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EP1728987B1 - Cooling device for a vehicle and the associated vehicle - Google Patents

Cooling device for a vehicle and the associated vehicle Download PDF

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Publication number
EP1728987B1
EP1728987B1 EP20060300540 EP06300540A EP1728987B1 EP 1728987 B1 EP1728987 B1 EP 1728987B1 EP 20060300540 EP20060300540 EP 20060300540 EP 06300540 A EP06300540 A EP 06300540A EP 1728987 B1 EP1728987 B1 EP 1728987B1
Authority
EP
European Patent Office
Prior art keywords
propeller
air
peripheral region
passage
blade
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.)
Not-in-force
Application number
EP20060300540
Other languages
German (de)
French (fr)
Other versions
EP1728987A1 (en
Inventor
David Menard
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.)
PSA Automobiles SA
Original Assignee
Peugeot Citroen Automobiles 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 Peugeot Citroen Automobiles SA filed Critical Peugeot Citroen Automobiles SA
Publication of EP1728987A1 publication Critical patent/EP1728987A1/en
Application granted granted Critical
Publication of EP1728987B1 publication Critical patent/EP1728987B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
    • F01P11/00—Component parts, details, or accessories not provided for in, or of interest apart from, groups F01P1/00 - F01P9/00
    • F01P11/10—Guiding or ducting cooling-air, to, or from, liquid-to-air heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
    • F01P1/00—Air cooling
    • F01P1/06—Arrangements for cooling other engine or machine parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
    • F01P5/00—Pumping cooling-air or liquid coolants
    • F01P5/02—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers
    • F01P5/06—Guiding or ducting air to, or from, ducted fans
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/326—Rotors specially for elastic fluids for axial flow pumps for axial flow fans comprising a rotating shroud
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Definitions

  • the present invention relates to a cooling device for a motor vehicle, of the type comprising a heat exchanger, and a motor-fan unit comprising a motorized propeller, arranged to rotate about an axis, facing the exchanger, and intended for aspirate, during operation of the propeller, air through the heat exchanger.
  • the heat exchanger is for example a radiator of a cooling circuit of a thermal engine of the motor vehicle, an air conditioning circuit of the passenger compartment of the motor vehicle, or an air cooling circuit of supercharging of the engine of the motor vehicle (see for example the document FR 2 269 636 A ).
  • motor vehicles comprise elements which it is desirable to cool to improve their operation.
  • These elements are, for example, an electronic box housed inside the engine compartment, or the brakes of the motor vehicle.
  • the air drawn by the propeller is warmed as it passes through the heat exchanger. Therefore, this hot air can not be used to satisfactorily cool such elements.
  • An object of the invention is to provide a cooling device for effectively cooling remote elements of the heat exchanger.
  • the present invention proposes a cooling device of the aforementioned type, characterized in that the helix comprises a peripheral region protruding, in at least one angular sector, from the periphery of the exchanger for capturing air in outside the exchanger, the motor-fan unit comprising elements for channeling the air captured by the peripheral region, the peripheral region being profiled so as to form a flow of air flowing mainly parallel to the axis of rotation of the helix the ducting elements delimit a main passage for the air sucked through the heat exchanger, and an auxiliary passage for the air captured by the peripheral region, the ducting elements comprising a separation wall of the main and auxiliary passages; the pipe elements comprise a fixed wall substantially perpendicular to the axis of rotation of the helix, the wall delimiting the auxiliary passage, and being contiguous to the peripheral region, downstream in the direction of flow of the formed air flow by the peripheral region of the propeller.
  • the invention also relates to a motor vehicle comprising a cooling device as defined above.
  • the cooling device 2 comprises a heat exchanger 4 (represented only by its outline in phantom on the figure 1 ) and a motor-fan unit 5, comprising an air duct nozzle 6, an air activation propeller 8, a propeller drive motor 9 and a frame 10 for supporting the motorcycle unit -ventilator 5.
  • a heat exchanger 4 represented only by its outline in phantom on the figure 1
  • a motor-fan unit 5 comprising an air duct nozzle 6, an air activation propeller 8, a propeller drive motor 9 and a frame 10 for supporting the motorcycle unit -ventilator 5.
  • orientations used are the usual orientations of motor vehicles.
  • front extend with respect to the direction and direction of travel of the motor vehicle, shown schematically by an arrow S on the figure 2 .
  • the exchanger 4 has a substantially rectangular contour ( figure 1 ), and is intended to be traversed by a fluid to be cooled and by air, in order to cool the fluid and to heat the air.
  • the nozzle 6 comprises a rectangular front opening 12, of contour substantially identical to the contour of the exchanger 4, and a circular rear opening 14, the openings 12, 14 extending in planes substantially parallel to each other.
  • the opening 12 is larger than the opening 14. More specifically, the diameter of the opening 14 is substantially equal to the height h of the opening 14, and less than the width l of the opening 14.
  • the nozzle 6 comprises internal walls 16 converging from the opening 12 to the opening 14.
  • the nozzle 6 comprises a central support plate 18 extending substantially in the plane of the opening 12, and fixed to the walls 16 by means of radial spacers 20 extending between the plate 18 and the walls 16.
  • platinum 18 and the spacers 20 form a perforated structure allowing the passage of air through the opening 12.
  • the propeller 8 has an axis of rotation R, and comprises a central hub 22, air activation blades 24, for example five in number and angularly regularly spaced, extending radially outwardly from the hub 22, and a ring 26 connecting the outer radial ends of the blades 24.
  • the vanes 24 constitute a main central air activation region, and are twisted to force a circulation of a main air flow axially along the R axis.
  • the propeller 8 comprises air activation fins 28 extending radially outwardly from the ring 26.
  • the fins 28 are for example ten in number, and angularly evenly distributed around the circumference of the crown. 26.
  • the fins 28 constitute an auxiliary peripheral region of air activation, and are profiled so as to cause the circulation of a flow of auxiliary air flowing along the axis R, and in the same direction as the flow of air. main air.
  • each fin 28 is inclined relative to the axis R so as to print in air a movement along the axis R.
  • each fin 28 extends between a leading edge of attack 28 a and a rear trailing edge 28 b, so that the tangent to each blade 28 in a plane perpendicular to a radial direction of the propeller 8 and passing through the fin 28, is substantially at any point of the fin 28 a non-zero angle with the axis R.
  • the propeller 8 is advantageously made in one piece, for example by plastic injection molding.
  • each fin 28 has, between its edges 28 a and 28 b of substantially constant thickness, and is curved, with a curvature oriented axially towards the rear, to improve the flow of air.
  • the angle of the tangent to each blade 28 with respect to the axis R, as defined above, is variable and decreases from edge 28 a to the edge 28 b, for example, an angle ⁇ 1 substantially 60 ° at an angle ⁇ 2 of substantially 30 °.
  • the propeller 8 has its hub 22 rotatably mounted on the engine 9, itself fixed on a rear face of the plate 18.
  • the propeller 8 is located behind the nozzle 6, across the opening 14.
  • the ring 26 has a diameter substantially equal to that of the opening 14, so that the blades 24 of the propeller 8 are located facing the opening 14, and that the fins 28 are located radially out of the opening 14.
  • the nozzle 6 and the propeller 8 are mounted on the frame 10, facing a circular opening 32 thereof, of the same diameter as the opening 12 and the ring 26.
  • the frame 10 comprises a cylindrical hole 34 coaxial with the opening 32 and having a cylindrical peripheral wall 36, and an annular partition 38 extending radially inwardly from the wall 36, a free inner edge 40 of the partition 38 defining the opening 32.
  • the peripheral wall 36 has a diameter substantially equal to the outer diameter of the fins 28, while being slightly greater.
  • Clearances 42 ( figure 1 ) are formed in a front face 44 of the frame 10 at the periphery of the hole 34.
  • the clearances 42 delimit a rectangular contour substantially of the same dimension as the opening 14.
  • the nozzle and the propeller 8 are arranged in the hole 34, facing the opening 32.
  • the propeller 8 is received in the hole 34, the ring 26 being aligned with the edge 40, so that the blades 14 are located opposite the opening 32, and the fins 28 are located opposite the partition 38.
  • the nozzle 6 is partially received in the hole 34, in front of the propeller 8, and partly in the recesses 42.
  • the nozzle 6 is fixed to the frame 10, for example by means of fasteners (not shown ) passing through orifices 45 ( figure 1 ) of the nozzle 6, and screwed into the frame 10.
  • the exchanger 4 is fixed in front of the nozzle 6, facing the opening 12.
  • the nozzle 6 and the exchanger 4 mask the hole 34 and the fins 28, except in an upper sector A, and a lower sector B, in which the fins 28 and the hole 34 protrude from the periphery of the nozzle 6 and of the exchanger 4, because of the outer diameter of fins 28 greater than the height h of the nozzle 6 and the exchanger 4.
  • the fins 28 overflow on two opposite sides of the nozzle 6.
  • the fins 28 project on only one side, or on more than two sides of the nozzle 6.
  • the hole 34 opens on the face 44, at the periphery of the nozzle 6 and the exchanger 4, by respective air inlets 46, 48 delimited between the outer surface of the nozzle 6 and the wall 36.
  • the sector A of the hole 34 is a sector of diameter greater than that of the remainder of the hole 34, so that the inlet 46 has an area greater than that of the inlet 48.
  • the device 2 comprises a conduit 50 having an inlet 52 opening into the hole 34, in the sector A and near the partition 38, and one or more outputs (not shown) opening remotely.
  • the outlets open into a space to cool, for example in an electronic box or in the brakes of the motor vehicle.
  • the propeller 8 is driven by the motor 9 in rotation about its axis R.
  • the blades 14 suck a main air flow through the exchanger 4, as illustrated by the arrows F1.
  • This main air flow passes through the exchanger 4 while heating, and is channeled downstream of the exchanger 4 in a main air passage P1 delimited by the inner surface of the nozzle 6 and the inner surface of the crown 28.
  • the main airflow is discharged to the rear of propeller 8.
  • An auxiliary air passage P2 is delimited between the outer surface of the nozzle 6, the outer surface of the ring 28, the wall 36, and the partition 38.
  • the passage P2 is separated from the passage P1, in particular by the nozzle 6 and the ring 28.
  • hot air circulating in the passage P1 does not flow in the passage P2, so as not to disturb the cooling of the space to be cooled.
  • the passage P2 comprises an annular portion 56 and two axial portions 58 extending between the annular portion 56 and the inlet 46, 48, above and below the nozzle 6.
  • the fins 28 extend in the annular portion 56.
  • the fins 28 force a flow of auxiliary air flowing axially rearwardly. In doing so, the fins 28 capture a flow of air through the inlets 46 and 48 and the axial portions 58, as illustrated by the arrows F2.
  • the air captured by the fins 28 is pressed by them against the partition 38 which is contiguous to the fins 28. This results in an increase in the pressure of the air against the partition 38 and in the annular portion 56.
  • the pressurized air circulates in the annular portion 58 and is evacuated through the pipe 50, opening into the annular portion 58, to the space to be cooled.
  • the fins 28 configured to force an axial air flow can improve the air flow in the passage P2, which increases the cooling of the space to be cooled.
  • these fins are made of a relatively flexible material, such as rubber to minimize play and consequently reduce leakage.
  • the partition 38 integral with the fixed frame 10, cooperates with the ring 26 to define the passage P2 sufficiently tight.
  • additional air exchangers are disposed downstream of the propeller, in the main air flow, so as to use the main air flow as a cold source in these additional exchangers.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Motor Or Generator Cooling System (AREA)
  • Power Steering Mechanism (AREA)
  • Steering Control In Accordance With Driving Conditions (AREA)

Abstract

The device has an electric fan unit (5) comprising a motorized propeller (8) rotatably disposed around a rotation axis (R) opposite to a radiator (4). The propeller aspirates an air across the radiator and has blades (28) overhanging from the periphery of the radiator to capture the air outside the radiator. The unit (5) has channeling units comprising an air pipe nozzle (6), a support frame (10) for the unit (5), a crown (26), a fixed wall (38), and a duct, for the air captured by the blades. The blades are configured to form an air flow (F2) flowing parallel to the axis (R). An independent claim is also included for a motor vehicle comprising a cooling device.

Description

La présente invention concerne un dispositif de refroidissement pour véhicule automobile, du type comprenant un échangeur de chaleur, et un groupe moto-ventilateur comprenant une hélice motorisée, disposée à rotation autour d'un axe, en regard de l'échangeur, et destinée à aspirer, lors du fonctionnement de l'hélice, de l'air à travers l'échangeur de chaleur.The present invention relates to a cooling device for a motor vehicle, of the type comprising a heat exchanger, and a motor-fan unit comprising a motorized propeller, arranged to rotate about an axis, facing the exchanger, and intended for aspirate, during operation of the propeller, air through the heat exchanger.

L'échangeur de chaleur est par exemple un radiateur d'un circuit de refroidissement d'un moteur thermique du véhicule automobile, d'un circuit de climatisation de l'habitacle du véhicule automobile, ou d'un circuit de refroidissement d'air de suralimentation du moteur thermique du véhicule automobile (voir par exemple le document FR 2 269 636 A ).The heat exchanger is for example a radiator of a cooling circuit of a thermal engine of the motor vehicle, an air conditioning circuit of the passenger compartment of the motor vehicle, or an air cooling circuit of supercharging of the engine of the motor vehicle (see for example the document FR 2 269 636 A ).

Par ailleurs, les véhicules automobiles comprennent des éléments qu'il est souhaitable de refroidir pour améliorer leur fonctionnement. Ces éléments sont, par exemple, un boîtier électronique logés à l'intérieur du compartiment moteur, ou les freins du véhicule automobile.On the other hand, motor vehicles comprise elements which it is desirable to cool to improve their operation. These elements are, for example, an electronic box housed inside the engine compartment, or the brakes of the motor vehicle.

L'air aspiré par l'hélice est réchauffé lors de son passage à travers l'échangeur de chaleur. Par conséquent, cet air chaud ne peut être utilisé pour refroidir de façon satisfaisante de tels éléments.The air drawn by the propeller is warmed as it passes through the heat exchanger. Therefore, this hot air can not be used to satisfactorily cool such elements.

Un but de l'invention est de proposer un dispositif de refroidissement permettant de refroidir efficacement des éléments distants de l'échangeur de chaleur.An object of the invention is to provide a cooling device for effectively cooling remote elements of the heat exchanger.

A cet effet, la présente invention propose un dispositif de refroidissement du type précité, caractérisé en ce que l'hélice comprend une région périphérique débordant, dans au moins un secteur angulaire, de la périphérie de l'échangeur pour capter de l'air en dehors de l'échangeur, le groupe moto-ventilateur comprenant des éléments de canalisation de l'air capté par la région périphérique, la région périphérique étant profilée de façon à former un flux d'air s'écoulant principalement parallèlement à l'axe de rotation de l'hélice les éléments de canalisation délimitent un passage principal pour l'air aspiré à travers l'échangeur de chaleur, et un passage auxiliaire pour l'air capté par la région périphérique, les éléments de canalisation comprenant une paroi de séparation des passages principal et auxiliaire; les éléments de canalisation comprennent une paroi fixe sensiblement perpendiculaire à l'axe de rotation de l'hélice, la paroi délimitant le passage auxiliaire, et étant accolée à la région périphérique, en aval dans le sens d'écoulement du flux d'air formé par la région périphérique de l'hélice.For this purpose, the present invention proposes a cooling device of the aforementioned type, characterized in that the helix comprises a peripheral region protruding, in at least one angular sector, from the periphery of the exchanger for capturing air in outside the exchanger, the motor-fan unit comprising elements for channeling the air captured by the peripheral region, the peripheral region being profiled so as to form a flow of air flowing mainly parallel to the axis of rotation of the helix the ducting elements delimit a main passage for the air sucked through the heat exchanger, and an auxiliary passage for the air captured by the peripheral region, the ducting elements comprising a separation wall of the main and auxiliary passages; the pipe elements comprise a fixed wall substantially perpendicular to the axis of rotation of the helix, the wall delimiting the auxiliary passage, and being contiguous to the peripheral region, downstream in the direction of flow of the formed air flow by the peripheral region of the propeller.

Selon d'autres modes de réalisation, le dispositif de refroidissement comprend une ou plusieurs des caractéristiques suivantes, prise(s) isolément ou selon toutes les combinaisons techniquement possibles :

  • les éléments de canalisation d'air définissent une sortie pour le passage principal et une sortie pour le passage auxiliaire séparées;
  • la région périphérique s'étend dans le passage auxiliaire, une région centrale de l'hélice s'étendant dans le passage principal, l'hélice comprenant une couronne délimitant la région centrale et la région périphérique, la couronne séparant les passages principal et auxiliaire;
  • les éléments de canalisation comprennent une buse délimitant intérieurement le passage principal, et un cadre entourant la buse et délimitant le passage auxiliaire avec une surface externe de la buse;
  • la région périphérique comprend des ailettes d'activation d'air, la tangente à chaque ailette dans un plan perpendiculaire à une direction radiale de l'hélice passant par l'ailette, faisant sensiblement en tout point de l'ailette un angle non nul avec l'axe de rotation de l'hélice ;
  • chaque ailette est courbe, et l'angle entre la tangente à chaque ailette dans un plan perpendiculaire à une direction radiale de l'hélice et l'axe de rotation est décroissant d'un bord d'attaque de l'ailette vers un bord de fuite de l'ailette.
According to other embodiments, the cooling device comprises one or more of the following characteristics, taken in isolation or in any technically possible combination:
  • the air duct elements define an outlet for the main passage and a separate auxiliary passage exit;
  • the peripheral region extends into the auxiliary passage, a central region of the helix extending in the main passage, the helix comprising a crown defining the central region and the peripheral region, the crown separating the main and auxiliary passages;
  • the pipe elements comprise a nozzle internally defining the main passage, and a frame surrounding the nozzle and delimiting the auxiliary passage with an outer surface of the nozzle;
  • the peripheral region comprises air activation fins, the tangent to each fin in a plane perpendicular to a radial direction of the helix passing through the fin, making substantially at any point of the fin a non-zero angle with the axis of rotation of the propeller;
  • each fin is curved, and the angle between the tangent to each fin in a plane perpendicular to a radial direction of the helix and the axis of rotation is decreasing from a leading edge of the fin to an edge of leakage of the fin.

L'invention concerne encore un véhicule automobile comprenant un dispositif de refroidissement tel que défini ci-dessus.The invention also relates to a motor vehicle comprising a cooling device as defined above.

L'invention et ses avantages seront mieux compris à la lecture de la description qui va suivre, donnée uniquement à titre d'exemple, et faite en se référant aux dessins annexés, sur lesquels :

  • la figure 1 est une vue schématique de face d'un dispositif de refroidissement conforme à l'invention ;
  • la figure 2 est une vue en coupe selon II-II du dispositif de la figure 1 ; et
  • la figure 3 est une vue schématique en perspective d'une hélice motorisée du dispositif de la figure 1.
The invention and its advantages will be better understood on reading the description which follows, given solely by way of example, and with reference to the appended drawings, in which:
  • the figure 1 is a schematic front view of a cooling device according to the invention;
  • the figure 2 is a sectional view along II-II of the device of the figure 1 ; and
  • the figure 3 is a schematic perspective view of a motorized propeller of the device of the figure 1 .

Tel que représenté sur les figures 1 et 2, le dispositif de refroidissement 2 comprend un échangeur de chaleur 4 (représenté uniquement par son contour en traits mixtes sur la figure 1) et un groupe moto-ventilateur 5, comportant une buse 6 de canalisation d'air, une hélice d'activation d'air 8, un moteur 9 d'entraînement de l'hélice 8, et un cadre 10 de support du groupe moto-ventilateur 5.As shown on the figures 1 and 2 , the cooling device 2 comprises a heat exchanger 4 (represented only by its outline in phantom on the figure 1 ) and a motor-fan unit 5, comprising an air duct nozzle 6, an air activation propeller 8, a propeller drive motor 9 and a frame 10 for supporting the motorcycle unit -ventilator 5.

Dans la suite de la description, les orientations utilisées sont les orientations usuelles des véhicules automobiles. Ainsi, les termes « avant », « arrière », « supérieur », et « inférieur » s'étendent par rapport à la direction et au sens d'avancement du véhicule automobile, schématisés par une flèche S sur la figure 2.In the remainder of the description, the orientations used are the usual orientations of motor vehicles. Thus, the terms "front", "rear", "upper" and "lower" extend with respect to the direction and direction of travel of the motor vehicle, shown schematically by an arrow S on the figure 2 .

L'échangeur 4 présente un contour sensiblement rectangulaire (figure 1), et est destiné à être traversé par un fluide à refroidir et par de l'air, en vue du refroidissement du fluide et du réchauffement de l'air.The exchanger 4 has a substantially rectangular contour ( figure 1 ), and is intended to be traversed by a fluid to be cooled and by air, in order to cool the fluid and to heat the air.

En se référant à la figure 1, la buse 6 comprend une ouverture avant rectangulaire 12, de contour sensiblement identique au contour de l'échangeur 4, et une ouverture arrière circulaire 14, les ouvertures 12, 14 s'étendant dans des plans sensiblement parallèles entre eux.Referring to the figure 1 , the nozzle 6 comprises a rectangular front opening 12, of contour substantially identical to the contour of the exchanger 4, and a circular rear opening 14, the openings 12, 14 extending in planes substantially parallel to each other.

L'ouverture 12 est plus grande que l'ouverture 14. Plus précisément, le diamètre de l'ouverture 14 est sensiblement égal à la hauteur h de l'ouverture 14, et inférieur à la largeur l de l'ouverture 14.The opening 12 is larger than the opening 14. More specifically, the diameter of the opening 14 is substantially equal to the height h of the opening 14, and less than the width l of the opening 14.

La buse 6 comprend des parois internes 16 convergeant de l'ouverture 12 vers l'ouverture 14.The nozzle 6 comprises internal walls 16 converging from the opening 12 to the opening 14.

La buse 6 comprend une platine centrale de support 18 s'étendant sensiblement dans le plan de l'ouverture 12, et fixée aux parois 16 par l'intermédiaire d'entretoises radiales 20 s'étendant entre la platine 18 et les parois 16. La platine 18 et les entretoises 20 forment une structure ajourée permettant le passage d'air à travers l'ouverture 12.The nozzle 6 comprises a central support plate 18 extending substantially in the plane of the opening 12, and fixed to the walls 16 by means of radial spacers 20 extending between the plate 18 and the walls 16. platinum 18 and the spacers 20 form a perforated structure allowing the passage of air through the opening 12.

En se référant à la figure 3, l'hélice 8 présente un axe de rotation R, et comprend un moyeu central 22, des pales d'activation d'air 24, par exemple au nombre de cinq et angulairement régulièrement espacées, s'étendant radialement vers l'extérieur à partir du moyeu 22, et une couronne 26 reliant les extrémités radiales extérieures des pales 24.Referring to the figure 3 , the propeller 8 has an axis of rotation R, and comprises a central hub 22, air activation blades 24, for example five in number and angularly regularly spaced, extending radially outwardly from the hub 22, and a ring 26 connecting the outer radial ends of the blades 24.

Les pâles 24 constituent une région centrale principale d'activation d'air, et sont vrillées pour forcer une circulation d'un flux d'air principal axialement selon l'axe R.The vanes 24 constitute a main central air activation region, and are twisted to force a circulation of a main air flow axially along the R axis.

L'hélice 8 comprend des ailettes d'activation d'air 28 s'étendant radialement vers l'extérieur à partir de la couronne 26. Les ailettes 28 sont par exemple au nombre de dix, et angulairement régulièrement réparties sur la circonférence de la couronne 26.The propeller 8 comprises air activation fins 28 extending radially outwardly from the ring 26. The fins 28 are for example ten in number, and angularly evenly distributed around the circumference of the crown. 26.

Les ailettes 28 constituent une région périphérique auxiliaire d'activation d'air, et sont profilées de façon à provoquer la circulation d'un flux d'air auxiliaire s'écoulant selon l'axe R, et dans le même sens que le flux d'air principal.The fins 28 constitute an auxiliary peripheral region of air activation, and are profiled so as to cause the circulation of a flow of auxiliary air flowing along the axis R, and in the same direction as the flow of air. main air.

A cet effet, chaque ailette 28 est inclinée par rapport à l'axe R de façon à imprimer à l'air un mouvement selon l'axe R.For this purpose, each fin 28 is inclined relative to the axis R so as to print in air a movement along the axis R.

Plus précisément, chaque ailette 28 s'étend entre un bord avant d'attaque 28a et un bord arrière de fuite 28b, de façon que la tangente à chaque ailette 28 dans un plan perpendiculaire à une direction radiale de l'hélice 8 et passant par l'ailette 28, fait sensiblement en tout point de l'ailette 28 un angle non nul avec l'axe R.More specifically, each fin 28 extends between a leading edge of attack 28 a and a rear trailing edge 28 b, so that the tangent to each blade 28 in a plane perpendicular to a radial direction of the propeller 8 and passing through the fin 28, is substantially at any point of the fin 28 a non-zero angle with the axis R.

L'hélice 8 est avantageusement réalisée d'un seul tenant, par exemple par moulage par injection de matière plastique.The propeller 8 is advantageously made in one piece, for example by plastic injection molding.

Dans le mode de réalisation représenté, chaque ailette 28 présente, entre ses bords 28a et 28b une épaisseur sensiblement constante, et est courbe, avec une courbure orientée axialement vers l'arrière, pour améliorer l'écoulement de l'air. L'angle de la tangente à chaque ailette 28 par rapport à l'axe R, tel que défini ci-dessus, est donc variable, et décroît du bord 28a vers le bord 28b, par exemple d'un angle θ1 de sensiblement 60° à un angle θ2 de sensiblement 30°.In the illustrated embodiment, each fin 28 has, between its edges 28 a and 28 b of substantially constant thickness, and is curved, with a curvature oriented axially towards the rear, to improve the flow of air. The angle of the tangent to each blade 28 with respect to the axis R, as defined above, is variable and decreases from edge 28 a to the edge 28 b, for example, an angle θ1 substantially 60 ° at an angle θ2 of substantially 30 °.

En se référant à la figure 2, l'hélice 8 a son moyeu 22 monté à rotation sur le moteur 9, lui-même fixé sur une face arrière de la platine 18.Referring to the figure 2 , the propeller 8 has its hub 22 rotatably mounted on the engine 9, itself fixed on a rear face of the plate 18.

L'hélice 8 est située en arrière de la buse 6, en travers de l'ouverture 14. La couronne 26 présente un diamètre sensiblement égal à celui de l'ouverture 14, de sorte que les pales 24 de l'hélice 8 sont situées en regard de l'ouverture 14, et que les ailettes 28 se situent radialement en dehors de l'ouverture 14.The propeller 8 is located behind the nozzle 6, across the opening 14. The ring 26 has a diameter substantially equal to that of the opening 14, so that the blades 24 of the propeller 8 are located facing the opening 14, and that the fins 28 are located radially out of the opening 14.

La buse 6 et l'hélice 8 sont montées sur le cadre 10, en regard d'une ouverture circulaire 32 de celui-ci, de même diamètre que l'ouverture 12 et la couronne 26.The nozzle 6 and the propeller 8 are mounted on the frame 10, facing a circular opening 32 thereof, of the same diameter as the opening 12 and the ring 26.

Plus précisément, le cadre 10 comprend un trou cylindrique 34 coaxial à l'ouverture 32 et possédant une paroi périphérique cylindrique 36, et une cloison annulaire 38 s'étendant radialement vers l'intérieur à partir de la paroi 36, un bord intérieur libre 40 de la cloison 38 délimitant l'ouverture 32.More specifically, the frame 10 comprises a cylindrical hole 34 coaxial with the opening 32 and having a cylindrical peripheral wall 36, and an annular partition 38 extending radially inwardly from the wall 36, a free inner edge 40 of the partition 38 defining the opening 32.

La paroi périphérique 36 présente un diamètre sensiblement égale au diamètre extérieur des ailettes 28, tout en étant légèrement supérieur.The peripheral wall 36 has a diameter substantially equal to the outer diameter of the fins 28, while being slightly greater.

Des dégagements 42 (figure 1) sont ménagés dans une face avant 44 du cadre 10 à la périphérie du trou 34. Les dégagements 42 délimitent un contour rectangulaire sensiblement de même dimension que l'ouverture 14.Clearances 42 ( figure 1 ) are formed in a front face 44 of the frame 10 at the periphery of the hole 34. The clearances 42 delimit a rectangular contour substantially of the same dimension as the opening 14.

La buse et l'hélice 8 sont disposées dans le trou 34, en regard de l'ouverture 32.The nozzle and the propeller 8 are arranged in the hole 34, facing the opening 32.

L'hélice 8 est reçue dans le trou 34, la couronne 26 étant alignée avec le bord 40, de façon que les pales 14 se situent en regard de l'ouverture 32, et les ailettes 28 se situent en regard de la cloison 38.The propeller 8 is received in the hole 34, the ring 26 being aligned with the edge 40, so that the blades 14 are located opposite the opening 32, and the fins 28 are located opposite the partition 38.

La buse 6 est reçue en partie dans le trou 34, devant l'hélice 8, et en partie dans les dégagements 42. La buse 6 est fixées sur le cadre 10, par exemple à l'aide d'organes de fixation (non représentés) traversant des orifices 45 (figure 1) de la buse 6, et vissés dans le cadre 10.The nozzle 6 is partially received in the hole 34, in front of the propeller 8, and partly in the recesses 42. The nozzle 6 is fixed to the frame 10, for example by means of fasteners (not shown ) passing through orifices 45 ( figure 1 ) of the nozzle 6, and screwed into the frame 10.

L'échangeur 4 est fixé devant la buse 6, en regard de l'ouverture 12.The exchanger 4 is fixed in front of the nozzle 6, facing the opening 12.

En vue suivant la direction X (figure 1), la buse 6 et l'échangeur 4 masquent le trou 34 et les ailettes 28, excepté dans un secteur supérieur A, et un secteur inférieur B, dans lesquelles les ailettes 28 et le trou 34 débordent de la périphérie de la buse 6 et de l'échangeur 4, du fait du diamètre extérieur de ailettes 28 supérieure à la hauteur h de la buse 6 et de l'échangeur 4.In view along direction X ( figure 1 ), the nozzle 6 and the exchanger 4 mask the hole 34 and the fins 28, except in an upper sector A, and a lower sector B, in which the fins 28 and the hole 34 protrude from the periphery of the nozzle 6 and of the exchanger 4, because of the outer diameter of fins 28 greater than the height h of the nozzle 6 and the exchanger 4.

Les ailettes 28 débordent sur deux côtés opposés de la buse 6. En variante, les ailettes 28 débordent sur un seul côté, ou sur plus de deux côtés de la buse 6.The fins 28 overflow on two opposite sides of the nozzle 6. In a variant, the fins 28 project on only one side, or on more than two sides of the nozzle 6.

Dans les secteurs A et B, le trou 34 débouche sur la face 44, à la périphérie de la buse 6 et de l'échangeur 4, par des entrées d'air respectivement 46, 48, délimitées entre la surface externe de la buse 6 et la paroi 36.In the sectors A and B, the hole 34 opens on the face 44, at the periphery of the nozzle 6 and the exchanger 4, by respective air inlets 46, 48 delimited between the outer surface of the nozzle 6 and the wall 36.

Le secteur A du trou 34 est un secteur de diamètre supérieur à celui du reste du trou 34, de façon que l'entrée 46 présente une aire supérieure à celle de l'entrée 48.The sector A of the hole 34 is a sector of diameter greater than that of the remainder of the hole 34, so that the inlet 46 has an area greater than that of the inlet 48.

Le dispositif 2 comprend un conduit 50 possédant une entrée 52 débouchant dans le trou 34, dans le secteur A et à proximité de la cloison 38, et une ou plusieurs sorties (non représentées) débouchant à distance. Les sorties débouchent dans un espace à refroidir, par exemple dans un boîtier électronique ou dans des freins du véhicule automobile.The device 2 comprises a conduit 50 having an inlet 52 opening into the hole 34, in the sector A and near the partition 38, and one or more outputs (not shown) opening remotely. The outlets open into a space to cool, for example in an electronic box or in the brakes of the motor vehicle.

En fonctionnement, l'hélice 8 est entraînée par le moteur 9 en rotation autour de son axe R.In operation, the propeller 8 is driven by the motor 9 in rotation about its axis R.

Les pales 14 aspirent un flux d'air principal à travers l'échangeur 4, comme illustré par les flèches F1.The blades 14 suck a main air flow through the exchanger 4, as illustrated by the arrows F1.

Ce flux d'air principal, traverse l'échangeur 4 en se réchauffant, et est canalisé en aval de l'échangeur 4 dans un passage d'air principal P1 délimité par la surface intérieure de la buse 6 et la surface intérieure de la couronne 28. Le flux d'air principal est évacué vers l'arrière de l'hélice 8.This main air flow, passes through the exchanger 4 while heating, and is channeled downstream of the exchanger 4 in a main air passage P1 delimited by the inner surface of the nozzle 6 and the inner surface of the crown 28. The main airflow is discharged to the rear of propeller 8.

Un passage d'air auxiliaire P2 est délimité entre la surface extérieure de la buse 6, la surface extérieure de la couronne 28, la paroi 36, et la cloison 38. Le passage P2 est séparé du passage P1, notamment par la buse 6 et la couronne 28. Ainsi, de l'air chaud circulant dans le passage P1 ne s'écoule pas dans le passage P2, de façon à ne pas perturber le refroidissement de l'espace à refroidir.An auxiliary air passage P2 is delimited between the outer surface of the nozzle 6, the outer surface of the ring 28, the wall 36, and the partition 38. The passage P2 is separated from the passage P1, in particular by the nozzle 6 and the ring 28. Thus, hot air circulating in the passage P1 does not flow in the passage P2, so as not to disturb the cooling of the space to be cooled.

Le passage P2 comprend une portion annulaire 56 et deux portions axiales 58 s'étendant entre la portion annulaire 56 et les entrée 46, 48, au-dessus et au-dessous de la buse 6.The passage P2 comprises an annular portion 56 and two axial portions 58 extending between the annular portion 56 and the inlet 46, 48, above and below the nozzle 6.

Les ailettes 28 s'étendent dans la portion annulaire 56. Les ailettes 28 forcent un flux d'air auxiliaire s'écoulant axialement vers l'arrière. Ce faisant, les ailettes 28 captent un flux d'air par les entrées 46 et 48 et les portions axiales 58, comme illustré par les flèches F2. L'air capté par les ailettes 28 est plaqué par celles-ci contre la cloison 38 qui est accolée aux ailettes 28. Il en résulte une augmentation de la pression de l'air contre la cloison 38 et dans la portion annulaire 56. L'air sous pression circule dans la portion annulaire 58 et s'évacue par la conduite 50, débouchant dans la portion annulaire 58, jusqu'à l'espace à refroidir.The fins 28 extend in the annular portion 56. The fins 28 force a flow of auxiliary air flowing axially rearwardly. In doing so, the fins 28 capture a flow of air through the inlets 46 and 48 and the axial portions 58, as illustrated by the arrows F2. The air captured by the fins 28 is pressed by them against the partition 38 which is contiguous to the fins 28. This results in an increase in the pressure of the air against the partition 38 and in the annular portion 56. The pressurized air circulates in the annular portion 58 and is evacuated through the pipe 50, opening into the annular portion 58, to the space to be cooled.

Les ailettes 28 configurées de façon à forcer un flux d'air axial permettent d'améliorer le débit d'air dans le passage P2, ce qui augmente le refroidissement de l'espace à refroidir. Avantageusement, ces ailettes sont réalisées dans un matériau relativement souple, comme par exemple du caoutchouc pour minimiser les jeux et par voie de conséquence, réduire les fuites.The fins 28 configured to force an axial air flow can improve the air flow in the passage P2, which increases the cooling of the space to be cooled. Advantageously, these fins are made of a relatively flexible material, such as rubber to minimize play and consequently reduce leakage.

La cloison 38, venue de matière avec le cadre 10 fixe, coopère avec la couronne 26 pour délimiter le passage P2 de façon suffisamment étanche.The partition 38, integral with the fixed frame 10, cooperates with the ring 26 to define the passage P2 sufficiently tight.

En variante, des échangeurs d'air supplémentaires sont disposés en aval de l'hélice, dans le flux d'air principal, de façon à utiliser le flux d'air principal comme source froide dans ces échangeurs supplémentaires.Alternatively, additional air exchangers are disposed downstream of the propeller, in the main air flow, so as to use the main air flow as a cold source in these additional exchangers.

Claims (7)

  1. Cooling device for a motor vehicle, of the type comprising a heat exchanger (4), and a motor fan unit (5) comprising a motorized propeller (8), rotatably disposed about an axis (R) opposite the exchanger (4), and intended to aspirate, on operation of the propeller (8), air through the heat exchanger (4), characterized in that the propeller (8) comprises a peripheral region (28) extending, in at least an angular sector (A, B), beyond the periphery of the exchanger (4) to capture air outside the exchanger (4), with the motor fan unit (5) comprising elements (6, 10, 26, 38, 50) for channelling the air captured by the peripheral region (28), the peripheral region (28) being profiled so as to form a flow of air (F2) flowing principally parallel to the rotation axis (R) of the propeller (8), the channelling elements (6, 10, 26, 38, 50) delimiting a main passage (P1) for the aspirated air through the heat exchanger (4), and an auxiliary passage (P2) for the air captured by the peripheral region (28), the channelling elements (6, 10, 26, 38, 50) comprising a separation wall (6, 26) of the main (P1) and auxiliary (P2) passages and a fixed wall (38) substantially perpendicular to the rotation axis (R) of the propeller (8), the wall (38) delimiting the auxiliary passage (P2) and being coupled to the peripheral region (28), downstream in the direction of flow of the flow of air formed by the peripheral region (28) of the propeller (8).
  2. Device according to Claim 1, characterized in that the air-channelling elements define a separate outlet (32) for the main passage (P1) and a separate outlet (50) for the auxiliary passage (P2).
  3. Device according to Claim 1 or 2, characterized in that the peripheral region (28) extends in the auxiliary passage (P2), with a central region (14) of the propeller (8) extending in the main passage (P1), the propeller (8) comprising a crown (26) delimiting the central region (14) and the peripheral region (28), with the crown (26) separating the main passage (P1) and the auxiliary passage (P2).
  4. Cooling device of Claim 3, characterized in that the channelling elements (6, 10, 26, 38, 50) comprise a nozzle (6) delimiting internally the main passage (P2), and a frame (10) surrounding the nozzle (6) and delimiting the auxiliary passage (P2) with an external surface of the nozzle (6).
  5. Cooling device according to any one of the preceding claims, characterized in that the peripheral region comprises air-activation blades (28), the tangent to each blade (28) in a plane perpendicular to a radial direction of the propeller passing through the blade (28) forming substantially at any point of the blade (28) an angle not equal to zero with the rotation axis (R) of the propeller (8).
  6. Cooling device according to Claim 5, characterized in that each blade (28) is curved, and the angle between the tangent to each blade (28) in a plane perpendicular to a radial direction of the propeller and the rotation axis (R) is decreasing from a leading edge (28a) of the blade (28) towards a trailing edge (28b) of the blade (28).
  7. Motor vehicle comprising a cooling device according to any one of Claims 1 to 6.
EP20060300540 2005-06-01 2006-05-31 Cooling device for a vehicle and the associated vehicle Not-in-force EP1728987B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0505564A FR2886672B1 (en) 2005-06-01 2005-06-01 COOLING DEVICE FOR MOTOR VEHICLE, MOTOR FAN ASSEMBLY FOR SUCH A DEVICE, AND CORRESPONDING MOTOR VEHICLE

Publications (2)

Publication Number Publication Date
EP1728987A1 EP1728987A1 (en) 2006-12-06
EP1728987B1 true EP1728987B1 (en) 2011-04-27

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP20060300540 Not-in-force EP1728987B1 (en) 2005-06-01 2006-05-31 Cooling device for a vehicle and the associated vehicle

Country Status (4)

Country Link
EP (1) EP1728987B1 (en)
AT (1) ATE507377T1 (en)
DE (1) DE602006021508D1 (en)
FR (1) FR2886672B1 (en)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2269636A1 (en) * 1974-04-18 1975-11-28 Saviem Cooling system for supercharged diesel engine - uses air drawn through radiator to cool air from supercharger
DE59108887D1 (en) * 1991-08-30 1997-12-11 Weinhold Wolfgang P M Sc Dipl Cooling device for an internal combustion engine in a motor vehicle
DE4136282C1 (en) * 1991-11-04 1993-05-06 Adam Opel Ag, 6090 Ruesselsheim, De

Also Published As

Publication number Publication date
EP1728987A1 (en) 2006-12-06
DE602006021508D1 (en) 2011-06-09
ATE507377T1 (en) 2011-05-15
FR2886672B1 (en) 2007-09-21
FR2886672A1 (en) 2006-12-08

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