smooth flow of the inlet stream in both closed and open positions of the piston. FIG. 6b shows an alternative embodiment of the step vane with the step chord, represented by the line 106, established at an angle with respect to the dawn chord, represented by the line 104. This arrangement provides a modified angle of attack on the blade relative to the air flow in the open and closed positions of the piston for enhanced aerodynamic control.
Le système d'actionnement du piston dans la réalisation illustrée sur les dessins, est un dispositif d'actionnement pneumatique 77 ayant un fond de boîtier 102 fixé à un support 78 comme cela est. illustré sur la FIG.l. Ayant décrit l'invention en détail comme l'exige le droit en propriété industrielle, les hommes de l'art se rendront compte de modifications et de substitutions aux réalisations spécifiques divulguées aux présentes. De telles modifications et " substitutions sont dans la portée et dans l'intention de la présente invention telle que définie dans les revendications qui suivent. The piston actuation system in the embodiment illustrated in the drawings is a pneumatic actuator 77 having a housing bottom 102 fixed to a support 78 as it is. illustrated in FIG.l. Having described the invention in detail as required by industrial property law, those skilled in the art will be aware of modifications and substitutions to the specific achievements disclosed herein. Such modifications and " substitutions are within the scope and intent of the present invention as defined in the claims which follow.

Claims

REVENDICATIONS : CLAIMS:
1. Un turbocompresseur comprenant : une carcasse ayant une enveloppe de turbine recevant du gaz d'échappement d'un collecteur d'échappement d'un moteur à combustion interne au niveau d'une admission et ayant une sortie d'échappement, une enveloppe de compresseur ayant une 'admission d'air et une première volute, et une enveloppe centrale à l'intermédiaire de l'enveloppe de turbine et de l'enveloppe de compresseur ; une roue de turbine portée dans l'enveloppe de turbine et extrayant l'énergie du gaz d'échappement, ladite roue de turbine étant connectée à un arbre s ' étendant de l'enveloppe de turbine à travers un alésage d'arbre dans l'enveloppe centrale ; un palier porté dans l'alésage d'arbre de l'enveloppe centrale, ledit palier soutenant l'. arbre pour le mouvement rotatif ; une roue à aubes connectée audit arbre en face de la roue de turbine et enfermée dans l'enveloppe de compresseur; un piston sensiblement cylindrique, concentrique à la roue de turbine et déplaçable parallèlement à un axe de rotation de la roue de turbine ; une pluralité d'ailettes s ' étendant sensiblement parallèlement à l'axe de rotation à partir d'une première extrémité, du piston à proximité du disque arrière, chaque ailette ayant 'une première partie ayant des premières corde et profondeur et une deuxième partie entre la première partie et la première . extrémité du piston, la deuxième partie ayant des deuxièmes corde et profondeur supérieures aux premières corde et profondeur ; un écran thermique engagé au niveau de sa circonférence externe entre l'enveloppe de turbine et l'enveloppe centrale et s 'étendant radialement vers l'intérieur vers l'axe de rotation, ledit écran thermique ayant en outre une pluralité de fentes ayant une corde et une profondeur pour recevoir de manière proche la première partie des ailettes ; et des moyens pour déplacer le piston d'une première position dans laquelle la première extrémité est à proximité de l'écran thermique vers une deuxième position dans laquelle la première extrémité est éloignée de l'écran thermique, la deuxième partie des ailettes engageant l'écran thermique et fermant hermétiquement les fentes avec le piston dans la première position.1. A turbocharger comprising: a carcass having a turbine casing receiving exhaust gas from an exhaust manifold of an internal combustion engine at an intake and having an exhaust outlet, a casing compressor having an 'air inlet and a first volute, and a central casing via the casing of the turbine and compressor housing; a turbine wheel carried in the turbine casing and extracting energy from the exhaust gas, said turbine wheel being connected to a shaft extending from the turbine casing through a shaft bore in the central envelope; a bearing carried in the shaft bore of the central envelope, said bearing supporting the. shaft for rotary movement; a paddle wheel connected to said shaft opposite the turbine wheel and enclosed in the casing compressor; a substantially cylindrical piston, concentric with the turbine wheel and movable parallel to an axis of rotation of the turbine wheel; a plurality of fins extending substantially parallel to the axis of rotation from a first end of the piston near the back disc, each vane having a first portion having first cord and depth and a second portion between the first part and the first. end of the piston, the second part having second chords and depth greater than the first chords and depth; a heat shield engaged at its outer circumference between the turbine shell and the central shell and extending radially inward towards the axis of rotation, said heat shield further having a plurality of slots having a cord and a depth for closely receiving the first portion of the fins; and means for moving the piston from a first position in which the first end is close to the heat shield towards a second position in which the first end is distant from the heat shield, the second part of the fins engaging the heat shield and hermetically closing the slots with the piston in the first position.
2. Un turbocompresseur tel que défini dans la revendication 1, dans lequel la deuxième partie des ailettes incorpore une forme aérodynamique en vue d'encourager l'écoulement lisse .du gaz d'admission de turbine.2. A turbocharger as defined in claim 1, wherein the second part of the fins incorporates an aerodynamic shape in order to encourage the smooth flow of the turbine inlet gas.
3. Un turbocompresseur tel que défini dans la revendication 2, dans lequel la deuxième partie des ailettes est inclinée par rapport à la première partie en vue de fournir un angle 'd'attaque modifié pour l'écoulement d'air avec le piston dans la position fermée. 3. A turbocharger as defined in claim 2, wherein the second part of the fins are inclined relative to the first part in order to provide a modified angle of attack for the air flow with the piston in the closed position.
EP00954699A 2000-07-19 2000-07-19 Sliding vane turbocharger with graduated vanes Expired - Lifetime EP1301689B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/FR2000/002069 WO2002006636A1 (en) 2000-07-19 2000-07-19 Sliding vane turbocharger with graduated vanes

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EP1301689A1 true EP1301689A1 (en) 2003-04-16
EP1301689B1 EP1301689B1 (en) 2006-09-20

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EP (1) EP1301689B1 (en)
JP (1) JP2004504524A (en)
KR (1) KR100643093B1 (en)
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AU (1) AU2000267060A1 (en)
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DE60030894D1 (en) 2006-11-02
CN1454284A (en) 2003-11-05
KR100643093B1 (en) 2006-11-10
WO2002006636A1 (en) 2002-01-24
KR20030029785A (en) 2003-04-16
DE60030894T2 (en) 2007-09-06
JP2004504524A (en) 2004-02-12
CN1289791C (en) 2006-12-13
EP1301689B1 (en) 2006-09-20
US7097432B1 (en) 2006-08-29

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