EP1301689B1 - Sliding vane turbocharger with graduated vanes - Google Patents
Sliding vane turbocharger with graduated vanes Download PDFInfo
- Publication number
- EP1301689B1 EP1301689B1 EP00954699A EP00954699A EP1301689B1 EP 1301689 B1 EP1301689 B1 EP 1301689B1 EP 00954699 A EP00954699 A EP 00954699A EP 00954699 A EP00954699 A EP 00954699A EP 1301689 B1 EP1301689 B1 EP 1301689B1
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- EP
- European Patent Office
- Prior art keywords
- piston
- turbine
- vanes
- housing
- 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.)
- Expired - Lifetime
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Classifications
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- 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
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- 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
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- 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
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- 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 particularly, a turbocharger is provided having a sliding finned nozzle turbine inlet, with the fins entering through a slotted sheet heat shield suspended in the turbine casing and the fins having a stepped shape to provide a hermetic closure against the surface of the heat shield.
- Variable geometry systems for turbochargers have typically been of two types: rotary vane and piston.
- the rotary fin type exemplified in US Patent No. 5,947,681, entitled PRESSURE BALANCED DUAL VARIABLE AXLE NOZZLE TURBOCHARGER provides a plurality of individual vanes disposed 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 Nos. 5,214,920 and 5,231,831 both entitled TURBOCHARGER APPARATUS, and US Patent No.
- Patent EP 0.571.205 entitled VARIABLE EXHAUST DRIVEN TURBOCHARGERS provides an annular nozzle formed between a heat shield provided with slots for receiving the fins carried by a sleeve axially displaceable in the exhaust duct.
- the piston-type variable geometry turbocharger incorporates vanes having a fixed angle of attack relative to the airflow, which are mounted either on the piston or on a fixed nozzle wall.
- WO 01/53679 entitled TURBOCHARGER WITH SLIDING BLADES HAVING COMBINED DYNAMIC SURFACES AND HEAT SCREEN AND UNCOUPLED AXIAL ACTUATING DEVICE employs a screen to prevent gas from the back disc cavity from recirculating into the cavity housing the blades, increasing aerodynamic flow.
- a turbocharger incorporating the present invention has a casing having a turbine casing receiving an exhaust gas from an exhaust manifold of an internal combustion engine at an intake and having an exhaust outlet, an enclosure compressor having an air intake and a first volute, and a central envelope 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 that extends from the turbine casing through a shaft bore into the central casing and the turbine wheel has a substantially complete rear disc and multiple vanes.
- a bearing mounted in the shaft bore of the central casing supports the shaft for rotary motion and a bladed wheel is connected to the shaft in front of 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 near the rear disc.
- a heat shield is engaged at its outer circumference between the turbine shell and the central shell and extends radially inwardly 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 remote from the screen thermal.
- the fins have a first portion sized to be received in the slots and a second portion or step between the first portion and the sized piston to engage the surface of the heat shield and cover the slot with the piston in the first position.
- 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 The turbine wheel converts the exhaust gas energy of an internal combustion engine provided from an exhaust manifold (not shown) to a volute 24 in the casing. of turbine. The exhaust gas is expanded through the turbine and exits the turbine casing through an outlet 26.
- the compressor casing incorporates an inlet 28 and an outlet volute 30.
- a back plate 32 is connected by bolts 34 to the compressor casing.
- the backplate is, in turn, secured to the central envelope by means of bolts (not shown).
- a first ring seal 36 is engaged between the back plate and the compressor casing and a second ring seal 38 is engaged between the back plate and the central casing.
- Bolts 40 and securing washers 42 connect the turbine casing to the central casing.
- Trunnion bearings 50 mounted in the shaft bore 52 of the center shell support the rotating shaft.
- a clamp 54 mounted on the shaft adjacent the compressor wheel engages a thrust bearing 56 forced between the center shell and the backplate 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 the bearing components on the shaft.
- the variable geometry mechanism of the present invention includes a substantially cylindrical piston 70 entering the turbine casing concentrically aligned with the rotating axis of the turbine.
- the piston is longitudinally displaceable by a spider 72, having three branches in the illustrated embodiment, attaching to the piston and attaching to an actuating shaft 74.
- the actuating shaft enters a sleeve 76 extending to through the turbine casing and connects to an actuator 77.
- the actuator is mounted on projections on the turbine casing using a support 78 and bolts 80.
- the piston slides into the turbine casing via 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 to the turbine from the volute 24. In the fully open position, a radial projection 86 on the piston between in a stripping 88 which limits the stroke of the piston.
- the vanes 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 shaped to extend into the cavity of the turbine casing from the interface between the central casing and the turbine casing and provides a wall inside the inlet nozzle of the casing. turbine.
- FIG. 2 shows the heat shield incorporating closed slots 96 to receive the fins 90.
- the fins have a first portion 98 which is received in the slots and a second step portion 100 which is longer rope and depth to exceed the size of the slot.
- FIG. 5b with the piston in the open position, the nozzle area of the turbine inlet is sized for maximum flow in the turbine.
- the piston in the closed position as seen in FIG. 5a, 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 seals the slot in the heat shield to prevent excessive loss of turbine inlet flow, as best seen in FIG. 6a.
- FIG. 6b shows an alternative embodiment of the stepped blade with the step rope, represented by the line 106, set at an angle to the rope of the blade, represented by the line 104. This arrangement provides an angle of modified attack on the blade with respect to the air flow in the open and closed positions of the piston for enhanced aerodynamic control.
- the piston operating system in the embodiment illustrated in the drawings is a pneumatic actuator 77 having a housing bottom 102 attached to a carrier 78 as illustrated in FIG. 1.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
- Control Of Turbines (AREA)
Description
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.The present invention generally relates to turbochargers with variable geometry. More particularly, a turbocharger is provided having a sliding finned nozzle turbine inlet, with the fins entering through a slotted sheet heat shield suspended in the turbine casing and the fins having a stepped shape to provide a hermetic closure against the surface of the heat shield.
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. Le brevet EP 0.571.205 intitulé VARIABLE EXHAUST DRIVEN TURBOCHARGERS prévoit une tuyère annulaire formée entre un bouclier thermique muni de fentes pour recevoir les ailettes portées par un manchon déplaçable axialement dans la gaine d'échappement. 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. Le WO 01/53679 intitulé TURBOCHARGER WITH SLIDING BLADES HAVING COMBINED DYNAMIC SURFACES AND HEAT SCREEN AND UNCOUPLED AXIAL ACTUATING DEVICE emploie un écran pour empêcher le gaz venant de la cavité du disque arrière de se remettre en circulation dans la cavité logeant les lames, accroîssant l'écoulement aérodynamique.High Efficiency Turbochargers Use Variable Geometry Systems for Turbine Nozzle Intakes to Increase Performance and Efficiency aerodynamic. Variable geometry systems for turbochargers have typically been of two types: rotary vane and piston. The rotary fin type exemplified in US Patent No. 5,947,681, entitled PRESSURE BALANCED DUAL VARIABLE AXLE NOZZLE TURBOCHARGER provides a plurality of individual vanes disposed 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 Nos. 5,214,920 and 5,231,831 both entitled TURBOCHARGER APPARATUS, and US Patent No. 5,441,383 entitled VARIABLE EXHAUST DRIVEN TURBOCHARGERS, utilizes a piston or cylindrical wall which is concentrically displaceable to the axis of rotation of the turbine to reduce the area of the inlet of the nozzle. Patent EP 0.571.205 entitled VARIABLE EXHAUST DRIVEN TURBOCHARGERS provides an annular nozzle formed between a heat shield provided with slots for receiving the fins carried by a sleeve axially displaceable in the exhaust duct. In most cases, the piston-type variable geometry turbocharger incorporates vanes having a fixed angle of attack relative to the airflow, which are mounted either on the piston or on a fixed nozzle wall. in front of the piston and which enter slots in the opposite surface during the movement of the piston. WO 01/53679, entitled TURBOCHARGER WITH SLIDING BLADES HAVING COMBINED DYNAMIC SURFACES AND HEAT SCREEN AND UNCOUPLED AXIAL ACTUATING DEVICE employs a screen to prevent gas from the back disc cavity from recirculating into the cavity housing the blades, increasing aerodynamic flow.
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.In piston-type variable geometry turbochargers of the prior art, the challenge has been to maximize balanced aerodynamic performance by tolerating contact surfaces, especially fins and receiving slots that are subject to temperature variation. extreme and mechanical stress, as well as providing a means for actuating the piston in a configuration that can be easily manufactured.
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.A turbocharger incorporating the present invention has a casing having a turbine casing receiving an exhaust gas from an exhaust manifold of an internal combustion engine at an intake and having an exhaust outlet, an enclosure compressor having an air intake and a first volute, and a central envelope 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 that extends from the turbine casing through a shaft bore into the central casing and the turbine wheel has a substantially complete rear disc and multiple vanes. A bearing mounted in the shaft bore of the central casing supports the shaft for rotary motion and a bladed wheel is connected to the shaft in front of the turbine wheel and enclosed in the compressor casing.
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 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 near the rear disc. A heat shield is engaged at its outer circumference between the turbine shell and the central shell and extends radially inwardly 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 remote from the screen thermal. The fins have a first portion sized to be received in the slots and a second portion or step between the first portion and the sized piston to engage the surface of the heat shield and cover the slot with the piston in the first position.
Les détails et caractéristiques de la présente invention seront mieux compris en rapport avec la description détaillée et des dessins sur lesquels :
- La FIG.1 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.6a 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.6b 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.
- FIG. 1 is a cross-sectional elevational view of a turbocharger using one 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 embodying the present invention showing the detail of 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 turbocompressor embodying the present invention showing the detail of step engagement of the fins of the heat shield with the piston in the open position;
- 6a is a bottom view of the heat shield showing in broken lines the footprint of the step on the fins which closes the slots; and
- FIG. 6b is a detailed view of an alternative embodiment of the blade and step imprint with the step cord line at an angle to the blade rope line.
En nous référant aux dessins, la FIG.1 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
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
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.
Le mécanisme à géométrie variable de la présente invention inclut un piston sensiblement cylindrique 70 entrant dans l'enveloppe de turbine concentriquement 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.The variable geometry mechanism of the present invention includes a substantially
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.1, 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 piston slides into the turbine casing via a low-
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 l'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.The
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. 5b, 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. 5a, 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. 6a. 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.FIG. 2 shows the heat shield incorporating
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. 1.The piston operating system in the embodiment illustrated in the drawings is a pneumatic actuator 77 having a
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.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 specific achievements disclosed herein. Such modifications and substitutions are within the scope and intent of the present invention as defined in the following claims.
Claims (3)
- A turbocharger (10) comprising:a case having a turbine housing (12) receiving exhaust gas from an exhaust manifold of an internal combustion engine at an inlet and having an exhaust outlet, a compressor housing (16) having an air inlet and a first volute (24), and a center housing (14) intermediate the turbine housing (12) and compressor housing (16);a turbine wheel (18) carried within the turbine housing (12) and extracting energy from the exhaust gas, said turbine wheel (18) connected to a shaft (20) extending from the turbine housing (12) through a shaft bore (52) in the center housing (14);a bearing (50) carried in the shaft bore (52) of the center housing (14), said bearing supporting the shaft for rotational motion;a compressor impeller connected to the shaft opposite the turbine wheel (18) and enclosed within the compressor housing (16);a substantially cylindrical piston (70), concentric to the turbine wheel (18) and movable parallel to an axis of rotation of the turbine wheel (18);a plurality of vanes (90) extending substantially parallel to the axis of rotation from a first end of the piston proximate the back disc, each vane (90) having a first portion (98) with a first cord and depth and a second portion (100) intermediate the first portion (98) and the first end of the piston (70), the second portion (100) having a second cord and depth,a heat shield (92) engaged at its outer circumferences between the turbine housing (12) and center housing (14) and extending radially inward toward the axis of rotation, said heat shield (92) further having a plurality of slots (96) having cord and depth to closely receive the first portion (98) of the vanes (90); andmeans for moving the piston (70) from a first position wherein the first end is proximate the heat shield (92) to a second position wherein the first end is distal the heat shield (92), the second portion of the vanes (90) engaging the heat shield (92) and sealing the slots (96) with the piston (70) in the first position;characterised in that the second portion (100) of the vanes (90) have a second cord and depth larger than the first cord and depth so as to provide a step around the first portion (98).
- A turbocharger (10) as defined an claim 1 wherein the second portion (100) of the vanes (90) incorporates an aerodynamic shape to promote smooth flow of the turbine inlet gas.
- A turbocharger (10) as defined in claim 2 wherein the second portion (100) of the vanes (90) is angled in relationship to the first portion (98) to provide a modified angle of attack for the airflow with the piston in the closed position.
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 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1301689A1 EP1301689A1 (en) | 2003-04-16 |
EP1301689B1 true EP1301689B1 (en) | 2006-09-20 |
Family
ID=8847165
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00954699A Expired - Lifetime EP1301689B1 (en) | 2000-07-19 | 2000-07-19 | Sliding vane turbocharger with graduated vanes |
Country Status (8)
Country | Link |
---|---|
US (1) | US7097432B1 (en) |
EP (1) | EP1301689B1 (en) |
JP (1) | JP2004504524A (en) |
KR (1) | KR100643093B1 (en) |
CN (1) | CN1289791C (en) |
AU (1) | AU2000267060A1 (en) |
DE (1) | DE60030894T2 (en) |
WO (1) | WO2002006636A1 (en) |
Cited By (3)
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DE102011109643A1 (en) | 2011-08-05 | 2013-02-07 | Daimler Ag | Turbine for exhaust gas turbocharger of internal combustion engine, is provided with receiving space for region-wise retaining of turbine wheel, where guide element is provided |
WO2013083212A1 (en) | 2011-12-08 | 2013-06-13 | Daimler Ag | Turbine for an exhaust-gas turbocharger |
DE102011120555A1 (en) | 2011-12-08 | 2013-06-13 | Daimler Ag | Guide baffle for turbine of supercharger for internal combustion engine of motor vehicle, has guiding elements variably formed in longitudinal regions with respect to aerodynamic properties of guiding elements |
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US6652224B2 (en) * | 2002-04-08 | 2003-11-25 | Holset Engineering Company Ltd. | Variable geometry turbine |
GB0213910D0 (en) | 2002-06-17 | 2002-07-31 | Holset Engineering Co | Turbine |
AU2002348917A1 (en) * | 2002-11-15 | 2004-06-15 | Honeywell International Inc. | Variable nozzle for turbocharger |
WO2004074643A1 (en) * | 2003-02-19 | 2004-09-02 | Honeywell International Inc. | Nozzle device for a turbocharger and associated control method |
AU2003206002A1 (en) * | 2003-02-19 | 2004-09-09 | Honeywell International Inc. | Turbine having variable throat |
DE602004016780D1 (en) | 2004-05-03 | 2008-11-06 | Honeywell Int Inc | TURBINE OF A TURBOLADER |
US8250760B2 (en) | 2004-05-03 | 2012-08-28 | Honeywell International Inc. | Center housing of a turbine for a turbocharger and method of manufacturing the same |
US8047772B2 (en) * | 2005-03-30 | 2011-11-01 | Honeywell International Inc. | Variable geometry turbine for a turbocharger and method of controlling the turbine |
JP4468286B2 (en) * | 2005-10-21 | 2010-05-26 | 三菱重工業株式会社 | Exhaust turbocharger |
US8197195B2 (en) | 2005-11-16 | 2012-06-12 | Honeywell International Inc. | Turbocharger with stepped two-stage vane nozzle |
US7338254B2 (en) * | 2005-11-29 | 2008-03-04 | Honeywell International, Inc. | Turbocharger with sliding piston assembly |
EP1816317B1 (en) * | 2006-02-02 | 2013-06-12 | IHI Corporation | Turbocharger with variable nozzle |
WO2007148390A1 (en) * | 2006-06-21 | 2007-12-27 | Ihi Corporation | Bearing structure for rotating machine, rotating machine, method of producing bearing structure, and method of producing rotating machine |
EP2094957B1 (en) * | 2006-11-01 | 2016-06-29 | BorgWarner, Inc. | Turbine heat shield assembly |
US7980816B2 (en) * | 2007-08-27 | 2011-07-19 | Honeywell International Inc. | Retainer for a turbocharger |
GB0805519D0 (en) * | 2008-03-27 | 2008-04-30 | Cummins Turbo Tech Ltd | Variable geometry turbine |
DE102008023552B4 (en) * | 2008-05-14 | 2018-12-20 | BMTS Technology GmbH & Co. KG | Exhaust gas turbocharger for a motor vehicle |
GB2461720B (en) * | 2008-07-10 | 2012-09-05 | Cummins Turbo Tech Ltd | A variable geometry turbine |
GB2462115A (en) * | 2008-07-25 | 2010-01-27 | Cummins Turbo Tech Ltd | Variable geometry turbine |
KR101012085B1 (en) * | 2009-03-05 | 2011-02-07 | 방규열 | Floating type waterpower generator |
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JP5473762B2 (en) * | 2010-04-30 | 2014-04-16 | 三菱重工業株式会社 | Variable capacity turbine and variable capacity turbocharger having the same |
RU2013158217A (en) * | 2011-06-10 | 2015-07-20 | Боргварнер Инк. | TWO-FLOW TURBINE HOUSING TURBOCHARGER |
JP5409741B2 (en) * | 2011-09-28 | 2014-02-05 | 三菱重工業株式会社 | Opening restriction structure of variable nozzle mechanism and variable capacity turbocharger |
US9950382B2 (en) * | 2012-03-23 | 2018-04-24 | Pratt & Whitney Canada Corp. | Method for a fabricated heat shield with rails and studs mounted on the cold side of a combustor heat shield |
KR20150117690A (en) * | 2013-02-19 | 2015-10-20 | 보르그워너 인코퍼레이티드 | A turbocharger internal turbine heat shield having axial flow turning vanes |
GB2555872A (en) | 2016-11-15 | 2018-05-16 | Cummins Ltd | Vane arrangement for a turbo-machine |
GB2574195B (en) * | 2018-05-15 | 2022-06-08 | Cummins Ltd | Vane and shroud arrangements for a turbo-machine |
CN110496556A (en) * | 2019-09-16 | 2019-11-26 | 中煤科工清洁能源股份有限公司 | A kind of feeding system |
US11686210B2 (en) * | 2021-03-24 | 2023-06-27 | General Electric Company | Component assembly for variable airfoil systems |
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2000
- 2000-07-19 AU AU2000267060A patent/AU2000267060A1/en not_active Abandoned
- 2000-07-19 CN CNB008197547A patent/CN1289791C/en not_active Expired - Fee Related
- 2000-07-19 WO PCT/FR2000/002069 patent/WO2002006636A1/en active IP Right Grant
- 2000-07-19 DE DE60030894T patent/DE60030894T2/en not_active Expired - Lifetime
- 2000-07-19 EP EP00954699A patent/EP1301689B1/en not_active Expired - Lifetime
- 2000-07-19 US US10/333,405 patent/US7097432B1/en not_active Expired - Fee Related
- 2000-07-19 KR KR1020037000693A patent/KR100643093B1/en not_active IP Right Cessation
- 2000-07-19 JP JP2002512513A patent/JP2004504524A/en active Pending
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102011109643A1 (en) | 2011-08-05 | 2013-02-07 | Daimler Ag | Turbine for exhaust gas turbocharger of internal combustion engine, is provided with receiving space for region-wise retaining of turbine wheel, where guide element is provided |
WO2013083212A1 (en) | 2011-12-08 | 2013-06-13 | Daimler Ag | Turbine for an exhaust-gas turbocharger |
DE102011120555A1 (en) | 2011-12-08 | 2013-06-13 | Daimler Ag | Guide baffle for turbine of supercharger for internal combustion engine of motor vehicle, has guiding elements variably formed in longitudinal regions with respect to aerodynamic properties of guiding elements |
DE102011120553A1 (en) | 2011-12-08 | 2013-06-13 | Daimler Ag | Turbine for an exhaust gas turbocharger |
Also Published As
Publication number | Publication date |
---|---|
KR20030029785A (en) | 2003-04-16 |
KR100643093B1 (en) | 2006-11-10 |
AU2000267060A1 (en) | 2002-01-30 |
EP1301689A1 (en) | 2003-04-16 |
WO2002006636A1 (en) | 2002-01-24 |
JP2004504524A (en) | 2004-02-12 |
CN1289791C (en) | 2006-12-13 |
CN1454284A (en) | 2003-11-05 |
DE60030894D1 (en) | 2006-11-02 |
DE60030894T2 (en) | 2007-09-06 |
US7097432B1 (en) | 2006-08-29 |
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