EP0240381A1 - Controlling device for the supply of a radial turbine, and turbine provided with such a device - Google Patents

Controlling device for the supply of a radial turbine, and turbine provided with such a device Download PDF

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Publication number
EP0240381A1
EP0240381A1 EP87400395A EP87400395A EP0240381A1 EP 0240381 A1 EP0240381 A1 EP 0240381A1 EP 87400395 A EP87400395 A EP 87400395A EP 87400395 A EP87400395 A EP 87400395A EP 0240381 A1 EP0240381 A1 EP 0240381A1
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EP
European Patent Office
Prior art keywords
flaps
axis
turbine
fluid
flap
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
EP87400395A
Other languages
German (de)
French (fr)
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EP0240381B1 (en
Inventor
Marcel Sedille
Maurice Le Creurer
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.)
Automobiles Peugeot SA
Automobiles Citroen SA
Original Assignee
Automobiles Peugeot SA
Automobiles Citroen SA
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Publication date
Application filed by Automobiles Peugeot SA, Automobiles Citroen SA filed Critical Automobiles Peugeot SA
Priority to AT87400395T priority Critical patent/ATE43404T1/en
Publication of EP0240381A1 publication Critical patent/EP0240381A1/en
Application granted granted Critical
Publication of EP0240381B1 publication Critical patent/EP0240381B1/en
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D17/146—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by throttling the volute inlet of radial machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • the invention relates to turbochargers and, more particularly, those used to ensure the supercharging of motor vehicle engines.
  • turbochargers that is to say comprising an air compressor increasing its density, this compressor being driven by a turbine disposed on the exhaust gases .
  • variable opening turbine that is to say capable of using different gas flow rates under the same pressure.
  • the object of the present invention is to construct a centripetal or helico-centripetal turbine, in particular for a motor vehicle turbocharger, comprising a spiral-shaped casing comprising a part with variable geometry and a steerable guide vane.
  • the turbine in question is provided with means for adjusting the flow rate of the fluid passing through it and is characterized in that said means comprise a first blade adjustable in position mounted on an axis and constituting a first movable portion of a volute and a second blade adjustable in position mounted on an axis and constituting a steerable director which are both arranged so that the fluid which runs through the lower surface of one of these blades is never again in contact with the second, that one of the blades has an upper surface traversed by a flow of fluid which feeds the other blade and that the upper surface of the other blade is traversed by a flow of fluid coming directly from the inlet of the turbine only between its axis and its trailing edge, the part situated between its axis and its leading edge being in contact only with sta fluid inconvenient or practically such.
  • the turbine for a turbocharger comprises a body 1 consisting of an envelope 2 and a base 3 assembled to each other according to any suitable technique.
  • this body delimits a tube 4 which is extended by a volute 5 whose configuration in the shape of a spiral defines a channel 6.
  • the body also contains a turbine wheel 7.
  • This wheel carries the movable receiving vanes; it is classic which is why it will not be described more fully and is only shown schematically in the drawing.
  • the exhaust gases penetrate through the tubing, follow the spiral channel to go towards the center where they come into contact with the blades of the wheel 7 which they rotate.
  • this wheel drives a compressor, not shown, which is used to power the engine.
  • the turbine comprises two guide vanes or flaps 10 a and 10 b which are each articulated on an axis 11 a and 11 b respectively; these axes are oriented parallel to the axis of the wheel 7. These two flaps thus mounted movable are capable of tilting along these axes so as to move and change orientation.
  • Each of the flaps has a leading edge 12 a and 12 b , a trailing edge 13 a and 13 b , an upper surface 14 a and 14 b and a lower surface 15 a and 15 b respectively.
  • an axis 11a is in the manner of a pin which is integral or is subject to the flap in any suitable manner to be integral in rotation.
  • Levers 16 a , 16 b are fixed on the axes 11 a , 11 b respectively, as drawn, by pins, bolts, grooves, shanks, welds or the like. These levers are connected to a common rod 17 by suitable articulations not shown in detail. Any type of articulation, for example, by finger, by groove and stud can be suitable as soon as it defines an axis of rotation practically parallel to that of the flaps.
  • the flaps occupy positions which are symmetrical with respect to the axis of rotation of the wheel and the levers are situated on the same side with a diameter.
  • the wheelhouse that we designed, which includes the rod 17 and the two levers 16 a and 16 b , we see that when we act on the rod, to push or pull it, we tilt the two flaps so that their leading edge approaches or moves away from the axis of the wheel, as shown in solid line and in broken line respectively where the flaps are drawn in the extreme positions that they can take.
  • the flap 10 a constitutes a deformable portion of the volute 5 of the spiral envelope and that the other flap 10 b constitutes a blade steerable director.
  • first flap 10a is only in contact with the fluid current while the other flap 10b is immersed in the fluid and is in contact with it by its two faces, its upper surface 14 b and its lower surface 15 b .
  • each of the two flaps arranged symmetrically with respect to the axis of the turbine, feeds half of the circumference of the wheel so that the fluid current which follows the lower surface of the any of the flaps is no longer subsequently in contact with the other.
  • leading edges 12 a and 12 b are of rounded profile so that whatever the position occupied by the flaps, they can be bypassed without, however, there is separation of the fluid which flows in their vicinity.
  • the two blades or flaps 10 a and 10 b are housed in the envelope 2 which, in cooperation with the base 3, delimit the channel which bypasses the upper surface of the flap 10b so that at maximum opening, the speed of the fluid is low enough there so that friction is practically non-existent. It can also be seen that this envelope delimits the tube 4 through which the fluid penetrates; this tubing is connected to the envelope by a spout 18.
  • This spout is located directly above the hinge pin 11 a so that, at this point, the clearance between the flap and the spout is also as small as possible so that the current which would eventually follow the upper surface 14 a is small and so that the upper surface part of the trailing edge of this flap 10 a is supplied directly by the inlet pipe.
  • the part of the upper surface 14 a located between the leading edge 12 a and the spout 18 or the axis 11 a is in contact with quasi-stagnant fluid.
  • the width L of the flaps which is also the distance which separates the parts of parallel walls of the envelope and of the base between which they move, is significantly greater than the width l of the inlet of the wheel 7.
  • the hinge axis 11a and the axis of articulation 11 b are located at about the middle of the length of the blade or component which requires that this axis be very resistant, this therefore fixes the minimum thickness of the blade or flap.
  • each cam comprises a plate 21 which carries a crank pin 22 and is extended opposite by a tail 23.
  • Each crank pin 22 is engaged in a complementary groove 30 formed in the corresponding flap. The profile of the groove is chosen so that the tilting of the flap is gradual.
  • On the tail of each cam is wedged a lever connected by an articulation to a rod, as was indicated in connection with the first embodiment.
  • the single control rod is associated with a regulator which regulates its position and therefore the orientation of the flaps thus acting on the flow rate of the turbocharger.
  • FIGS. 3 and 4 The embodiment drawn in FIGS. 3 and 4 is somewhat more complex but it has the advantage that each flap is held in two "points" which makes them less sensitive to the vibratory pulses caused by the puffs of the cylinders during exhaust.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne les turbines de turbocompresseur. La turbine comprend des aubes ou volets (10b, 10a) orientables formant respectivement le distributeur et une partie mobile de la volute. Ces aubes sont disposées de manière que (a) l'intrados (15) de l'une d'elles dirige le fluide qui le parcourt sur une trajectoire qui n'est plus jamais en contact avec l'autre, que (b) l'extrados (14b) de l'une des aubes soit parcouru par un courant de fluide qui alimente l'autre aube et que (c) l'extrados (14a) de l'autre des aubes ne soit parcouru par un courant de fluide entrant directement dans la turbine qu'entre son axe (11a) et son bord de fuite (13a). Application à la suralimentation des moteurs des véhicules automobiles.The invention relates to turbocharger turbines. The turbine comprises adjustable vanes or flaps (10b, 10a) respectively forming the distributor and a movable part of the volute. These blades are arranged so that (a) the lower surface (15) of one of them directs the fluid which flows through it on a trajectory which is never again in contact with the other, than (b) l the upper surface (14b) of one of the blades is traversed by a current of fluid which feeds the other blade and that (c) the upper surface (14a) of the other of the blades is traversed by a stream of incoming fluid directly in the turbine only between its axis (11a) and its trailing edge (13a). Application to the supercharging of motor vehicle engines.

Description

L'invention concerne les turbocompresseurs et, plus particulièrement, ceux utilisés pour assurer la suralimentation des moteurs de véhicules automo­biles.The invention relates to turbochargers and, more particularly, those used to ensure the supercharging of motor vehicle engines.

Il est courant, sur les véhicules automo­biles, d'utiliser des moteurs suralimentés par des turbocompresseurs, c'est-à-dire comportant un com­presseur d'air accroissant sa densité, ce compresseur étant entraîné par une turbine disposée sur les gaz d'échappement.It is common, on motor vehicles, to use engines supercharged by turbochargers, that is to say comprising an air compressor increasing its density, this compressor being driven by a turbine disposed on the exhaust gases .

Comme les conditions d'utilisation des mo­teurs de véhicules sont très variables, il est néces­saire de prévoir un dispositif limitant la pression de l'aire, ce qui est généralement obtenu en adjoignant à la turbine une soupape de by-pass s'ouvrant dès que la pression de l'air dépasse une certaine valeur.As the conditions of use of vehicle engines are very variable, it is necessary to provide a device limiting the pressure of the area, which is generally obtained by adding to the turbine a bypass valve opening as soon as air pressure exceeds a certain value.

Toutefois, en raison de la perte d'énergie provoquée par la détente des gaz dans cette soupape de décharge, on a récemment proposé d'utiliser une tur­bine à ouverture variable, c'est-à-dire capable d'u­tiliser différents débits de gaz sous une même pres­sion.However, due to the energy loss caused by the expansion of the gases in this relief valve, it has recently been proposed to use a variable opening turbine, that is to say capable of using different gas flow rates under the same pressure.

En particulier, on a utilisé un dispositif inspiré de ce qui se fait sur les turbines hydrauli­ques et composé d'un certain nombre de distributeurs orientables disposés en couronne autour de la roue et alimentés d'une manière identique par une enveloppe qui présente le plus souvent une configuration en colimaçon.In particular, we used a device inspired by what is done on hydraulic turbines and composed of a number of orientable distributors arranged in a ring around the wheel and supplied in an identical manner by an envelope which most often has a spiral configuration.

Pour les moteurs de véhicules de tourisme cependant, ces distributeurs ont des dimensions rela­tivement très petites et sont fragiles car soumis aux bouffées des gaz d'échappement qui son éjectés des cylindres à une température élevée et qui sont rela­ tivement corrosifs. Le mécanisme de commande simul­tanée des aubes directrices de ces distributeurs est d'autre part complexe et le coût d'un tel équipement accroît d'une manière notable le prix d'un turbocom­presseur.For passenger car engines, however, these distributors have relatively very small dimensions and are fragile because they are subjected to puffs of exhaust gases which are ejected from the cylinders at a high temperature and which are rela highly corrosive. The mechanism for simultaneously controlling the guide vanes of these distributors is also complex and the cost of such equipment increases significantly the price of a turbocharger.

On a donc cherché à simplifier de tels dis­positifs et à les rendre plus robustes et moins chers. C'est ainsi que certains ne comportent qu'un ou deux volets mobiles qui sont des portions de volute, cel­le-ci étant en quelque sorte déformable dans une pro­portion plus ou moins étendue.We have therefore sought to simplify such devices and to make them more robust and less expensive. Thus, some only have one or two movable flaps which are portions of a scroll, the latter being in a way deformable in a more or less extensive proportion.

Le but de la présente invention est de cons­truire une turbine centripète ou hélico-centripète, notamment pour turbocompresseur de véhicule auto­mobile, comprenant une enveloppe en forme de colimaçon comportant une partie à géométrie variable et une aube directrice orientable.The object of the present invention is to construct a centripetal or helico-centripetal turbine, in particular for a motor vehicle turbocharger, comprising a spiral-shaped casing comprising a part with variable geometry and a steerable guide vane.

Pour ce faire la turbine en question est munie de moyens de réglage du débit du fluide la tra­versant et est caractérisée en ce que lesdits moyens comprennent une première aube réglable en position montée sur un axe et constituant une première portion mobile d'une volute et une seconde aube réglable en position montée sur un axe et constituant une di­rectrice orientable qui sont toutes deux agencées de manière que le fluide qui parcourt l'intrados de l'une de ces aubes ne soit plus jamais en contact avec la seconde, que l'une des aubes présente un extrados par­couru par un courant de fluide qui alimente l'autre aube et que l'extrados de l'autre aube ne soit par­couru par un courant de fluide en provenance directe de l'entrée de la turbine qu'entre son axe et son bord de fuite, la partie située entre son axe et son bord d'attaque n'étant en contact qu'avec du fluide sta­ gnant ou pratiquement tel.To do this, the turbine in question is provided with means for adjusting the flow rate of the fluid passing through it and is characterized in that said means comprise a first blade adjustable in position mounted on an axis and constituting a first movable portion of a volute and a second blade adjustable in position mounted on an axis and constituting a steerable director which are both arranged so that the fluid which runs through the lower surface of one of these blades is never again in contact with the second, that one of the blades has an upper surface traversed by a flow of fluid which feeds the other blade and that the upper surface of the other blade is traversed by a flow of fluid coming directly from the inlet of the turbine only between its axis and its trailing edge, the part situated between its axis and its leading edge being in contact only with sta fluid inconvenient or practically such.

D'autres caractéristiques de l'invention ressortiront de la lecture de la description qui suit et de l'examen du dessin où :

  • - la Fig.1 est une vue schématique de des­sus, partiellement en coupe, d'un mode de réalisation de l'invention ;
  • - la Fig.2 est une coupe suivant les plans X O Y de la Fig.1 ;
  • - la Fig.3 est une vue schématique de des­sus, partiellement en coupe, d'un autre mode de réa­lisation de l'invention ; et
  • - la Fig.4 est une coupe partielle de détail suivant l'axe OM de la Fig.3.
Other characteristics of the invention will emerge from reading the following description and examining the drawing where:
  • - Fig.1 is a schematic top view, partially in section, of an embodiment of the invention;
  • - Fig.2 is a section along the planes XOY of Fig.1;
  • - Fig.3 is a schematic top view, partially in section, of another embodiment of the invention; and
  • - Fig.4 is a partial sectional detail along the axis OM of Fig.3.

La turbine pour turbocompresseur suivant l'invention comprend un corps 1 constitué d'une en­veloppe 2 et d'une embase 3 assemblées l'une à l'autre suivant toute technique convenable. Comme on le voit, notamment sur la Fig.1, ce corps délimite une tubulure 4 qui se prolonge par une volute 5 dont la configu­ration en forme de colimaçon définit un canal 6. Le corps contient aussi une roue de turbine 7. Cette roue porte les aubes mobiles réceptrices ; elle est clas­sique c'est pourquoi elle ne sera pas plus amplement décrite et est seulement figurée schématiquement sur le dessin. Comme il est classique, les gaz d'échap­pement pénètrent par la tubulure, suivent le canal en colimaçon pour se diriger vers le centre où ils viennent au contact des aubes de la roue 7 qu'ils font tourner. Comme il est connu, cette roue entraîne un compresseur, non représenté, qui sert à l'alimentation du moteur. Ces éléments étant bien connus en technique automobile on ne s'y étendra pas plus longuement dans la description qui suit, description qui sera res­ treinte aux moyens qui font partie de l'invention et à ceux qui s'y rapportent directement ou indirectement.The turbine for a turbocharger according to the invention comprises a body 1 consisting of an envelope 2 and a base 3 assembled to each other according to any suitable technique. As can be seen, in particular in FIG. 1, this body delimits a tube 4 which is extended by a volute 5 whose configuration in the shape of a spiral defines a channel 6. The body also contains a turbine wheel 7. This wheel carries the movable receiving vanes; it is classic which is why it will not be described more fully and is only shown schematically in the drawing. As is conventional, the exhaust gases penetrate through the tubing, follow the spiral channel to go towards the center where they come into contact with the blades of the wheel 7 which they rotate. As is known, this wheel drives a compressor, not shown, which is used to power the engine. These elements being well known in automotive technology, we will not extend them further in the description which follows, which description will be res to the means which form part of the invention and to those which relate to it directly or indirectly.

En examinant la Fig. 1, on voit que la tur­bine comprend deux aubes directrices ou volets 10a et 10b qui sont chacun articulés sur un axe 11a et 11b respectivement ; ces axes sont orientés parallèlement à l'axe de la roue 7. Ces deux volets ainsi montés mobiles sont susceptibles de basculer suivant ces axes de manière à se déplacer et à changer d'orientation. Chacun des volets présente un bord d'attaque 12a et 12b, un bord de fuite 13a et 13b, un extrados 14a et 14b et un intrados 15a et 15b respectivement.By examining Fig. 1, it can be seen that the turbine comprises two guide vanes or flaps 10 a and 10 b which are each articulated on an axis 11 a and 11 b respectively; these axes are oriented parallel to the axis of the wheel 7. These two flaps thus mounted movable are capable of tilting along these axes so as to move and change orientation. Each of the flaps has a leading edge 12 a and 12 b , a trailing edge 13 a and 13 b , an upper surface 14 a and 14 b and a lower surface 15 a and 15 b respectively.

Comme on le voit plus particulièrement sur la Fig.2, un axe 11a se présente à la manière d'une cheville qui fait corps ou est assujettie au volet de toute manière appropriée pour en être solidaire en rotation. Des leviers 16a, 16b sont calés sur les axes 11a, 11b respectivement, comme dessiné, par des gou­pilles, boulons, cannelures, emmanchements, soudures ou autre. Ces leviers sont reliés à une tige commune 17 par des articulations appropriées non dessinées dans le détail. Tout type d'articulation par exemple, par doigt, par rainure et téton peut convenir dès lors qu'elle définit un axe de rotation pratiquement paral­lèle à celui des volets.As seen more particularly in Fig.2, an axis 11a is in the manner of a pin which is integral or is subject to the flap in any suitable manner to be integral in rotation. Levers 16 a , 16 b are fixed on the axes 11 a , 11 b respectively, as drawn, by pins, bolts, grooves, shanks, welds or the like. These levers are connected to a common rod 17 by suitable articulations not shown in detail. Any type of articulation, for example, by finger, by groove and stud can be suitable as soon as it defines an axis of rotation practically parallel to that of the flaps.

Comme on le voit, notamment sur la Fig.1, les volets occupent des positions qui sont symétriques par rapport à l'axe de rotation de la roue et les le­viers sont situés d'un même côté d'un diamètre. Grâce à la timonerie que l'on a dessinée, qui comprend la tige 17 et les deux leviers 16a et 16b, on voit que lorsqu'on agit sur la tige, pour la pousser ou la tirer, on fait basculer les deux volets de manière que leur bord d'attaque s'approche ou s'éloigne de l'axe de la roue, comme cela est représenté en trait plein et en trait discontinu respectivement où les volets sont dessinés dans les positions extrêmes qu'ils peuvent prendre.As can be seen, in particular in FIG. 1, the flaps occupy positions which are symmetrical with respect to the axis of rotation of the wheel and the levers are situated on the same side with a diameter. Thanks to the wheelhouse that we designed, which includes the rod 17 and the two levers 16 a and 16 b , we see that when we act on the rod, to push or pull it, we tilt the two flaps so that their leading edge approaches or moves away from the axis of the wheel, as shown in solid line and in broken line respectively where the flaps are drawn in the extreme positions that they can take.

En examinant la Fig.1, on voit que, selon l'invention l'un des volets, le volet 10a constitue une portion déformable de la volute 5 de l'enveloppe en colimaçon et que l'autre volet 10b constitue une aube directrice orientable.By examining FIG. 1, it can be seen that, according to the invention, one of the flaps, the flap 10 a constitutes a deformable portion of the volute 5 of the spiral envelope and that the other flap 10 b constitutes a blade steerable director.

En examinant toujours la Fig.1, on remarque que le premier volet 10a n'est en contact avec le courant fluide que partiellement tandis que l'autre volet 10b baigne dans le fluide et est à son contact par ses deux faces, son extrados 14b et son intrados 15b.Still examining Fig. 1, we note that the first flap 10a is only in contact with the fluid current while the other flap 10b is immersed in the fluid and is in contact with it by its two faces, its upper surface 14 b and its lower surface 15 b .

La réalisation des deux volets est telle que leurs bords de fuite 13a et 13b sont d'épaisseur mini­male.The realization of the two components is such that their trailing edges 13 and 13b are of minimal thickness.

Comme on le voit en examinant la Fig.1, cha­cun des deux volets, disposés symétriquement par rap­port à l'axe de la turbine, alimente une moitié de la circonférence de la roue de sorte que le courant flui­de qui suit l'intrados de l'un quelconque des volets n'est plus ultérieurement en contact avec l'autre.As can be seen by examining Fig. 1, each of the two flaps, arranged symmetrically with respect to the axis of the turbine, feeds half of the circumference of the wheel so that the fluid current which follows the lower surface of the any of the flaps is no longer subsequently in contact with the other.

Dans ce mode de réalisation dessiné schéma­tiquement, on a supposé que les deux volets étaient identiques bien que cela ne soit pas indispensable. Toutefois, on observera que pour éviter des dissymé­tries d'écoulement sur la roue on utilise des volets dont les profils de l'intrados sont identiques.In this schematically drawn embodiment, it has been assumed that the two components are identical although this is not essential. However, it will be observed that to avoid asymmetries of flow on the wheel, flaps are used, the profiles of the lower surface are identical.

En outre, on observera que les bords d'at­taque 12a et 12b sont de profil arrondi pour que quelle que soit la position qu'occupent les volets, ils puissent être contournés sans que, pour autant, il y ait décollement du fluide qui s'écoule à leur proxi­mité.In addition, it will be observed that the leading edges 12 a and 12 b are of rounded profile so that whatever the position occupied by the flaps, they can be bypassed without, however, there is separation of the fluid which flows in their vicinity.

Comme on le voit en observant les Fig.1 et 2, les deux aubes ou volets 10a et 10b sont logés dans l'enveloppe 2 qui, en coopération avec l'embase 3, délimitent le canal qui contourne l'extrados du volet 10b de manière à ce qu'à l'ouverture maximale, la vitesse du fluide y soit suffisamment faible pour que les frottements soient pratiquement inexistants. On y constate aussi que cette enveloppe délimite la tubu­lure 4 par laquelle pénètre le fluide ; cette tubulure est raccordée à l'enveloppe par un bec 18. Ce bec est situé à l'aplomb de l'axe d'articulation 11a de telle sorte, qu'à cet endroit, le jeu entre le volet et le bec soit aussi petit que possible pour que le courant qui suivrait éventuellement l'extrados 14a soit peu important et pour que la partie extrados du bord de fuite de ce volet 10a soit alimentée directement par la tubulure d'entrée. La partie de l'extrados 14a située entre le bord d'attaque 12a et le bec 18 ou l'axe 11a est au contact de fluide quasi-stagnant.As can be seen by observing Fig. 1 and 2, the two blades or flaps 10 a and 10 b are housed in the envelope 2 which, in cooperation with the base 3, delimit the channel which bypasses the upper surface of the flap 10b so that at maximum opening, the speed of the fluid is low enough there so that friction is practically non-existent. It can also be seen that this envelope delimits the tube 4 through which the fluid penetrates; this tubing is connected to the envelope by a spout 18. This spout is located directly above the hinge pin 11 a so that, at this point, the clearance between the flap and the spout is also as small as possible so that the current which would eventually follow the upper surface 14 a is small and so that the upper surface part of the trailing edge of this flap 10 a is supplied directly by the inlet pipe. The part of the upper surface 14 a located between the leading edge 12 a and the spout 18 or the axis 11 a is in contact with quasi-stagnant fluid.

Suivant une autre particularité importante de l'invention, la largeur L des volets qui est aussi la distance qui sépare les parties de parois pa­rallèles de l'enveloppe et de l'embase entre lesquel­les ils se meuvent, est supérieure d'une manière notable à la largeur l d'entrée de la roue 7.According to another important feature of the invention, the width L of the flaps which is also the distance which separates the parts of parallel walls of the envelope and of the base between which they move, is significantly greater than the width l of the inlet of the wheel 7.

Grâce à cette disposition, on obtient une convergence importante à l'entrée de la roue, ce qui a pour résultat de minimiser l'effet de sillages des deux volets et, de la sorte, de procurer une augmen­tation du rendement et une réduction des impulsions périodiques mécaniques sur l'aubage de la roue. On obtient de la sorte aussi que le débattement angulaire maximal entre les positions extrêmes des deux volets soit réduit, ce qui permet d'éviter à la position de plus grande ouverture que leurs bords de fuite se rapprochent trop de la roue et aussi que leurs bords d'attaque soient trop éloignés du centre ce qui permet de réduire l'importance de l'enveloppe.Thanks to this arrangement, a significant convergence is obtained at the inlet of the wheel, which has the result of minimizing the wake effect of the two flaps and, in this way, of providing an increase in efficiency and a reduction in pulses. mechanical periodicals on the impeller of the wheel. In this way we also obtain that the angular displacement maximum between the extreme positions of the two flaps is reduced, which makes it possible, in the position of largest opening, to avoid that their trailing edges approach too close to the wheel and also that their leading edges are too far from the center which reduces the size of the envelope.

Il est clair qu'on peut choisir judicieuse­ment la place des axes d'articulation des volets et la manière dont s'effectue leur commande.It is clear that one can choose judiciously the place of the axes of articulation of the shutters and the manner in which their control is carried out.

Comme on le voit sur le mode de réalisation de la Fig.1, l'axe d'articulation 11a et l'axe d'ar­ticulation 11b sont situés à peu près au milieu de la longueur de l'aube ou volet ce qui nécessite que cet axe soit très résistant, ceci fixe donc l'épaisseur minimale de l'aube ou volet.As seen in the embodiment of Fig.1, the hinge axis 11a and the axis of articulation 11 b are located at about the middle of the length of the blade or component which requires that this axis be very resistant, this therefore fixes the minimum thickness of the blade or flap.

On se reportera maintenant à la Fig.3 et à la Fig.4 où est dessiné un autre mode de réalisation.We will now refer to Fig.3 and Fig.4 where another embodiment is drawn.

Les éléments, lorsqu'ils sont repérés par les mêmes numéros de référence sont similaires et assurent les mêmes fonctions ; on ne s'attardera donc pas davantage sur leur description.The elements, when identified by the same reference numbers are similar and perform the same functions; we will therefore not dwell on their description any further.

Comme on le voit ici les axes 11a et 11b sont placées aussi près que possible des bords de fuite 13a et 13b des volets 10a et 10b, respectivement, mais cette fois ils ne servent pas à la commande de leur orientation. L'orientation des volets est, ici, com­mandée par des cames 20a et 20b. Comme on le voit notamment sur la Fig.4, chaque came comprend un plateau 21 qui porte un maneton 22 et se prolonge à l'opposé par une queue 23. Chaque maneton 22 est engagé dans une rainure complémentaire 30 ménagée dans le volet correspondant. Le profil de la rainure est choisi de manière à ce que le basculement du volet soit progressif. Sur la queue de chaque came est calé un levier relié par une articulation à une tige, comme il a été indiqué à propos du premier mode de réali­sation.As seen here the axes 11 a and 11 b are placed as close as possible to the trailing edges 13 a and 13 b of the flaps 10 a and 10 b , respectively, but this time they are not used to control their orientation . The orientation of the flaps is, here, controlled by cams 20 a and 20 b . As seen in particular in Fig.4, each cam comprises a plate 21 which carries a crank pin 22 and is extended opposite by a tail 23. Each crank pin 22 is engaged in a complementary groove 30 formed in the corresponding flap. The profile of the groove is chosen so that the tilting of the flap is gradual. On the tail of each cam is wedged a lever connected by an articulation to a rod, as was indicated in connection with the first embodiment.

Dans ce mode de réalisation comme dans le mode de réalisation décrit à propos des Fig.1 et 2, la tige unique de commande est associée à un régulateur qui règle sa position et donc l'orientation des volets agissant ainsi sur le débit du turbocompresseur.In this embodiment as in the embodiment described in connection with Fig.1 and 2, the single control rod is associated with a regulator which regulates its position and therefore the orientation of the flaps thus acting on the flow rate of the turbocharger.

Le mode de réalisation dessiné sur les Fig. 3 et 4 est quelque peu plus complexe mais il présente l'avantage que chaque volet est maintenu en deux "points" ce qui les rend moins sensibles aux impul­sions vibratoires provoquées par les bouffées des cylindres en cours d'échappement.The embodiment drawn in FIGS. 3 and 4 is somewhat more complex but it has the advantage that each flap is held in two "points" which makes them less sensitive to the vibratory pulses caused by the puffs of the cylinders during exhaust.

Claims (5)

1. Turbine centripète ou hélico-centripète comprenant des moyens de réglage du débit du fluide la traversant, caractérisée en ce que lesdits moyens comprennent un premier volet orientable (10a) monté sur un axe (11a) et constituant une partie mobile d'une volute (5) et un second volet orientable (10b) monté sur un axe (11b) et constituant une directrice orientable et en ce que ces volets sont disposés de manière que (a) l'intrados (15) de l'un des volets dirige le courant de fluide qui le parcourt sur une trajectoire qui n'est plus jamais au contact du second volet, que (b) l'extrados (14b) de l'un des volets soit parcouru par un courant de fluide qui alimente l'autre volet et que (c) l'extrados (14a) de l'autre des volets ne soit parcouru par un courant de fluide entrant directement dans la turbine qu'entre son axe (11a) et son bord de fuite (13a) afin qu'il ne soit en contact qu'avec du fluide stagnant ou pratiquement tel entre son axe (11a) et son bord d'attaque (12a).1. Centripetal or helico-centripetal turbine comprising means for adjusting the flow rate of the fluid passing through it, characterized in that said means comprise a first orientable flap (10 a ) mounted on an axis (11 a ) and constituting a movable part of a scroll (5) and a second orientable flap (10 b ) mounted on an axis (11 b ) and constituting an orientable director and in that these flaps are arranged so that (a) the lower surface (15) of the one of the flaps directs the flow of fluid which traverses it on a trajectory which is never again in contact with the second flap, that (b) the upper surface (14b) of one of the flaps is traversed by a flow of fluid which feeds the other flap and that (c) the upper surface (14a) of the other flap is traversed by a stream of fluid entering the turbine directly only between its axis (11a) and its trailing edge (13a ) so that it is in contact only with stagnant fluid or practically such between its axis (11a) and its leading edge (12a). 2. Turbine conforme à la revendication 1, caractérisée en ce que les volets sont disposés dans une partie du corps (1) de la turbine qui comprend deux plans perpendiculaires à l'axe de sa roue (7) et dont la distance est supérieure à la largeur de cette dernière à son entrée.2. Turbine according to claim 1, characterized in that the flaps are arranged in a part of the body (1) of the turbine which comprises two planes perpendicular to the axis of its wheel (7) and the distance of which is greater than the width of the latter at its entrance. 3. Turbine conforme à la revendication 1 ou 2, caractérisée en ce que l'axe (11) des volets (10) est situé à peu près au milieu de leur longueur et en ce que ces volets (10) sont orientés simultanément par une tringlerie qui comprend deux leviers (16) agissant sur leurs axes (11) respectifs et une tige de commande (17) unique associée à ces leviers (16) et placée sous la dépendance d'un régulateur approprié.3. Turbine according to claim 1 or 2, characterized in that the axis (11) of the flaps (10) is located approximately in the middle of their length and in that these flaps (10) are oriented simultaneously by a linkage which comprises two levers (16) acting on their respective axes (11) and a single control rod (17) associated with these levers (16) and placed under the dependence of an appropriate regulator. 4. Turbine conforme à l'une quelconque des revendications 1 et 2, caractérisée en ce que l'axe (11) des volets (10) est situé près de leur bord de fuite (13), en ce que ces volets (10) sont orientés simultanément par des cames (20) placées vers le bord d'attaque (12) des volets (10) de manière que ceux-ci soient supportés en deux points distincts et éloignés et en ce que chaque came (20) est commandée par un levier (16), ces leviers étant associés à une tige de commande (17) unique placée sous la dépendance d'un régulateur approprié.4. Turbine according to any one of claims 1 and 2, characterized in that the axis (11) of the flaps (10) is located near their trailing edge (13), in that these flaps (10) are simultaneously oriented by cams (20) placed towards the leading edge (12) of the flaps (10) so that these are supported at two separate and distant points and in that each cam (20) is controlled by a lever (16), these levers being associated with a single control rod (17) placed under the dependence of an appropriate regulator. 5. Application de la turbine conforme à l'une quelconque des revendications 1 à 4, à la construction d'un turbocompresseur destiné à assurer l'alimentation d'un moteur automobile.5. Application of the turbine according to any one of claims 1 to 4, to the construction of a turbocharger intended to supply power to an automobile engine.
EP87400395A 1986-02-28 1987-02-23 Controlling device for the supply of a radial turbine, and turbine provided with such a device Expired EP0240381B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT87400395T ATE43404T1 (en) 1986-02-28 1987-02-23 CONTROL DEVICE FOR THE FEED OF A RADIAL TURBINE AND TURBINE WITH SUCH DEVICE.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8602814A FR2595118B1 (en) 1986-02-28 1986-02-28 CENTRIPETE OR HELICO-CENTRIPETE TURBINE COMPRISING A VOLUME WITH VARIABLE GEOMETRY AND AN ADJUSTABLE VANE, IN PARTICULAR FOR A TURBOCHARGER OF AUTOMOBILES
FR8602814 1986-02-28

Publications (2)

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EP0240381A1 true EP0240381A1 (en) 1987-10-07
EP0240381B1 EP0240381B1 (en) 1989-05-24

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EP87400395A Expired EP0240381B1 (en) 1986-02-28 1987-02-23 Controlling device for the supply of a radial turbine, and turbine provided with such a device

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US (1) US4776757A (en)
EP (1) EP0240381B1 (en)
JP (1) JPS62206232A (en)
AT (1) ATE43404T1 (en)
DE (1) DE3760183D1 (en)
FR (1) FR2595118B1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH01227823A (en) * 1988-03-08 1989-09-12 Honda Motor Co Ltd Variable nozzle structure of turbine
JPH02107735U (en) * 1989-02-16 1990-08-28
DE19819699B4 (en) * 1998-05-02 2005-05-19 Daimlerchrysler Ag turbocharger
US6272859B1 (en) 1998-10-02 2001-08-14 Caterpillar Inc. Device for controlling a variable geometry turbocharger

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR766760A (en) * 1933-01-13 1934-07-04 Adjustment device for reaction turbines
FR1512184A (en) * 1966-02-25 1968-02-02 Garrett Corp Control device for regulating the flow of a fluid through a turbomachine
GB1379075A (en) * 1973-01-16 1975-01-02 Lanyon T B Radial flow turbo-machines
EP0043305A1 (en) * 1980-06-27 1982-01-06 Regie Nationale Des Usines Renault Turbine with adjustable spiral casing for the admission of the gas
EP0096624A1 (en) * 1982-06-03 1983-12-21 Automobiles Peugeot Turbo charger for an internal-combustion engine
EP0212834A2 (en) * 1985-07-17 1987-03-04 Geoffrey Light Wilde Variable inlet for a radial turbine

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2648195A (en) * 1945-12-28 1953-08-11 Rolls Royce Centrifugal compressor for supercharging internal-combustion engines
US2858666A (en) * 1954-01-25 1958-11-04 Cooper Bessemer Corp Turbocharging of two-cycle engines
GB780621A (en) * 1954-05-15 1957-08-07 Stork Koninklijke Maschf Internal combustion engines with exhaust-gas-actuated compressors supplying scavenging and supercharging air
FR1272830A (en) * 1960-11-04 1961-09-29 Eberspaecher J Safety device for exhaust gas turbochargers
US3232043A (en) * 1964-01-13 1966-02-01 Birmann Rudolph Turbocompressor system
DE2060271A1 (en) * 1970-12-08 1972-06-29 Kuehnle Kopp Kausch Ag Procedure for the automatic adjustment of the inlet swirl when compressing the exhaust gas turbocharger and diffuser
DE2558878C2 (en) * 1975-12-27 1983-12-01 Daimler-Benz Ag, 7000 Stuttgart Piston internal combustion engine with exhaust gas turbocharger
US4403913A (en) * 1981-11-03 1983-09-13 Helsingoer Vaerft A/S Guide blade arrangement for adjustable guide blades
JPS5879622A (en) * 1981-11-04 1983-05-13 Nissan Motor Co Ltd Engine with turbocharger
FR2524071B1 (en) * 1982-03-29 1986-05-23 Renault Sport DEVICE FOR CONTROLLING THE SUPPLY OF AN INTERNAL COMBUSTION ENGINE
JPS58167825A (en) * 1982-03-29 1983-10-04 Hino Motors Ltd Turbosupercharger device of vehicle engine
US4678397A (en) * 1983-06-15 1987-07-07 Nissan Motor Co., Ltd. Variable-capacitance radial turbine having swingable tongue member
JPS6155316A (en) * 1984-08-28 1986-03-19 Nissan Motor Co Ltd Supercharging pressure controller

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR766760A (en) * 1933-01-13 1934-07-04 Adjustment device for reaction turbines
FR1512184A (en) * 1966-02-25 1968-02-02 Garrett Corp Control device for regulating the flow of a fluid through a turbomachine
GB1379075A (en) * 1973-01-16 1975-01-02 Lanyon T B Radial flow turbo-machines
EP0043305A1 (en) * 1980-06-27 1982-01-06 Regie Nationale Des Usines Renault Turbine with adjustable spiral casing for the admission of the gas
EP0096624A1 (en) * 1982-06-03 1983-12-21 Automobiles Peugeot Turbo charger for an internal-combustion engine
EP0212834A2 (en) * 1985-07-17 1987-03-04 Geoffrey Light Wilde Variable inlet for a radial turbine

Also Published As

Publication number Publication date
JPS62206232A (en) 1987-09-10
FR2595118A1 (en) 1987-09-04
DE3760183D1 (en) 1989-06-29
ATE43404T1 (en) 1989-06-15
US4776757A (en) 1988-10-11
EP0240381B1 (en) 1989-05-24
FR2595118B1 (en) 1988-06-24

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