WO2006063825A1 - Ventilating system comprising means for limiting backflow - Google Patents

Ventilating system comprising means for limiting backflow Download PDF

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Publication number
WO2006063825A1
WO2006063825A1 PCT/EP2005/013475 EP2005013475W WO2006063825A1 WO 2006063825 A1 WO2006063825 A1 WO 2006063825A1 EP 2005013475 W EP2005013475 W EP 2005013475W WO 2006063825 A1 WO2006063825 A1 WO 2006063825A1
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WO
WIPO (PCT)
Prior art keywords
radial
fan
annular
axial
flow
Prior art date
Application number
PCT/EP2005/013475
Other languages
French (fr)
Inventor
Stéphane MOREAU
Manuel Henner
Aurélien LEVASSEUR
Bruno Demory
Original Assignee
Valeo Systemes D'essuyage
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 Valeo Systemes D'essuyage filed Critical Valeo Systemes D'essuyage
Publication of WO2006063825A1 publication Critical patent/WO2006063825A1/en

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Classifications

    • 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
    • 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

Definitions

  • the invention proposes a fan system which comprises means for limiting the flow rate of the flow of air flowing against the current in an annular duct extending between the fan and the peripheral shroud.
  • the invention more particularly proposes a fan system, in particular for cooling the motor of a motor vehicle, comprising a fan mounted for rotation around a principal axis A of rotation with respect to a peripheral fairing of the fan which is fixed to the the engine of the vehicle, so as to produce a flow of air generally coaxial with the main axis A of rotation of the fan, wherein the fan comprises:
  • Blades angularly distributed around the main axis A of rotation, and each of which extends generally radially outwardly of the fan from the central core;
  • each axial wall extending in a generally axial plane, and extending radially from the concave inner cylindrical face of the shroud, such that its axial free radial end edge is located at a distance from the convex outer cylindrical face of the annular skirt; and an inner annular radial cheek which extends radially inwardly of the fairing from the concave inner cylindrical face of the fairing.
  • a conventional system for cooling the engine of a motor vehicle comprises in particular a heat exchanger, or radiator, which is traversed by a coolant liquid, called coolant, and a fan system for producing a flow of air through the radiator.
  • a certain quantity of the heat of the coolant is then dissipated in this air flow passing through the radiator, which makes it possible to reduce the temperature of the coolant.
  • the fan system includes a helical fan which is rotatably mounted relative to a shroud around an axis generally coaxial with the airflow to be produced.
  • the fairing attached to the radiator, it carries a fan drive motor in rotation, and it extends radially around the fan, so that it has a concave inner cylindrical face which extends radially vis-à-vis an outer annular face of the peripheral skirt of the fan.
  • the concave inner cylindrical face of the shroud and the outer annular face of the peripheral skirt of the ventilator define an annular duct in which part of the air flow produced by the fan is able to flow against the current relative to the flow of the fan. main air flow.
  • This part of the main airflow forms a spurious airflow that reduces the overall efficiency of the fan system.
  • the fan system comprises a set of axial walls and a cheek annular radial carried by the shroud and an annular radial rib carried by the fan, which are arranged in the annular conduit.
  • the radial fairing of the fairing and the radial rib of the fan are shaped so as to reduce the axial component value of the parasitic flux, and the walls are arranged so as to reduce the tangential component value of the parasitic air flow, compared with the main axis of the airflow produced by the fan.
  • the document WO-A-02.38962 describes such a fan system for which the radial fairing of the fairing is arranged downstream of the axial walls and the radial rib of the fan is arranged upstream of the axial walls.
  • the pressurized air that is present in all the axial ducts produces a resistant torque between the fairing and the fan, which reduces the overall efficiency of the fan system.
  • the object of the invention is to propose a fan system which comprises means for limiting the formation of the parasitic air flow without increasing the value of the resistive torque.
  • the invention proposes a fan system as described above, characterized in that the radial cheek is arranged axially upstream of the axial walls, with respect to the direction of flow of the air flow. According to other features of the invention:
  • the radial cheek comprises an annular radial face downstream with respect to the direction of flow of the air flow which is connected to the annular edge of the free radial end of the radial cheek radially with the axial edge of free radial end of each axial wall;
  • the radial cheek is arranged downstream and at a distance from the radial rib, with respect to the direction of flow of the air flow;
  • the annular free radial end edge of the radial flange extends radially vis-à-vis and at a distance from the convex outer cylindrical face of the annular skirt;
  • the downstream end edge of the annular skirt is located upstream of the downstream end edge of each axial wall, relative to the direction of flow of the air flow;
  • downstream end edge of the annular skirt is situated axially in line with the downstream end edge of each axial wall;
  • the downstream end edge of the annular skirt is located downstream of the upstream end edge of each axial wall, relative to the flow direction of the air flow.
  • FIG. 1 is a schematic perspective view of a fan system comprising a fairing and a fan according to the invention
  • FIG. 2 is a detail on a larger scale and with tearing of the fan system shown in Figure 1;
  • FIG. 3 is a section of the fan system shown in Figure 2, in an axial plane located angularly between two consecutive axial walls.
  • upstream-downstream orientation will also be adopted as being the axial direction relative to the main axis of rotation and from the top to the bottom with reference to the figures.
  • fan system 10 which is a component of an engine cooling system of a motor vehicle (not shown).
  • the fan system 10 includes a peripheral fairing 14 which is attached to the vehicle radiator (not shown) and a fan 12 which is rotatably mounted relative to the fairing 14 about a main axis A of rotation.
  • the fan 12 comprises a central core 16 through which the fan 12 is mounted on a drive shaft (not shown) in rotation about the main axis A of main rotation rotation.
  • the core 16 is an element of revolution coaxial with the main axis A of main rotation rotation, and it mainly comprises a central annular radial wall 16a which carries mounting means on the drive shaft (not shown), and an outer cylindrical wall 16b.
  • the fan 12 comprises blades 18 which are distributed angularly about the main axis A of rotation, and each of which extends radially outwardly from the outer cylindrical wall 16b of the core.
  • the fan 12 is a fan of the helical type, that is to say that the blades 18 are shaped so as to produce a main air flow "G" ( Figure 3) coaxial with the main axis A of rotation when the rotation of the fan 12.
  • the fan 12 also comprises a peripheral annular skirt 20 which extends coaxially with the main axis A of rotation, and whose concave inner cylindrical face 20i is connected to the outer radial end 18a of each blade 18.
  • the shroud 14 extends radially around the fan 12, and it has a concave inner cylindrical face 14i coaxial with the main axis A of rotation which is located radially in facing relation to and away from the convex outer cylindrical face 20e of the annular skirt 20.
  • the figures show a fairing 14 which is annular in shape coaxial with the main axis A of main rotation rotation.
  • shape of the fairing 14 is not limited to this single annular shape.
  • the external cylindrical face 20e of the annular skirt 20 and the internal cylindrical face 14i of the fairing delimit an annular duct 22 coaxial with the main axis A of rotation.
  • the fan 12 When the fan system 10 is in operation, the fan 12 produces the main air flow "G", and the air pressure downstream of the fan 12 is greater than the air pressure upstream of the fan 12. difference in air pressure between the upstream and downstream of the fan 12 promotes the flow of a portion of the main air flow "G" in the annular duct 22.
  • This part of the main air flow "G” forms a parasitic air flow "F” which circulates in the annular duct 22 against the short circuit relative to the main air flow "G", that is to say from downstream to upstream, thereby reducing the total air flow produced by the fan system 10.
  • the parasitic "F” air flow is consequently also driven in a rotational movement around the main axis A of rotation, before it enters the annular duct 22, that is to say it comprises an axial component, and a tangential component, with respect to the main axis A of rotation.
  • the fan 12 comprises an external annular radial rib 24 which extends radially outwardly of the fan 12 from the outer cylindrical face 20e of the annular skirt 20, and the fairing 14 carries a series of generally axial walls 26 which are angularly distributed around the main axis A rotation at a constant interval, and an inner annular radial cheek 28 coaxial with the main axis A of rotation.
  • the radial rib 24 extends inside the annular duct 22 so that its free radial end annular edge 24a extends opposite and at a distance from the internal cylindrical face 14i of the fairing 14.
  • the radial flange 28 extends in a radial plane relative to the main axis A of rotation and extends radially inside the annular duct 22 from the inner cylindrical face 14i of the fairing 14 so that its annular edge free radial end 28a extends vis-à-vis and away from the outer cylindrical face 20e of the annular skirt 20.
  • Each axial wall 26 extends in a generally axial plane relative to the main axis A of rotation, and it extends radially inside the annular duct 22 from the inner cylindrical face 14i of the fairing 14 so that its axial edge of free radial end 26a extends opposite and at a distance from the outer cylindrical face 20e of the annular skirt 20.
  • the axial walls 26, the radial cheek 28 and the radial rib 24 cooperate with each other so as to reduce the formation of the flow "F" of stray air.
  • the axial walls 26, the radial flange 28 and the radial rib 24 are arranged axially in
  • the annular duct 22 so that the radial cheek 28 is arranged upstream of the axial walls, with respect to the direction of flow of the main air flow G.
  • the radial rib 24 is arranged axially upstream with respect to the axial walls 26 and with respect to the radial cheek 28, that is to say that the radial cheek 28 is arranged axially between the axial walls 26 of a part and the radial rib 24 on the other hand.
  • the radial flange 28 comprises a downstream annular radial face 28b (FIG. 3) which is connected to the upstream end radial edge 26b of each axial wall 26.
  • the annular duct 22 is divided by the radial cheek
  • the downstream portion 22a of the annular duct 22 is divided by the axial walls 26 into a plurality of parallel axial channels 30 which are distributed angularly about the main axis A of rotation.
  • the axial channels 30 are shaped so that when the parasitic "F" air flow enters the downstream portion 22a, the parasitic "F” air flow divides into several streams. secondary 32.
  • the tangential component of the parasitic "F" air flow causes a vortex movement of each secondary flow 32 around the main axis B of the associated axial channel 30.
  • each secondary stream 32 mixes with the other secondary streams 32 to form the parasitic "F" air flow again.
  • the parasitized "F” air flow thus reformed opens out from the downstream portion 22a of the annular duct 22 and then enters the upstream portion 22b of the annular duct 22.
  • the radial cheek 28 and the radial rib 24 are arranged in the upstream portion 22b of the annular duct 22 so that they form a baffle which creates a significant pressure drop in the air flow. "F" parasite running through it.
  • the pressure drop experienced by the parasitic "F” air flow makes it possible to significantly limit the flow rate of the parasitic "F” air flow.
  • the pressure drop is formed at the upstream portion 22b of the annular duct 22, it therefore does not cause an increase in the air pressure in the annular duct 22, and therefore the value of the resistant torque is not significantly increased despite the presence of this chicane.
  • the radial flange 28 is shaped so that its downstream annular radial face 28b is connected to the upstream end radial edge 26b of each axial wall 26.
  • the radial flange 28 extends radially from the concave inner cylindrical face 14i of the fairing 14 so that its free radial end annular edge 28 is flush with the radially free end axial edge 26a of each wall 26.
  • downstream end edge 20a of the annular skirt 20 is situated axially upstream of the downstream end edge 26c of each axial wall 26 and downstream of the upstream end radial edge 26b of each axial wall 26.
  • each axial duct 30 opens out radially towards the inside of the control system.
  • fan 10 which facilitates the penetration of each secondary flow 32 in the associated axial duct 30, in a direction tangential to the main axis A of rotation, thereby promoting the vortex movement of each secondary flow 32 in the duct axial 30 associated.
  • each secondary stream 32 penetrates axially into the associated axial duct 30.
  • the downstream end edge 20a of the annular skirt 20 is situated axially in line with the downstream end edge 26c of each axial wall 26, and according to yet another variant embodiment of this aspect of the invention, the downstream end edge 20a of the annular skirt 20 is located axially downstream of the downstream end edge 26c of each axial wall 26.
  • the radial rib 24 is positioned axially on the annular skirt 20 so that it extends radially from the upstream end edge 20c of the annular skirt 20.
  • the invention is not limited to this embodiment of the annular skirt 20 and the radial rib 24, and that the radial rib 24 can be located axially downstream of the upstream end edge 20c of the annular skirt 20.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention concerns a ventilating system (10) comprising a fan (12) mounted rotatable about a main axis (A) of rotation relative to a shroud (14), wherein the fan (12) includes an annular peripheral skirt (20) and an outer radial rib (20) extending from the outer cylindrical surface (20e) of the annular skirt (20), and wherein the shroud (14) comprises: an inner cylindrical surface (14i) extending spaced away from and opposite the outer cylindrical surface (20e) of the annular skirt (20); a series of axial walls (26) which are angularly distributed about the main axis (A) of rotation and an inner flange (28) extending inwards of the shroud (14) from the inner cylindrical surface (14i) of the shroud (14), characterized in that the radial flange (28) is arranged axially upstream of the axial walls (36).

Description

"Système de ventilateur comportant des moyens de limitation du débit d'air parasite." "Fan system having means for limiting the flow of stray air."
L'invention propose un système de ventilateur qui comporte des moyens pour limiter le débit du flux d'air circulant à contre courant dans un conduit annulaire s'étendant entre le ventilateur et le carénage périphérique.The invention proposes a fan system which comprises means for limiting the flow rate of the flow of air flowing against the current in an annular duct extending between the fan and the peripheral shroud.
L'invention propose plus particulièrement un système de ventilateur, notamment pour le refroidissement du moteur d'un véhicule automobile, comportant un ventilateur monté à rotation autour d'un axe principal A de rotation par rapport à un carénage périphérique au ventilateur qui est fixé au moteur du véhicule, de manière à produire un flux d'air globalement coaxial à l'axe principal A de rotation du ventilateur, dans lequel le ventilateur comporte :The invention more particularly proposes a fan system, in particular for cooling the motor of a motor vehicle, comprising a fan mounted for rotation around a principal axis A of rotation with respect to a peripheral fairing of the fan which is fixed to the the engine of the vehicle, so as to produce a flow of air generally coaxial with the main axis A of rotation of the fan, wherein the fan comprises:
- un noyau central de montage sur un arbre d'entraînement en rotation du ventilateur ;a central mounting core on a drive shaft in rotation of the fan;
- des pales réparties angulairement autour de l'axe principal A de rotation, et dont chacune s'étend globalement radialement vers l'extérieur du ventilateur depuis le noyau central ;- Blades angularly distributed around the main axis A of rotation, and each of which extends generally radially outwardly of the fan from the central core;
- une jupe annulaire périphérique coaxiale à l'axe principal A de rotation, dont une face cylindrique interne concave est fixée à l'extrémité radiale externe de chaque pale ; - et une nervure radiale annulaire externe qui s'étend radialement vers l'extérieur du ventilateur, depuis la face cylindrique externe convexe de la jupe annulaire, et dans lequel le carénage comporte :- A peripheral annular skirt coaxial with the main axis A of rotation, a concave inner cylindrical face is fixed to the outer radial end of each blade; and an outer annular radial rib which extends radially outwardly of the fan, from the convex outer cylindrical face of the annular skirt, and wherein the fairing comprises:
- une face cylindrique interne concave qui s'étend radialement à distance et en vis-à-vis de la face cylindrique externe convexe de la jupe annulaire ;- A concave inner cylindrical face which extends radially at a distance and vis-à-vis the convex outer cylindrical face of the annular skirt;
- une série de murets généralement axiaux qui sont répartis angulairement autour de l'axe principal A de rotation, chaque muret axial s'étendant dans un plan généralement axial, et s'étendant radialement depuis la face cylindrique interne concave du carénage, de manière que son bord axial d'extrémité radiale libre est situé à distance de la face cylindrique externe convexe de la jupe annulaire ; - et une joue radiale annulaire interne qui s'étend radialement vers l'intérieur du carénage depuis la face cylindrique interne concave du carénage.a series of generally axial walls which are distributed angularly around the main axis A of rotation, each axial wall extending in a generally axial plane, and extending radially from the concave inner cylindrical face of the shroud, such that its axial free radial end edge is located at a distance from the convex outer cylindrical face of the annular skirt; and an inner annular radial cheek which extends radially inwardly of the fairing from the concave inner cylindrical face of the fairing.
Un système conventionnel pour le refroidissement du moteur d'un véhicule automobile comporte notamment un échangeur thermique, ou radiateur, qui est traversé par un liquide caloporteur, appelé liquide de refroidissement, et un système de ventilateur de production d'un flux d'air traversant le radiateur.A conventional system for cooling the engine of a motor vehicle comprises in particular a heat exchanger, or radiator, which is traversed by a coolant liquid, called coolant, and a fan system for producing a flow of air through the radiator.
Une certaine quantité de la chaleur du liquide de refroidissement est alors dissipée dans ce flux d'air traversant le radiateur, ce qui permet de réduire la température du liquide de refroidissement.A certain quantity of the heat of the coolant is then dissipated in this air flow passing through the radiator, which makes it possible to reduce the temperature of the coolant.
Le système de ventilateur comporte un ventilateur de type hélicoïdal qui est monté à rotation par rapport à un carénage autour d'un axe globalement coaxial au flux d'air à produire. Le carénage fixé au radiateur, il porte un moteur d'entraînement du ventilateur en rotation, et il s'étend radialement autour du ventilateur, de manière qu'il comporte une face cylindrique interne concave qui s'étend radialement en vis-à-vis d'une face annulaire externe de la jupe périphérique du ventilateur.The fan system includes a helical fan which is rotatably mounted relative to a shroud around an axis generally coaxial with the airflow to be produced. The fairing attached to the radiator, it carries a fan drive motor in rotation, and it extends radially around the fan, so that it has a concave inner cylindrical face which extends radially vis-à-vis an outer annular face of the peripheral skirt of the fan.
La face cylindrique interne concave du carénage et la face annulaire externe de la jupe périphérique du .ventilateur délimitent un conduit annulaire dans lequel une partie du flux d'air produit par le ventilateur est apte à circuler à contre courant par rapport à l'écoulement du flux d'air principal.The concave inner cylindrical face of the shroud and the outer annular face of the peripheral skirt of the ventilator define an annular duct in which part of the air flow produced by the fan is able to flow against the current relative to the flow of the fan. main air flow.
Cette partie du flux d'air principal forme un flux d'air parasite qui réduit l'efficacité globale du système de ventilateur.This part of the main airflow forms a spurious airflow that reduces the overall efficiency of the fan system.
Pour limiter le débit de ce flux d'air parasite, le système de ventilateur comporte un ensemble de murets axiaux et une joue radiale annulaire portés par le carénage et une nervure radiale annulaire portée par le ventilateur, qui sont agencés dans le conduit annulaire.To limit the flow of this spurious air flow, the fan system comprises a set of axial walls and a cheek annular radial carried by the shroud and an annular radial rib carried by the fan, which are arranged in the annular conduit.
La joue radiale du carénage et la nervure radiale du ventilateur sont conformées de manière à réduire la valeur de composante axiale du flux parasite, et les murets sont agencés de manière à réduire la valeur de composante tangentielle du flux d'air parasite, par rapport à l'axe principal du flux d'air produit par le ventilateur. Le document WO-A-02.38962 décrit un tel système de ventilateur pour lequel la joue radiale du carénage est agencée en aval des murets axiaux et la nervure radiale du ventilateur est agencée en amont des murets axiaux.The radial fairing of the fairing and the radial rib of the fan are shaped so as to reduce the axial component value of the parasitic flux, and the walls are arranged so as to reduce the tangential component value of the parasitic air flow, compared with the main axis of the airflow produced by the fan. The document WO-A-02.38962 describes such a fan system for which the radial fairing of the fairing is arranged downstream of the axial walls and the radial rib of the fan is arranged upstream of the axial walls.
Cependant, bien qu'elle permette de réduire de manière efficace la formation du flux d'air parasite, une telle disposition de la joue radiale et de la nervure radiale par rapport aux murets axiaux provoque une augmentation de la pression d'air dans les conduits axiaux délimités par les murets axiaux.However, although it makes it possible to effectively reduce the formation of the parasitic air flow, such an arrangement of the radial cheek and the radial rib with respect to the axial walls causes an increase in the air pressure in the ducts. axial delimited by the axial walls.
L'air pressurisé qui est présent dans l'ensemble des conduits axiaux produit un couple résistant entre le carénage et le ventilateur, qui réduit le rendement général du système de ventilateur.The pressurized air that is present in all the axial ducts produces a resistant torque between the fairing and the fan, which reduces the overall efficiency of the fan system.
L'invention a pour but de proposer un système de ventilateur qui comporte des moyens pour limiter la formation du flux d'air parasite, sans augmenter la valeur du couple résistant.The object of the invention is to propose a fan system which comprises means for limiting the formation of the parasitic air flow without increasing the value of the resistive torque.
Dans ce but, l'invention propose un système de ventilateur tel que décrit précédemment, caractérisé en ce que la joue radiale est agencée axialement en amont des murets axiaux, par rapport au sens d'écoulement du flux d'air. Selon d'autres caractéristiques de l'invention :For this purpose, the invention proposes a fan system as described above, characterized in that the radial cheek is arranged axially upstream of the axial walls, with respect to the direction of flow of the air flow. According to other features of the invention:
- la joue radiale comporte une face radiale annulaire aval par rapport au sens d'écoulement du flux d'air qui est reliée au bord annulaire d'extrémité radiale libre de la joue radiale affleure radialement avec le bord axial d'extrémité radiale libre de chaque muret axial ;the radial cheek comprises an annular radial face downstream with respect to the direction of flow of the air flow which is connected to the annular edge of the free radial end of the radial cheek radially with the axial edge of free radial end of each axial wall;
- la joue radiale est agencée en aval et à distance de la nervure radiale, par rapport au sens d'écoulement du flux d'air ; - le bord annulaire d'extrémité radiale libre de la joue radiale s'étend radialement en vis-à-vis et à distance de la face cylindrique externe convexe de la jupe annulaire ;- The radial cheek is arranged downstream and at a distance from the radial rib, with respect to the direction of flow of the air flow; - The annular free radial end edge of the radial flange extends radially vis-à-vis and at a distance from the convex outer cylindrical face of the annular skirt;
- le bord d'extrémité aval de la jupe annulaire est situé en amont du bord d'extrémité aval de chaque muret axial, par rapport au sens d'écoulement du flux d'air ;- The downstream end edge of the annular skirt is located upstream of the downstream end edge of each axial wall, relative to the direction of flow of the air flow;
- le bord d'extrémité aval de la jupe annulaire est situé axialement au droit du bord d'extrémité aval de chaque muret axial ;the downstream end edge of the annular skirt is situated axially in line with the downstream end edge of each axial wall;
- le bord d'extrémité aval de la jupe annulaire est situé en aval du bord d'extrémité amont de chaque muret axial, par rapport au sens d'écoulement du flux d'air.- The downstream end edge of the annular skirt is located downstream of the upstream end edge of each axial wall, relative to the flow direction of the air flow.
D'autres caractéristiques et avantages de l'invention apparaîtront à la lecture de la description détaillée qui suit pour la compréhension de laquelle on se reportera aux figures annexées parmi lesquelles :Other characteristics and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the appended figures among which:
- la figure 1 est une représentation schématique en perspective d'un système de ventilateur comportant un carénage et un ventilateur conformes à l'invention ;- Figure 1 is a schematic perspective view of a fan system comprising a fairing and a fan according to the invention;
- la figure 2 est un détail à plus grande échelle et avec arrachement du système de ventilateur représenté à la figure 1 ;- Figure 2 is a detail on a larger scale and with tearing of the fan system shown in Figure 1;
- la figure 3 est une section du système de ventilateur représenté à la figure 2, suivant un plan axial situé angulairement entre deux murets axiaux consécutifs.- Figure 3 is a section of the fan system shown in Figure 2, in an axial plane located angularly between two consecutive axial walls.
Dans la description qui va suivre, des éléments identiques, similaires ou analogues seront désignés par les mêmes chiffres de référence. On adoptera aussi l'orientation d'amont en aval comme étant la direction axiale par rapport à l'axe principal A de rotation et du haut vers le bas en se reportant aux figures.In the following description, identical, similar or similar elements will be designated by the same reference numerals. The upstream-downstream orientation will also be adopted as being the axial direction relative to the main axis of rotation and from the top to the bottom with reference to the figures.
On a représenté aux figures un système de ventilateur 10 qui est un composant d'un système de refroidissement du moteur d'un véhicule automobile (non représenté).There is shown in the figures a fan system 10 which is a component of an engine cooling system of a motor vehicle (not shown).
Le système de ventilateur 10 comporte un carénage 14 périphérique qui est fixé au radiateur du véhicule (non représenté) et un ventilateur 12 qui est monté à rotation par rapport au carénage 14 autour d'un axe principal A de rotation.The fan system 10 includes a peripheral fairing 14 which is attached to the vehicle radiator (not shown) and a fan 12 which is rotatably mounted relative to the fairing 14 about a main axis A of rotation.
Le ventilateur 12 comporte un noyau central 16 par l'intermédiaire duquel le ventilateur 12 est monté sur un arbre d'entraînement (non représenté) en rotation autour de l'axe principal A de rotation principal de rotation. Le noyau 16 est un élément de révolution coaxial à l'axe principal A de rotation principal de rotation, et il comporte principalement une paroi radiale annulaire centrale 16a qui porte des moyens de montage sur l'arbre d'entraînement (non représentés), et une paroi cylindrique externe 16b. Le ventilateur 12 comporte des pales 18 qui sont réparties angulairement autour de l'axe principal A de rotation, et dont chacune s'étend radialement vers l'extérieur depuis Ia paroi cylindrique externe 16b du noyau.The fan 12 comprises a central core 16 through which the fan 12 is mounted on a drive shaft (not shown) in rotation about the main axis A of main rotation rotation. The core 16 is an element of revolution coaxial with the main axis A of main rotation rotation, and it mainly comprises a central annular radial wall 16a which carries mounting means on the drive shaft (not shown), and an outer cylindrical wall 16b. The fan 12 comprises blades 18 which are distributed angularly about the main axis A of rotation, and each of which extends radially outwardly from the outer cylindrical wall 16b of the core.
Le ventilateur 12 est un ventilateur du type hélicoïdal, c'est-à-dire que les pales 18 sont conformées de manière à produire un flux d'air principal "G" (figure 3) coaxial à l'axe principal A de rotation lors de la rotation du ventilateur 12.The fan 12 is a fan of the helical type, that is to say that the blades 18 are shaped so as to produce a main air flow "G" (Figure 3) coaxial with the main axis A of rotation when the rotation of the fan 12.
Le ventilateur 12 comporte aussi une jupe annulaire périphérique 20 qui s'étend coaxialement à l'axe principal A de rotation, et dont la face cylindrique interne concave 2Oi est reliée à l'extrémité radiale externe 18a de chaque pale 18.The fan 12 also comprises a peripheral annular skirt 20 which extends coaxially with the main axis A of rotation, and whose concave inner cylindrical face 20i is connected to the outer radial end 18a of each blade 18.
Le carénage 14 s'étend radialement autour du ventilateur 12, et il comporte une face cylindrique interne concave 14i coaxiale à l'axe principal A de rotation qui est située radialement en vis-à-vis et à distance de la face cylindrique externe convexe 20e de la jupe annulaire 20.The shroud 14 extends radially around the fan 12, and it has a concave inner cylindrical face 14i coaxial with the main axis A of rotation which is located radially in facing relation to and away from the convex outer cylindrical face 20e of the annular skirt 20.
On a représenté aux figures un carénage 14 qui est de forme annulaire coaxiale à l'axe principal A de rotation principal de rotation. Cependant, il sera compris que la forme du carénage 14 n'est pas limitée à cette seule forme annulaire.The figures show a fairing 14 which is annular in shape coaxial with the main axis A of main rotation rotation. However, it will be understood that the shape of the fairing 14 is not limited to this single annular shape.
Comme on peut le voir plus en détail à la figure 3, la face cylindrique externe 20e de la jupe annulaire 20 et la face cylindrique interne 14i du carénage délimitent un conduit annulaire 22 coaxial à l'axe principal A de rotation.As can be seen in more detail in FIG. 3, the external cylindrical face 20e of the annular skirt 20 and the internal cylindrical face 14i of the fairing delimit an annular duct 22 coaxial with the main axis A of rotation.
Lorsque le système de ventilateur 10 est en fonctionnement, le ventilateur 12 produit le flux d'air principal "G", et la pression d'air en aval du ventilateur 12 est supérieure à la pression d'air en amont du ventilateur 12. La différence de pression d'air entre l'amont et l'aval du ventilateur 12 favorise l'écoulement d'une partie du flux d'air principal "G" dans le conduit annulaire 22.When the fan system 10 is in operation, the fan 12 produces the main air flow "G", and the air pressure downstream of the fan 12 is greater than the air pressure upstream of the fan 12. difference in air pressure between the upstream and downstream of the fan 12 promotes the flow of a portion of the main air flow "G" in the annular duct 22.
Cette partie du flux d'air principal "G" forme un flux d'air parasite "F" qui circule dans le conduit annulaire 22 à contre courtant par rapport au flux d'air principal "G", c'est-à-dire de l'aval vers l'amont, et qui réduit par conséquent le débit d'air total produit par le système de ventilateur 10.This part of the main air flow "G" forms a parasitic air flow "F" which circulates in the annular duct 22 against the short circuit relative to the main air flow "G", that is to say from downstream to upstream, thereby reducing the total air flow produced by the fan system 10.
Par ailleurs, la rotation du ventilateur 12 par rapport au carénage 14, qui permet d'obtenir l'écoulement axial du flux d'air principal "G", par rapport à l'axe principal A de rotation, provoque aussi un mouvement de rotation du flux d'air principal "G" autour de l'axe principal A de rotation.Furthermore, the rotation of the fan 12 relative to the shroud 14, which makes it possible to obtain the axial flow of the main air flow "G", with respect to the main axis A of rotation, also causes a rotational movement. the main air flow "G" around the main axis A of rotation.
Le flux d'air "F" parasite est par conséquent animé lui aussi d'un mouvement de rotation autour de l'axe principal A de rotation, avant qu'il ne pénètre dans le conduit annulaire 22, c'est-à-dire qu'il comporte une composante axiale, et une composante tangentielle, par rapport à l'axe principal A de rotation. Pour limiter Ie débit de ce flux "F" d'air parasite, le ventilateur 12 comporte une nervure radiale 24 annulaire externe qui s'étend radialement vers l'extérieur du ventilateur 12 depuis la face cylindrique externe 20e de la jupe annulaire 20, et le carénage 14 porte une série de muret généralement axiaux 26 qui sont répartis angulairement autour de l'axe principal A de rotation à intervalle constant, et une joue radiale annulaire interne 28 coaxiale à l'axe principal A de rotation.The parasitic "F" air flow is consequently also driven in a rotational movement around the main axis A of rotation, before it enters the annular duct 22, that is to say it comprises an axial component, and a tangential component, with respect to the main axis A of rotation. To limit the flow rate of this "F" flow of parasitic air, the fan 12 comprises an external annular radial rib 24 which extends radially outwardly of the fan 12 from the outer cylindrical face 20e of the annular skirt 20, and the fairing 14 carries a series of generally axial walls 26 which are angularly distributed around the main axis A rotation at a constant interval, and an inner annular radial cheek 28 coaxial with the main axis A of rotation.
La nervure radiale 24 s'étend à l'intérieur du conduit annulaire 22 de manière que son bord annulaire d'extrémité radiale libre 24a s'étend en vis-à-vis et à distance de la face cylindrique interne 14i du carénage 14.The radial rib 24 extends inside the annular duct 22 so that its free radial end annular edge 24a extends opposite and at a distance from the internal cylindrical face 14i of the fairing 14.
La joue radiale 28 s'étend dans un plan radial par rapport à l'axe principal A de rotation et elle s'étend radialement à l'intérieur du conduit annulaire 22 depuis la face cylindrique interne 14i du carénage 14 de manière que son bord annulaire d'extrémité radiale libre 28a s'étend en vis-à-vis et à distance de la face cylindrique externe 20e de la jupe annulaire 20.The radial flange 28 extends in a radial plane relative to the main axis A of rotation and extends radially inside the annular duct 22 from the inner cylindrical face 14i of the fairing 14 so that its annular edge free radial end 28a extends vis-à-vis and away from the outer cylindrical face 20e of the annular skirt 20.
Chaque muret axial 26 s'étend dans un plan généralement axial par rapport à l'axe principal A de rotation, et il s'étend radialement à l'intérieur du conduit annulaire 22 depuis la face cylindrique interne 14i du carénage 14 de manière que son bord axial d'extrémité radiale libre 26a s'étend en vis-à-vis et à distance de la face cylindrique externe 20e de la jupe annulaire 20.Each axial wall 26 extends in a generally axial plane relative to the main axis A of rotation, and it extends radially inside the annular duct 22 from the inner cylindrical face 14i of the fairing 14 so that its axial edge of free radial end 26a extends opposite and at a distance from the outer cylindrical face 20e of the annular skirt 20.
Les murets axiaux 26, la joue radiale 28 et la nervure radiale 24 coopèrent entre eux de manière à réduire la formation du flux "F" d'air parasite.The axial walls 26, the radial cheek 28 and the radial rib 24 cooperate with each other so as to reduce the formation of the flow "F" of stray air.
Conformément à l'invention, les murets axiaux 26, la joue radiale 28 et la nervure radiale 24 sont agencés axialement dansAccording to the invention, the axial walls 26, the radial flange 28 and the radial rib 24 are arranged axially in
Ie conduit annulaire 22 de manière que la joue radiale 28 est agencée en amont des murets axiaux, par rapport au sens d'écoulement du flux d'air principal G. De plus, la nervure radiale 24 est agencée axialement en amont par rapport aux murets axiaux 26 et par rapport à la joue radiale 28, c'est-à-dire que la joue radiale 28 est agencée axialement entre les murets axiaux 26 d'une part et la nervure radiale 24 d'autre part.The annular duct 22 so that the radial cheek 28 is arranged upstream of the axial walls, with respect to the direction of flow of the main air flow G. In addition, the radial rib 24 is arranged axially upstream with respect to the axial walls 26 and with respect to the radial cheek 28, that is to say that the radial cheek 28 is arranged axially between the axial walls 26 of a part and the radial rib 24 on the other hand.
Selon un mode de réalisation préféré de l'invention, la joue radiale 28 comporte une face radiale annulaire aval 28b (figure 3) qui est reliée au bord radial d'extrémité amont 26b de chaque muret axial 26. Ainsi, le conduit annulaire 22 est divisé par la joue radialeAccording to a preferred embodiment of the invention, the radial flange 28 comprises a downstream annular radial face 28b (FIG. 3) which is connected to the upstream end radial edge 26b of each axial wall 26. Thus, the annular duct 22 is divided by the radial cheek
28 en une portion aval 22a dans laquelle sont agencés les murets axiaux 26 et au niveau de laquelle le flux d'air "F" parasite pénètre dans le conduit annulaire 22, et une portion amont 22b dans laquelle la nervure radiale 24 et la joue radiale 28 sont agencées.28 in a downstream portion 22a in which are arranged the axial walls 26 and at which the parasitic air flow "F" enters the annular duct 22, and an upstream portion 22b in which the radial rib 24 and the radial cheek 28 are arranged.
La portion aval 22a du conduit annulaire 22 est divisée par les murets axiaux 26 en plusieurs canaux axiaux parallèles 30 qui sont répartis angulairement autour de l'axe principal A de rotation.The downstream portion 22a of the annular duct 22 is divided by the axial walls 26 into a plurality of parallel axial channels 30 which are distributed angularly about the main axis A of rotation.
Comme on peut le voir à la figure 3, les canaux axiaux 30 sont conformés de manière que lorsque le flux d'air "F" parasite pénètre dans la portion aval 22a, le flux d'air "F" parasite se divise en plusieurs flux secondaires 32.As can be seen in FIG. 3, the axial channels 30 are shaped so that when the parasitic "F" air flow enters the downstream portion 22a, the parasitic "F" air flow divides into several streams. secondary 32.
De plus, la composante tangentielle du flux d'air "F" parasite provoque un mouvement tourbillonnaire de chaque flux secondaire 32 autour de l'axe principal B du canal axial 30 associé.In addition, the tangential component of the parasitic "F" air flow causes a vortex movement of each secondary flow 32 around the main axis B of the associated axial channel 30.
En sortie du canal axial 30 associé au niveau de la joue radiale 28, chaque flux secondaire 32 se mélange aux autres flux secondaires 32 pour former de nouveau le flux d'air "F" parasite. Le mouvement tourbillonnaire de chaque flux secondaireAt the output of the associated axial channel 30 at the level of the radial cheek 28, each secondary stream 32 mixes with the other secondary streams 32 to form the parasitic "F" air flow again. The swirling motion of each secondary flow
32 dans le conduit axial 30 associé provoque une réduction importante, voire l'annulation de la composante tangentielle du flux d'air "F" parasite lorsqu'il se reforme au niveau de la joue radiale 28, tandis que la composante axiale du flux d'air "F" parasite reste globalement inchangée.32 in the associated axial duct 30 causes a significant reduction, or even the cancellation of the tangential component of the parasitic "F" air flow when it is reformed at the level of the cheek radial 28, while the axial component of the parasitic "F" air flow remains largely unchanged.
Le flux d'air "F" parasite ainsi reformé débouche de la portion aval 22a du conduit annulaire 22 et pénètre ensuite dans la portion amont 22b du conduit annulaire 22.The parasitized "F" air flow thus reformed opens out from the downstream portion 22a of the annular duct 22 and then enters the upstream portion 22b of the annular duct 22.
Comme on peut le voir à la figure 3, la joue radiale 28 et la nervure radiale 24 sont agencées dans la portion amont 22b du conduit annulaire 22 de manière qu'elles forment une chicane qui crée une perte de charge importante du flux d'air "F" parasite qui la traverse.As can be seen in FIG. 3, the radial cheek 28 and the radial rib 24 are arranged in the upstream portion 22b of the annular duct 22 so that they form a baffle which creates a significant pressure drop in the air flow. "F" parasite running through it.
La perte de charge subie par le flux d'air "F" parasite permet de limiter de manière importante le débit du flux d'air "F" parasite.The pressure drop experienced by the parasitic "F" air flow makes it possible to significantly limit the flow rate of the parasitic "F" air flow.
Par ailleurs, la perte de charge est formée au niveau de la portion amont 22b du conduit annulaire 22, elle ne provoque donc pas d'augmentation de la pression d'air dans le conduit annulaire 22, et par conséquent, la valeur du couple résistant n'est pas augmenté de manière importante malgré la présence de cette chicane. Comme on l'a dit plus haut la joue radiale 28 est conformée de manière que sa face radiale annulaire aval 28b est reliée au bord radial d'extrémité amont 26b de chaque muret axial 26. De plus, selon une variante de réalisation de l'invention, la joue radiale 28 s'étend radialement depuis la face cylindrique interne concave 14i du carénage 14 de manière que son bord annulaire d'extrémité radiale libre 28a affleure radialement par rapport au bord axial d'extrémité radiale libre 26a de chaque muret 26.Furthermore, the pressure drop is formed at the upstream portion 22b of the annular duct 22, it therefore does not cause an increase in the air pressure in the annular duct 22, and therefore the value of the resistant torque is not significantly increased despite the presence of this chicane. As mentioned above, the radial flange 28 is shaped so that its downstream annular radial face 28b is connected to the upstream end radial edge 26b of each axial wall 26. In addition, according to an embodiment variant of FIG. According to the invention, the radial flange 28 extends radially from the concave inner cylindrical face 14i of the fairing 14 so that its free radial end annular edge 28 is flush with the radially free end axial edge 26a of each wall 26.
Selon un autre aspect de l'invention, le bord d'extrémité aval 20a de la jupe annulaire 20 est situé axialement en amont du bord d'extrémité aval 26c de chaque muret axial 26 et en aval du bord radial d'extrémité amont 26b de chaque muret axial 26.According to another aspect of the invention, the downstream end edge 20a of the annular skirt 20 is situated axially upstream of the downstream end edge 26c of each axial wall 26 and downstream of the upstream end radial edge 26b of each axial wall 26.
Ainsi, une partie aval de chaque conduit axial 30 est débouchante radialement vers l'intérieur du système de ventilateur 10, ce qui permet de faciliter la pénétration de chaque flux secondaire 32 dans le conduit axial 30 associé, suivant une direction tangentielle par rapport à l'axe principal A de rotation, favorisant ainsi le mouvement tourbillonnaire de chaque flux secondaire 32 dans le conduit axial 30 associé.Thus, a downstream part of each axial duct 30 opens out radially towards the inside of the control system. fan 10, which facilitates the penetration of each secondary flow 32 in the associated axial duct 30, in a direction tangential to the main axis A of rotation, thereby promoting the vortex movement of each secondary flow 32 in the duct axial 30 associated.
Selon une variante de réalisation (non représentée) de cet aspect l'invention, chaque flux secondaire 32 pénètre axialement dans le conduit axial 30 associé. A cet effet, le bord d'extrémité aval 20a de la jupe annulaire 20 est situé axialement au droit du bord d'extrémité aval 26c de chaque muret axial 26, et selon encore une autre variante de réalisation de cet aspect de l'invention, le bord d'extrémité aval 20a de la jupe annulaire 20 est situé axialement en aval du bord d'extrémité aval 26c de chaque muret axial 26. Enfin, la nervure radiale 24 est positionnée axialement sur la jupe annulaire 20 de manière qu'elle s'étend radialement depuis le bord d'extrémité amont 20c de la jupe annulaire 20.According to an alternative embodiment (not shown) of this aspect of the invention, each secondary stream 32 penetrates axially into the associated axial duct 30. For this purpose, the downstream end edge 20a of the annular skirt 20 is situated axially in line with the downstream end edge 26c of each axial wall 26, and according to yet another variant embodiment of this aspect of the invention, the downstream end edge 20a of the annular skirt 20 is located axially downstream of the downstream end edge 26c of each axial wall 26. Finally, the radial rib 24 is positioned axially on the annular skirt 20 so that it extends radially from the upstream end edge 20c of the annular skirt 20.
Cependant, il sera compris que l'invention n'est pas limitée à ce mode de réalisation de la jupe annulaire 20 et de la nervure radiale 24, et qui la nervure radiale 24 peut être située axialement en aval du bord d'extrémité amont 20c de la jupe annulaire 20. However, it will be understood that the invention is not limited to this embodiment of the annular skirt 20 and the radial rib 24, and that the radial rib 24 can be located axially downstream of the upstream end edge 20c of the annular skirt 20.

Claims

REVENDICATIONS
1. Système de ventilateur (10), notamment pour le refroidissement du moteur d'un véhicule automobile, comportant un ventilateur (12) monté à rotation autour d'un axe principal (A) de rotation par rapport à un carénage (14) périphérique au ventilateur (12) qui est fixé au moteur du véhicule, de manière à produire un flux d'air (G) globalement coaxial à l'axe principal (A) de rotation du ventilateur (12), dans lequel le ventilateur (12) comporte : - un noyau central (16) de montage sur un arbre d'entraînement en rotation du ventilateur (12) ;A fan system (10), in particular for cooling the motor of a motor vehicle, comprising a fan (12) rotatably mounted about a main axis (A) of rotation with respect to a peripheral fairing (14). to the fan (12) which is attached to the engine of the vehicle, so as to produce a flow of air (G) generally coaxial with the main axis (A) of rotation of the fan (12), wherein the fan (12) comprises: - a central core (16) for mounting on a rotary drive shaft of the fan (12);
- des pales (18) réparties angulairement autour de l'axe principal (A) de rotation, et dont chacune s'étend globalement radialement vers l'extérieur du ventilateur (12) depuis Ie noyau centra! (16) ;- Blades (18) angularly distributed around the main axis (A) of rotation, and each of which extends generally radially outwardly of the fan (12) from the central core! (16);
- une jupe annulaire (20) périphérique coaxiale à l'axe principal (A) de rotation, dont une face cylindrique interne concave (2Oi) est fixée à l'extrémité radiale externe (18a) de chaque pale (18) ; - et une nervure radiale annulaire externe (24) qui s'étend radialement vers l'extérieur du ventilateur (12), depuis la face cylindrique externe (20e) convexe de la jupe annulaire (20), et dans lequel le carénage (14) comporte :- A peripheral annular skirt (20) coaxial with the main axis (A) of rotation, a concave inner cylindrical face (20i) is fixed to the outer radial end (18a) of each blade (18); - and an outer annular radial rib (24) extending radially outwardly of the fan (12), from the outer cylindrical (20e) convex face of the annular skirt (20), and wherein the shroud (14) has:
- une face cylindrique interne concave (14i) qui s'étend radialement à distance et en vis-à-vis de la face cylindrique externe convexe (20e) de la jupe annulaire (20) ;- A concave inner cylindrical face (14i) which extends radially at a distance and vis-à-vis the convex outer cylindrical face (20e) of the annular skirt (20);
- une série de murets généralement axiaux (26) qui sont répartis angulairement autour de l'axe principal (A) de rotation, chaque muret axial (26) s'étendant dans un plan généralement axial, et s'étendant radialement depuis la face cylindrique interne concave (14i) du carénage (14), de manière que son bord axial d'extrémité radiale libre (26a) est situé à distance de la face cylindrique externe convexe (20e) de la jupe annulaire (20) ; - et une joue radiale annulaire interne (28) qui s'étend radialement vers l'intérieur du carénage (14) depuis la face cylindrique interne concave (14i) du carénage (14), caractérisé en ce que la joue radiale (28) est agencée axialement en amont des murets axiaux (26), par rapport au sens d'écoulement du flux d'air (G).- a series of generally axial walls (26) which are angularly distributed around the main axis (A) of rotation, each axial wall (26) extending in a generally axial plane, and extending radially from the cylindrical face concave internal member (14i) of the fairing (14), so that its free radial end axial edge (26a) is located at a distance from the convex outer cylindrical face (20e) of the annular skirt (20); - and an inner annular radial cheek (28) extending radially inwardly of the fairing (14) from the concave inner cylindrical face (14i) of the fairing (14), characterized in that the radial cheek (28) is arranged axially upstream of the axial walls (26), with respect to the direction of flow of the air flow (G).
2. Système de ventilateur (10) selon la revendication précédente, caractérisé en ce que la joue radiale (28) comporte une face radiale annulaire aval (28b) par rapport au sens d'écoulement du flux d'air (G) qui est reliée au bord radial d'extrémité amont (26b) de chaque muret axial (26).2. Fan system (10) according to the preceding claim, characterized in that the radial flange (28) comprises a downstream annular radial face (28b) relative to the direction of flow of the air flow (G) which is connected at the upstream end radial edge (26b) of each axial wall (26).
3. Système de ventilateur (10) selon la revendication précédente, caractérisé en ce que le bord annulaire d'extrémité radiale libre (28a) de la joue radiale (28) affleure radialement avec Ie bord axial d'extrémité radiale libre (26a) de chaque muret axial (26).3. Fan system (10) according to the preceding claim, characterized in that the free radial end annular edge (28a) of the radial flange (28) is flush with the radial end radially free end edge (26a) of each axial wall (26).
4. Système de ventilateur (10) selon l'une quelconque des revendications précédentes, caractérisé en ce que la joue radiale (28) est agencée en aval et à distance de la nervure radiale (24), par rapport au sens d'écoulement du flux d'air (G).4. Fan system (10) according to any one of the preceding claims, characterized in that the radial cheek (28) is arranged downstream and at a distance from the radial rib (24), with respect to the direction of flow of the air flow (G).
5. Système de ventilateur (10) selon l'une quelconque des revendications précédentes, caractérisé en ce que le bord annulaire d'extrémité radiale libre (28a) de la joue radiale (28) s'étend radialement en vis-à-vis et à distance de la face cylindrique externe convexe (20e) de la jupe annulaire (20).5. Fan system (10) according to any one of the preceding claims, characterized in that the annular free radial end edge (28a) of the radial flange (28) extends radially vis-a-vis and away from the convex outer cylindrical face (20e) of the annular skirt (20).
6. Système de ventilateur (10) selon l'une quelconque des revendications précédentes, caractérisé en ce que le bord d'extrémité aval (20a) de la jupe annulaire (20) est situé en amont du bord d'extrémité aval (26c) de chaque muret axial (26), par rapport au sens d'écoulement du flux d'air (G).6. Fan system (10) according to any one of the preceding claims, characterized in that the downstream end edge (20a) of the annular skirt (20) is located upstream the downstream end edge (26c) of each axial wall (26), relative to the direction of flow of the air flow (G).
7. Système de ventilateur (10) selon l'une quelconque des revendications 1 à 5, caractérisé en ce que le bord d'extrémité aval (20a) de la jupe annulaire (20) est situé axialement au droit du bord d'extrémité aval (26c) de chaque muret axial (26).7. Fan system (10) according to any one of claims 1 to 5, characterized in that the downstream end edge (20a) of the annular skirt (20) is located axially to the right of the downstream end edge (26c) of each axial wall (26).
8. Système de ventilateur (10) selon l'une quelconque des revendications précédentes, caractérisé en ce que le bord d'extrémité aval (20a) de la jupe annulaire est situé en aval du bord d'extrémité amont de (26b) chaque muret axial (26), par rapport au sens d'écoulement du flux d'air (G). 8. Fan system (10) according to any one of the preceding claims, characterized in that the downstream end edge (20a) of the annular skirt is located downstream of the upstream end edge of (26b) each wall axial (26), with respect to the flow direction of the air flow (G).
PCT/EP2005/013475 2004-12-15 2005-12-15 Ventilating system comprising means for limiting backflow WO2006063825A1 (en)

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FR04/13297 2004-12-15
FR0413297A FR2879266B1 (en) 2004-12-15 2004-12-15 FAN SYSTEM COMPRISING MEANS FOR LIMITING PARASITE AIR FLOW

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FR2879266A1 (en) 2006-06-16

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