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EP1034376A1 - Fan blade - Google Patents

Fan blade

Info

Publication number
EP1034376A1
EP1034376A1 EP99934796A EP99934796A EP1034376A1 EP 1034376 A1 EP1034376 A1 EP 1034376A1 EP 99934796 A EP99934796 A EP 99934796A EP 99934796 A EP99934796 A EP 99934796A EP 1034376 A1 EP1034376 A1 EP 1034376A1
Authority
EP
European Patent Office
Prior art keywords
propeller
hub
blades
blade
propeller according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP99934796A
Other languages
German (de)
French (fr)
Other versions
EP1034376B1 (en
Inventor
Stéphane MOREAU
Bruno Dessale
Eric Coggiola
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.)
Valeo Thermique Moteur SA
Original Assignee
Valeo Thermique Moteur 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
Family has litigation
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Application filed by Valeo Thermique Moteur SA filed Critical Valeo Thermique Moteur SA
Publication of EP1034376A1 publication Critical patent/EP1034376A1/en
Application granted granted Critical
Publication of EP1034376B1 publication Critical patent/EP1034376B1/en
Anticipated expiration legal-status Critical
Revoked legal-status Critical Current

Links

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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/02—Formulas of curves

Definitions

  • the invention relates to a fan propeller comprising a hub and blades extending radially outward from the hub, the hub being adapted to be fixed on the shaft of an engine so as to allow the engine to transmit at least 150 watts of power to the propeller.
  • Such propellers are used in particular for cooling the drive motor of motor vehicles, the propeller producing a flow of air through a cooling radiator.
  • the space available in the engine compartment of vehicles is generally very limited, it is desirable to have cooling propellers of reduced size, especially in the axial direction.
  • the invention relates in particular to a propeller of the kind defined in the introduction, and provides that its axial length L, measured in meters, is not notably greater than the value L 0 given by the following formula (I):
  • L is not appreciably less than L 0 , because below this performance decreases.
  • the range of variation of L with respect to L 0 is 20%.
  • the blades are substantially identical to each other and uniformly spaced in the circumferential direction at an angular pitch ⁇ , the point located halfway between the leading and trailing edges at the radially outer end being offset from the point corresponding to the foot of the blade, in the direction opposite to the direction of rotation of the propeller, by an angle of between half and three-quarters approximately of said angular pitch. This concerns the case of so-called symmetrical propellers.
  • each blade is curved in the direction of rotation of the propeller, the point located midway between them progressively moving back towards the rear of the axial plane containing its position at foot of the blade, then gradually returning to this plane, over a fraction of the radial extent of the blade between 20% and 70%, and progressively deviating from this same plane forward on the remaining fraction.
  • the acute angle ⁇ between the chord of the flattened cross section of a blade and a radial plane decreases progressively at least over the last 30% of the radial extent of the blade.
  • the hub comprises a substantially cylindrical wall from which the blades extend, and a bottom wall disposed substantially in a radial plane, facing upstream of the air flow produced by the propeller, the cylindrical wall drique and the bottom wall being connected to each other by a convex rounding with a radius of curvature between 4 and 8 mm.
  • the rounding has a substantially quarter-circle profile with a radius of 5 mm.
  • the blades extend over the entire axial length of the cylindrical wall of the hub.
  • the hub is hollow and internally has ribs.
  • FIG. 1 is an axial rear view of a fan propeller according to the invention
  • FIG. 1 is a side view in axial half-section of the propeller
  • FIG. 3 is an enlarged part of Figure 1;
  • - Figure 4 is a top view of the propeller hub, further showing the shape of the flattened cross section of a blade;
  • FIGS. 5 and 6 are graphs illustrating the axial length as a function of the diameter for known fan propellers and for fan propellers according to the invention.
  • Figure 7 shows on a larger scale than Figure 4 the flattened cross section of the blade in the vicinity of the leading edge thereof.
  • the propeller illustrated in Figures 1 to 4 comprises, conventionally, a multiplicity of blades 1 extending generally radially from a central hub 2 and connected together, at the periphery of the propeller, by a ferrule 3.
  • the hub, the blades and the ferrule are formed in one piece by molding.
  • the hub 2 has a cylindrical annular wall of revolution 4, to which the feet of the blades 1 are connected, and a flat front wall 5, facing upstream, the terms upstream and downstream referring here to the direction of the air flow produced by the rotation of the propeller.
  • the walls 4 and 5 are interconnected by a rounded 6 with an arcuate profile of radius 5 mm.
  • the wall 5 is connected to a central sleeve 7 molded onto a metallic annular insert 8 intended for the connection of the propeller to the shaft of a drive motor not shown.
  • Reinforcement ribs 9 are provided inside the hub 2.
  • the ferrule 3 also has a cylindrical annular wall of revolution 10, to which the ends of the blades are connected, and which continues, on the upstream side, by a rounded flaring 11.
  • the wall 5 of the hub which, in FIG. 1 , represents the axial end thereof on the upstream side, is arranged projecting by relative to the corresponding end of the ferrule 3.
  • the position of the leading edge of the blades it gradually moves downstream from the base of the blades, where it is located at the upstream end of the cylindrical wall 4, that is to say 5 mm downstream from the upstream face of the wall 5, to the vicinity of the upstream end of the cylindrical wall 10.
  • the point M s located halfway between the leading edge 21 and the trailing edge 20 of a blade 1, at the radially outer end of it. ci, is offset by an angle ⁇ , in the direction of rotation of the propeller, indicated by the arrow FI, relative to the point M located halfway between the leading and trailing edges at the foot of the blade.
  • the angle ⁇ is advantageously between about half and three-quarters of the angular pitch ⁇ of the blades.
  • the leading edge 21 and the trailing edge 20 of each blade are curved in the direction of rotation FI, as well as the center line 23 along which moves, from foot at the end of the blade, point M located midway between the leading and trailing edges, line 23 having the points M ⁇ and M s mentioned above as ends.
  • the line 23 progressively moves back towards the rear of the axial plane P containing the latter, then gradually returns to cut the plane P at a point M. j _. It then gradually deviates from this same plane forward, up to point M s .
  • the distance between the points M ⁇ and 1 ⁇ represents between 20 and 70% of the radial extent of the blades, that is to say the distance between the cylindrical walls 4 and 10.
  • FIG. 4 shows the flat cross section of a blade, that is to say the planar closed curve obtained by cutting the blade by a cylindrical surface of revolution around the axis A of the propeller, and unwinding at flat this cylindrical surface.
  • This flat cross section has an airplane wing profile, the cord 25 of which is inclined by a acute angle ⁇ relative to a radial plane such as plane 19 containing the downstream end of the propeller.
  • the invention provides that the angle ⁇ , or pitch angle, decreases progressively over the last 30% of the radial extent of the blade, that is to say from the cylindrical surface 27 indicated in FIG. 3 until at the wall 10, the distance between the surface 27 and the wall 10 representing 30% of the distance between the walls 4 and 10.
  • the point 28 of the flattened cross section furthest from the cord 25 is substantially equidistant from the ends of the latter, while the distance h between the point 28 and the cord 25 is at least equal to 3%. of the length 1 thereof, and in particular equal to 10% of this length.
  • FIG. 7 shows on a larger scale the region of the flattened cross section of the blade close to the leading edge.
  • the profile of the blade comprises in this region an elliptical arc 29, the ratio of the axes of the ellipse being greater than 1.5.
  • each of the points marked by a cross, a triangle, a square or a circle has as coordinates the diameter and the axial length, in millimeters, of the propeller of a cooling fan existing on the market.
  • the table below gives the axial length and the maximum efficiency for fan propellers having the usual diameters for the cooling of motor vehicle engines, namely 280, 320, 350, 380 and 450 mm.
  • the maximum efficiency is the maximum efficiency obtained by varying the speed of rotation of the fan.
  • the table concerns, for each diameter, five propellers designated by the references 1 to 5, the first four being commercially available propellers and the fifth being a propeller according to the invention. Some of the propellers referenced 1 to 4 correspond to points marked in FIG. 5.
  • the propellers referenced 5 have been defined by the calculation method known under the name “Computational Fluid Dynamics” (CFD), described by Éric Coggiola et al. in AIAA article 98-0772 "On the use of CFD in the automotive engine cooling fan System design” presented at Aerospace Sciences Meeting and Exhibit, in Reno, United States of America, from January 12 to 15, 1998.
  • CFD Computer Fluid Dynamics

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

Abstract

The invention concerns a blade having an axial length L, expressed in metre, equal, by approximately 20 %, to the value of L0 given by the following formula (I): L0 = 0.426262 - 5.14288.D + 23.1798.D<2> - 44.2505.D<3> + 30.8841.D<4>, D being the blade diameter expressed in metre. The invention enables to substantially reduce the blade axial space requirement, for a given diameter and for obtaining the desired performance. The invention is useful for cooling a motor vehicle engine.

Description

Hélice de ventilateurFan propeller
L'invention concerne une hélice de ventilateur comprenant un moyeu et des pales s 'étendant radiale ent vers l'extérieur à partir du moyeu, le moyeu étant propre à être fixé sur l'arbre d'un moteur de manière à permettre au moteur de transmettre à l'hélice une puissance d'au moins 150 watts.The invention relates to a fan propeller comprising a hub and blades extending radially outward from the hub, the hub being adapted to be fixed on the shaft of an engine so as to allow the engine to transmit at least 150 watts of power to the propeller.
De telles hélices sont utilisées notamment pour le refroidissement du moteur d'entraînement de véhicules automobiles, l'hélice produisant un flux d'air à travers un radiateur de refroidissement .Such propellers are used in particular for cooling the drive motor of motor vehicles, the propeller producing a flow of air through a cooling radiator.
Il était admis jusqu'ici que les performances aérauliques et acoustiques de telles hélices sont d'autant meilleures que leur diamètre et leur longueur axiale sont plus importants.It was accepted until now that the aeraulic and acoustic performances of such propellers are all the better the greater their diameter and their axial length.
La place disponible dans le compartiment moteur des véhicules étant généralement très limitée, il est souhaitable de disposer d'hélices de refroidissement d'encombrement réduit, notamment dans la direction axiale.The space available in the engine compartment of vehicles is generally very limited, it is desirable to have cooling propellers of reduced size, especially in the axial direction.
De manière surprenante, on a découvert que, pour un diamètre donné, les performances aérauliques et. acoustiques ne se détériorent pratiquement qu' en-deçà d'une certaine longueur axiale optimale.Surprisingly, it has been discovered that, for a given diameter, the air performance and. acoustics practically deteriorate only below a certain optimal axial length.
L'invention vise notamment une hélice du genre défini en introduction, et prévoit que sa longueur axiale L, mesurée en mètre, n'est pas notablement supérieure à la valeur L0 donnée par la formule (I) suivante:The invention relates in particular to a propeller of the kind defined in the introduction, and provides that its axial length L, measured in meters, is not notably greater than the value L 0 given by the following formula (I):
L0 = 0,426262 -5, 14288. D + 23, 1798. D2- 44, 2505. D3 + 30, 8841. D4,L 0 = 0.426262 -5, 14288. D + 23, 1798. D 2 - 44, 2505. D 3 + 30, 8841. D 4 ,
D étant le diamètre de l'hélice mesuré en mètre. Au moins pour certaines configurations géométriques des pales, il est préférable que L ne soit pas notablement inférieure à L0, car en-deçà les performances diminuent.D being the diameter of the propeller measured in meters. At least for certain geometrical configurations of the blades, it is preferable that L is not appreciably less than L 0 , because below this performance decreases.
De préférence, le domaine de variation de L par rapport à L0, vers le haut et le cas échéant vers le bas, est de 20 %.Preferably, the range of variation of L with respect to L 0 , upwards and if necessary downwards, is 20%.
Les relations ci-dessus valent tout particulièrement lorsque la configuration géométrique de l'hélice présente certaines au moins des particularités suivantes:The above relationships are particularly valid when the geometric configuration of the propeller has at least some of the following characteristics:
- Les extrémités axiales des pales et du moyeu tournées vers l'aval du flux d'air produit par l'hélice sont sensiblement contenues dans un même plan radial.- The axial ends of the blades and of the hub facing downstream of the air flow produced by the propeller are substantially contained in the same radial plane.
- Le bord de fuite des pales est entièrement contenu dans ledit plan radial.- The trailing edge of the blades is entirely contained in said radial plane.
- Les extrémités axiales des pales et du moyeu tournées vers l'amont du flux d'air produit par l'hélice sont sensiblement contenues dans un même plan radial.- The axial ends of the blades and of the hub turned upstream of the air flow produced by the propeller are substantially contained in the same radial plane.
- Les extrémités radialement extérieures des pales sont reliées entre elles par une virole.- The radially outer ends of the blades are connected together by a ferrule.
- Les pales sont sensiblement identiques entre elles et uniformément espacées dans la direction circonférentielle selon un pas angulaire β , le point situé à mi-distance des bords d'attaque et de fuite à l'extrémité radialement extérieure étant décalé par rapport au point correspondant au pied de la pale, dans le sens opposé au sens de rotation de l'hélice, d'un angle compris entre la moitié et les trois quarts environ dudit pas angulaire. Ceci concerne le cas des hélices dites symétriques.- The blades are substantially identical to each other and uniformly spaced in the circumferential direction at an angular pitch β, the point located halfway between the leading and trailing edges at the radially outer end being offset from the point corresponding to the foot of the blade, in the direction opposite to the direction of rotation of the propeller, by an angle of between half and three-quarters approximately of said angular pitch. This concerns the case of so-called symmetrical propellers.
- Les bords d'attaque et de fuite de chaque pale sont bombés dans le sens de rotation de l'hélice, le point situé à mi- distance de ceux-ci s 'écartant progressivement vers l'arrière du plan axial contenant sa position au pied de la pale, puis revenant progressivement jusque dans ce plan, sur une fraction de l'étendue radiale de la pale comprise entre 20 % et 70 %, et s 'écartant progressivement de ce même plan vers l'avant sur la fraction restante.- The leading and trailing edges of each blade are curved in the direction of rotation of the propeller, the point located midway between them progressively moving back towards the rear of the axial plane containing its position at foot of the blade, then gradually returning to this plane, over a fraction of the radial extent of the blade between 20% and 70%, and progressively deviating from this same plane forward on the remaining fraction.
- L'angle aigu Ω entre la corde de la section transversale aplatie d'une pale et un plan radial décroît progressivement au moins sur les derniers 30 % de l'étendue radiale de la pale.- The acute angle Ω between the chord of the flattened cross section of a blade and a radial plane decreases progressively at least over the last 30% of the radial extent of the blade.
- Le moyeu comprend une paroi sensiblement cylindrique à partir de laquelle s'étendent les pales, et une paroi de fond disposée sensiblement selon un plan radial, tournée vers l'amont du flux d'air produit par l'hélice, la paroi cylin- drique et la paroi de fond étant raccordées entre elles par un arrondi convexe d'un rayon de courbure compris entre 4 et 8 mm.- The hub comprises a substantially cylindrical wall from which the blades extend, and a bottom wall disposed substantially in a radial plane, facing upstream of the air flow produced by the propeller, the cylindrical wall drique and the bottom wall being connected to each other by a convex rounding with a radius of curvature between 4 and 8 mm.
- L'arrondi a sensiblement un profil en quart de cercle de rayon 5 mm.- The rounding has a substantially quarter-circle profile with a radius of 5 mm.
- Les pales s'étendent sur toute la longueur axiale de la paroi cylindrique du moyeu.- The blades extend over the entire axial length of the cylindrical wall of the hub.
- Le moyeu est creux et présente intérieurement des nervures.- The hub is hollow and internally has ribs.
Les caractéristiques et avantages de l'invention seront exposés plus en détail dans la description ci-après, en se référant aux dessins annexés, sur lesquels:The characteristics and advantages of the invention will be explained in more detail in the description below, with reference to the accompanying drawings, in which:
- la figure 1 est une vue axiale d'arrière d'une hélice de ventilateur selon l'invention;- Figure 1 is an axial rear view of a fan propeller according to the invention;
- la figure 2 est une vue de côté en demi-coupe axiale de l'hélice;- Figure 2 is a side view in axial half-section of the propeller;
- la figure 3 est une partie agrandie de la figure 1; - la figure 4 est une vue de dessus du moyeu de l'hélice, montrant en outre la forme de la section transversale aplatie d'une pale;- Figure 3 is an enlarged part of Figure 1; - Figure 4 is a top view of the propeller hub, further showing the shape of the flattened cross section of a blade;
- les figures 5 et 6 sont des graphiques illustrant la longueur axiale en fonction du diamètre pour des hélices de ventilateur connues et pour des hélices de ventilateur selon l'invention; et- Figures 5 and 6 are graphs illustrating the axial length as a function of the diameter for known fan propellers and for fan propellers according to the invention; and
- la figure 7 montre à plus grande échelle que la figure 4 la section transversale aplatie de la pale au voisinage du bord d'attaque de celle-ci.- Figure 7 shows on a larger scale than Figure 4 the flattened cross section of the blade in the vicinity of the leading edge thereof.
L'hélice illustrée sur les figures 1 à 4 comprend, de façon classique, une multiplicité de pales 1 s 'étendant généralement radialement à partir d'un moyeu central 2 et reliées entre elles, à la périphérie de l'hélice, par une virole 3. Le moyeu, les pales et la virole sont formés d'une seule pièce par moulage. Le moyeu 2 présente une paroi annulaire cylindrique de révolution 4, à laquelle se raccordent les pieds des pales 1, et une paroi frontale plane 5, tournée vers l'amont, les termes amont et aval se référant ici au sens du flux d'air produit par la rotation de l'hélice. Les parois 4 et 5 sont reliées entre elles par un arrondi 6 à profil en arc de cercle de rayon 5 mm. En direction de l'axe A de l'hélice, la paroi 5 se raccorde à un manchon central 7 surmoulé sur un insert annulaire métallique 8 destiné à la liaison de l'hélice à l'arbre d'un moteur d'entraînement non représenté. Des nervures de renforcement 9 sont prévues à l'intérieur du moyeu 2. La virole 3 présente également une paroi annulaire cylindrique de révolution 10, à laquelle se raccordent les extrémités des pales, et qui se continue, du côté amont, par un évasement arrondi 11.The propeller illustrated in Figures 1 to 4 comprises, conventionally, a multiplicity of blades 1 extending generally radially from a central hub 2 and connected together, at the periphery of the propeller, by a ferrule 3. The hub, the blades and the ferrule are formed in one piece by molding. The hub 2 has a cylindrical annular wall of revolution 4, to which the feet of the blades 1 are connected, and a flat front wall 5, facing upstream, the terms upstream and downstream referring here to the direction of the air flow produced by the rotation of the propeller. The walls 4 and 5 are interconnected by a rounded 6 with an arcuate profile of radius 5 mm. In the direction of the axis A of the propeller, the wall 5 is connected to a central sleeve 7 molded onto a metallic annular insert 8 intended for the connection of the propeller to the shaft of a drive motor not shown. . Reinforcement ribs 9 are provided inside the hub 2. The ferrule 3 also has a cylindrical annular wall of revolution 10, to which the ends of the blades are connected, and which continues, on the upstream side, by a rounded flaring 11.
Les extrémités axiales du moyeu et de la virole tournée vers l'aval du flux d'air et le bord de fuite des pales sont contenues dans un même plan radial 19. En revanche, la paroi 5 du moyeu, qui, sur la figure 1, représente l'extrémité axiale de celui-ci du côté amont, est disposée en saillie par rapport à l'extrémité correspondante de la virole 3. Quant à la position du bord d'attaque des pales, il se déplace progressivement vers l'aval depuis le pied des pales, où il est situé à l'extrémité amont de la paroi cylindrique 4, c'est-à-dire à 5 mm en aval de la face amont de la paroi 5, jusqu'au voisinage de l'extrémité amont de la paroi cylindrique 10.The axial ends of the hub and of the ferrule facing downstream of the air flow and the trailing edge of the blades are contained in the same radial plane 19. On the other hand, the wall 5 of the hub, which, in FIG. 1 , represents the axial end thereof on the upstream side, is arranged projecting by relative to the corresponding end of the ferrule 3. As for the position of the leading edge of the blades, it gradually moves downstream from the base of the blades, where it is located at the upstream end of the cylindrical wall 4, that is to say 5 mm downstream from the upstream face of the wall 5, to the vicinity of the upstream end of the cylindrical wall 10.
Selon l'invention, comme on le voit sur la figure 1, le point Ms situé à mi-distance du bord d'attaque 21 et du bord de fuite 20 d'une pale 1, à l'extrémité radialement extérieure de celle-ci, est décalé d'un angle α, dans le sens de rotation de l'hélice, indiqué par la flèche FI, par rapport au point M situé à mi-distance des bords d'attaque et de fuite au pied de la pale. L'angle α est avantageusement compris entre la moitié et les trois-quart environ du pas angulaire β des pales.According to the invention, as can be seen in FIG. 1, the point M s located halfway between the leading edge 21 and the trailing edge 20 of a blade 1, at the radially outer end of it. ci, is offset by an angle α, in the direction of rotation of the propeller, indicated by the arrow FI, relative to the point M located halfway between the leading and trailing edges at the foot of the blade. The angle α is advantageously between about half and three-quarters of the angular pitch β of the blades.
On voit également sur les figures 1 et 3 que le bord d'atta- que 21 et le bord de fuite 20 de chaque pale sont bombés dans le sens de rotation FI, ainsi que la ligne médiane 23 le long de laquelle se déplace, du pied à l'extrémité de la pale, le point M situé à mi-distance des bords d'attaque et de fuite, la ligne 23 ayant pour extrémités les points M^ et Ms préci- tés. A partir de MD, la ligne 23 s'écarte progressivement vers l'arrière du plan axial P contenant celui-ci, puis revient progressivement pour couper le plan P en un point M.j_. Elle s'écarte ensuite progressivement de ce même plan vers l'avant, jusqu'au point Ms. La distance entre les points M^ et 1^ représente entre 20 et 70 % de l'étendue radiale des pales, c'est-à-dire de la distance entre les parois cylindriques 4 et 10.It can also be seen in FIGS. 1 and 3 that the leading edge 21 and the trailing edge 20 of each blade are curved in the direction of rotation FI, as well as the center line 23 along which moves, from foot at the end of the blade, point M located midway between the leading and trailing edges, line 23 having the points M ^ and M s mentioned above as ends. From M D , the line 23 progressively moves back towards the rear of the axial plane P containing the latter, then gradually returns to cut the plane P at a point M. j _. It then gradually deviates from this same plane forward, up to point M s . The distance between the points M ^ and 1 ^ represents between 20 and 70% of the radial extent of the blades, that is to say the distance between the cylindrical walls 4 and 10.
La figure 4 montre la section transversale aplatie d'une pale, c'est-à-dire la courbe fermée plane obtenue en coupant la pale par une surface cylindrique de révolution autour de l'axe A de l'hélice, et en déroulant à plat cette surface cylindrique. Cette section transversale aplatie présente un profil en aile d'avion, dont la corde 25 est inclinée d'un angle aigu Ω par rapport à un plan radial tel que le plan 19 contenant l'extrémité aval de l'hélice. L'invention prévoit que l'angle Ω, ou angle de calage, décroît progressivement sur les derniers 30 % de l'étendue radiale de la pale, c'est- à-dire depuis la surface cylindrique 27 indiquée sur la figure 3 jusqu'à la paroi 10, la distance entre la surface 27 et la paroi 10 représentant 30 % de la distance entre les parois 4 et 10.FIG. 4 shows the flat cross section of a blade, that is to say the planar closed curve obtained by cutting the blade by a cylindrical surface of revolution around the axis A of the propeller, and unwinding at flat this cylindrical surface. This flat cross section has an airplane wing profile, the cord 25 of which is inclined by a acute angle Ω relative to a radial plane such as plane 19 containing the downstream end of the propeller. The invention provides that the angle Ω, or pitch angle, decreases progressively over the last 30% of the radial extent of the blade, that is to say from the cylindrical surface 27 indicated in FIG. 3 until at the wall 10, the distance between the surface 27 and the wall 10 representing 30% of the distance between the walls 4 and 10.
Avantageusement, le point 28 de la section transversale aplatie le plus éloigné de la corde 25 se trouve sensiblement à égale distance des extrémités de celle-ci, tandis que la distance h entre le point 28 et la corde 25 est au moins égale à 3 % de la longueur 1 de celle-ci, et en particulier égale à 10 % de cette longueur.Advantageously, the point 28 of the flattened cross section furthest from the cord 25 is substantially equidistant from the ends of the latter, while the distance h between the point 28 and the cord 25 is at least equal to 3%. of the length 1 thereof, and in particular equal to 10% of this length.
La figure 7 montre à plus grande échelle la région de la section transversale aplatie de la pale voisine du bord d'attaque. Selon l'invention, le profil de la pale comporte dans cette région un arc d'ellipse 29, le rapport des axes de l'ellipse étant supérieur à 1,5.FIG. 7 shows on a larger scale the region of the flattened cross section of the blade close to the leading edge. According to the invention, the profile of the blade comprises in this region an elliptical arc 29, the ratio of the axes of the ellipse being greater than 1.5.
Sur le graphique de la figure 5, chacun des points marqués par une croix, un triangle, un carré ou un cercle a pour coordonnées le diamètre et la longueur axiale, en millimètres, de l'hélice d'un ventilateur de refroidissement existant sur le marché.In the graph in FIG. 5, each of the points marked by a cross, a triangle, a square or a circle has as coordinates the diameter and the axial length, in millimeters, of the propeller of a cooling fan existing on the market.
Le tableau ci-après donne la longueur axiale et le rendement maximal pour des hélices de ventilateur ayant des diamètres usuels pour le refroidissement des moteurs de véhicules automobiles, à savoir 280, 320, 350, 380 et 450 mm. Le rendement maximal est la valeur maximale du rendement obtenue en faisant varier la vitesse de rotation du ventilateur. Le tableau concerne, pour chaque diamètre, cinq hélices désignées par les références 1 à 5, les quatre premières étant des hélices disponibles dans le commerce et la cinquième étant une hélice selon l'invention. Certaines des hélices référencées 1 à 4 correspondent à des points marqués sur la figure 5.The table below gives the axial length and the maximum efficiency for fan propellers having the usual diameters for the cooling of motor vehicle engines, namely 280, 320, 350, 380 and 450 mm. The maximum efficiency is the maximum efficiency obtained by varying the speed of rotation of the fan. The table concerns, for each diameter, five propellers designated by the references 1 to 5, the first four being commercially available propellers and the fifth being a propeller according to the invention. Some of the propellers referenced 1 to 4 correspond to points marked in FIG. 5.
Les hélices référencées 5 ont été définies par la méthode de calcul connue sous la dénomination "Computational Fluid Dynamics" (CFD), décrite par Éric Coggiola et al. dans l'article AIAA 98-0772 "On the use of CFD in the automotive engine cooling fan System design" présenté à Aerospace Sciences Meeting and Exhibit, à Reno, États-Unis d'Amérique, du 12 au 15 janvier 1998.The propellers referenced 5 have been defined by the calculation method known under the name "Computational Fluid Dynamics" (CFD), described by Éric Coggiola et al. in AIAA article 98-0772 "On the use of CFD in the automotive engine cooling fan System design" presented at Aerospace Sciences Meeting and Exhibit, in Reno, United States of America, from January 12 to 15, 1998.
Sur la figure 5, les points correspondant aux hélices référencées 5 sont indiqués par des étoiles à huit branches.In FIG. 5, the points corresponding to the propellers referenced 5 are indicated by eight-pointed stars.
La formule (I) n'est autre que l'équation de la courbe Cl qui passe sensiblement par ces points. Dans le domaine considéré, c'est-à-dire pour des diamètres compris entre 0,2 et 0,5 m environ, cette équation peut-être en pratique remplacée par l'équation linéaire approchée (II):The formula (I) is none other than the equation of the curve Cl which passes substantially through these points. In the field under consideration, that is to say for diameters of between 0.2 and 0.5 m approximately, this equation may in practice be replaced by the approximate linear equation (II):
L0 = - 0,00584 + 0,105. DL 0 = - 0.00584 + 0.105. D
L0 et D étant mesurés en mètre. La droite représentative de cette équation est représentée en C2 sur la figure 5. Les courbes Cl et C2 sont reproduites sur la figure 6, avec une plus grande échelle pour les ordonnées.L 0 and D being measured in meters. The line representative of this equation is represented in C2 in FIG. 5. The curves C1 and C2 are reproduced in FIG. 6, with a larger scale for the ordinates.
On voit sur la figure 5 que, pour un diamètre donné, la longueur axiale des hélices existantes est plus élevée, parfois très sensiblement, que la valeur L0 donnée par la formule I. On voit par ailleurs sur le tableau que le rendement maximal de l'hélice selon l'invention, pour un diamètre donné, est supérieur, ou à peu près égal, au rendement maximal des hélices connues, une légère supériorité de ces dernières n'étant obtenue, dans des cas limités, qu'au prix d'un encombrement axial sensiblement supérieur. It can be seen in FIG. 5 that, for a given diameter, the axial length of the existing propellers is greater, sometimes very significantly, than the value L 0 given by the formula I. It is also seen on the table that the maximum efficiency of the propeller according to the invention, for a given diameter, is greater, or approximately equal, to the maximum efficiency of known propellers, a slight superiority of the latter being obtained, in limited cases, only at the cost of '' a significantly larger axial size.

Claims

Revendications claims
1. Hélice de ventilateur, notamment pour le refroidissement du moteur d'entraînement d'un véhicule automobile, comprenant un moyeu (2) et des pales (1) s 'étendant radialement vers l'extérieur à partir du moyeu, le moyeu étant propre à être fixé sur l'arbre d'un moteur de manière à permettre au moteur de transmettre à l'hélice une puissance d'au moins 150 watts, caractérisée en ce que sa longueur axiale L, mesurée en mètre, est inférieure ou sensiblement égale à la valeur L0 donnée par la formule (I) suivante:1. Fan propeller, in particular for cooling the drive motor of a motor vehicle, comprising a hub (2) and blades (1) extending radially outward from the hub, the hub being clean to be fixed on the shaft of an engine so as to allow the engine to transmit to the propeller a power of at least 150 watts, characterized in that its axial length L, measured in meters, is less than or substantially equal at the value L 0 given by the following formula (I):
L0 = 0,426262 - 5, 14288. D + 23, 1798. D2 - 44, 2505. D3 + 30, 8841. D4,L 0 = 0.426262 - 5, 14288. D + 23, 1798. D 2 - 44, 2505. D 3 + 30, 8841. D 4 ,
D étant le diamètre de l'hélice mesuré en mètre.D being the diameter of the propeller measured in meters.
2. Hélice selon la revendication 1, caractérisée en ce que L est sensiblement égale à L0.2. Propeller according to claim 1, characterized in that L is substantially equal to L 0 .
3. Hélice selon l'une des revendications 1 et 2 , caractérisée en ce que L ne s'écarte pas de L0 de plus de 20 %.3. Propeller according to one of claims 1 and 2, characterized in that L does not deviate from L 0 by more than 20%.
4. Hélice selon l'une des revendications précédentes, caractérisée en ce que les extrémités axiales des pales et du moyeu tournées vers l'aval du flux d'air produit par l'hélice sont sensiblement contenues dans un même plan radial (19).4. Propeller according to one of the preceding claims, characterized in that the axial ends of the blades and of the hub facing downstream of the air flow produced by the propeller are substantially contained in the same radial plane (19).
5. Hélice selon la revendication 4, caractérisée en ce que le bord de fuite des pales est entièrement contenu dans ledit plan radial.5. Propeller according to claim 4, characterized in that the trailing edge of the blades is entirely contained in said radial plane.
6. Hélice selon l'une des revendications précédentes, caractérisée en ce que les extrémités axiales des pales et du moyeu tournées vers l'amont du flux d'air produit par l'hélice sont sensiblement contenues dans un même plan radial. 6. Propeller according to one of the preceding claims, characterized in that the axial ends of the blades and of the hub turned upstream of the air flow produced by the propeller are substantially contained in the same radial plane.
7. Hélice selon l'une des revendications précédentes, caractérisée en ce que les extrémités radialement extérieures des pales sont reliées entre elles par une virole (3).7. Propeller according to one of the preceding claims, characterized in that the radially outer ends of the blades are connected together by a ferrule (3).
8. Hélice selon l'une des revendications précédentes, caractérisée en ce que les pales sont sensiblement identiques entre elles et uniformément espacées dans la direction circonférentielle selon un pas angulaire β , le point (Ms) situé à mi-distance des bords d'attaque et de fuite à l'extrémité radialement extérieure étant décalé par rapport au point correspondant (M-.) au pied de la pale, dans le sens opposé au sens de rotation (FI) de l'hélice, d'un angle a compris entre la moitié et les trois quarts environ dudit pas angulaire.8. Propeller according to one of the preceding claims, characterized in that the blades are substantially identical to each other and uniformly spaced in the circumferential direction at an angular pitch β, the point (M s ) located midway between the edges of attack and flight at the radially outer end being offset from the corresponding point (M-.) at the foot of the blade, in the direction opposite to the direction of rotation (FI) of the propeller, by an angle a between about half and three quarters of said angular pitch.
9. Hélice selon l'une des revendications précédentes, caractérisée en ce que les bords d'attaque et de fuite de chaque pale sont bombés dans le sens de rotation de l'hélice, le point (M) situé à mi-distance de ceux-ci s 'écartant progressivement vers l'arrière du plan axial (P) contenant sa position (M-.) au pied de la pale, puis revenant progressivement jusque dans ce plan, sur une fraction de l'étendue radiale de la pale comprise entre 20 % et 70 %, et s 'écartant progressivement de ce même plan vers l'avant sur la fraction restante.9. Propeller according to one of the preceding claims, characterized in that the leading and trailing edges of each blade are curved in the direction of rotation of the propeller, the point (M) located midway between those -this progressively moving backwards from the axial plane (P) containing its position (M-.) at the foot of the blade, then gradually returning to this plane, over a fraction of the radial extent of the blade included between 20% and 70%, and progressively deviating from this same plane forward on the remaining fraction.
10. Hélice selon l'une des revendications précédentes, caractérisée en ce que l'angle aigu Ω entre la corde (25) de la section transversale aplatie d'une pale et un plan radial (19) décroît progressivement au moins sur les derniers 30 % de l'étendue radiale de la pale.10. Propeller according to one of the preceding claims, characterized in that the acute angle Ω between the cord (25) of the flattened cross section of a blade and a radial plane (19) decreases progressively at least over the last 30 % of the radial extent of the blade.
11. Hélice selon l'une des revendications précédentes, caractérisée en ce que le moyeu comprend une paroi senεible- ment cylindrique (4) à partir de laquelle s'étendent les pales, et une paroi de fond (5) disposée sensiblement selon un plan radial, tournée vers l'amont du flux d'air produit par l'hélice, la paroi cylindrique et la paroi de fond étant raccordées entre elles par un arrondi convexe (6) d'un rayon de courbure compris entre 4 et 8 mm.11. Propeller according to one of the preceding claims, characterized in that the hub comprises a substantially cylindrical wall (4) from which the blades extend, and a bottom wall (5) arranged substantially in a plane radial, facing upstream of the air flow produced by the propeller, the cylindrical wall and the bottom wall being connected together by a convex rounding (6) with a radius of curvature between 4 and 8 mm.
12. Hélice selon la revendication 11, caractérisée en ce que l'arrondi a sensiblement un profil en quart de cercle de rayon 5 mm.12. Propeller according to claim 11, characterized in that the rounding has substantially a quarter-circle profile with a radius of 5 mm.
13. Hélice selon l'une des revendications 11 et 12, caractérisée en ce que les pales s'étendent sur toute la longueur axiale de la paroi cylindrique (6) du moyeu.13. Propeller according to one of claims 11 and 12, characterized in that the blades extend over the entire axial length of the cylindrical wall (6) of the hub.
14. Hélice selon l'une des revendications précédentes, caractérisée en ce que le moyeu est creux et présente intérieurement des nervures ( 9 ) . 14. Propeller according to one of the preceding claims, characterized in that the hub is hollow and internally has ribs (9).
EP99934796A 1998-07-28 1999-07-28 Fan blade Revoked EP1034376B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR9809648A FR2781843B1 (en) 1998-07-28 1998-07-28 OPTIMIZED COMPACT FAN PROPELLER
FR9809648 1998-07-28
PCT/FR1999/001861 WO2000006913A1 (en) 1998-07-28 1999-07-28 Fan blade

Publications (2)

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EP1034376A1 true EP1034376A1 (en) 2000-09-13
EP1034376B1 EP1034376B1 (en) 2003-04-23

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EP99934796A Revoked EP1034376B1 (en) 1998-07-28 1999-07-28 Fan blade

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DE (1) DE69907134T2 (en)
ES (1) ES2198929T3 (en)
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WO (1) WO2000006913A1 (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6428277B1 (en) * 2001-05-17 2002-08-06 Siemens Vdo Automotive Inc. High speed, low torque axial flow fan
FR2848619B1 (en) * 2002-12-13 2006-03-17 Valeo Systemes Dessuyage ENGINE COOLING PROPELLER
US6872052B2 (en) * 2003-03-07 2005-03-29 Siemens Vdo Automotive Inc. High-flow low torque fan
US7484925B2 (en) * 2005-05-10 2009-02-03 Emp Advanced Development, Llc Rotary axial fan assembly
FR2898943B1 (en) 2006-03-23 2012-08-31 Valeo Systemes Thermiques FAN PROPELLER, ESPECIALLY FOR AUTOMOTIVE VEHICLES
US20070237656A1 (en) * 2006-04-11 2007-10-11 Pipkorn Nicholas T Rotary fan with encapsulated motor assembly
EP1862675B1 (en) * 2006-05-31 2009-09-30 Robert Bosch GmbH Axial fan assembly
US8091177B2 (en) 2010-05-13 2012-01-10 Robert Bosch Gmbh Axial-flow fan
US9091452B2 (en) * 2012-11-14 2015-07-28 Yu-Chi Yen Misting fan
CN115750439B (en) * 2022-11-16 2023-06-16 南昌航空大学 An air-cooled integrated ducted fan based on boundary layer intake

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3220574A1 (en) * 1982-06-01 1983-12-01 Siemens AG, 1000 Berlin und 8000 München STEEL-FREE AXIAL FAN, ESPECIALLY FOR ELECTRICALLY DRIVED MOTOR VEHICLE RADIATOR FANS
DE3335649A1 (en) * 1983-09-30 1985-04-18 Siemens AG, 1000 Berlin und 8000 München STEERING WHEELLESS AXIAL FAN, ESPECIALLY FOR VENTILATING HEAT EXCHANGERS
US5000660A (en) * 1989-08-11 1991-03-19 Airflow Research And Manufacturing Corporation Variable skew fan
EP0446316B2 (en) * 1989-09-29 2001-12-05 Micronel AG Miniature fan
ES2087501T5 (en) * 1992-01-30 1999-04-16 Spal Srl A FAN WITH CONVEX BLADES.
EP0913584B1 (en) * 1992-05-15 2005-07-20 Siemens VDO Automotive Inc. Axial flow fan
US5399070A (en) * 1992-07-22 1995-03-21 Valeo Thermique Moteur Fan hub
US5423660A (en) * 1993-06-17 1995-06-13 Airflow Research And Manufacturing Corporation Fan inlet with curved lip and cylindrical member forming labyrinth seal
US5490693A (en) 1994-09-28 1996-02-13 Cajon Company Tube coupling locking device
EP0704625B1 (en) * 1994-09-29 2003-01-15 Valeo Thermique Moteur A fan
US5577888A (en) * 1995-06-23 1996-11-26 Siemens Electric Limited High efficiency, low-noise, axial fan assembly
US5769607A (en) * 1997-02-04 1998-06-23 Itt Automotive Electrical Systems, Inc. High-pumping, high-efficiency fan with forward-swept blades
US5957661A (en) * 1998-06-16 1999-09-28 Siemens Canada Limited High efficiency to diameter ratio and low weight axial flow fan

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO0006913A1 *

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Publication number Publication date
DE69907134D1 (en) 2003-05-28
FR2781843A1 (en) 2000-02-04
FR2781843B1 (en) 2000-10-20
WO2000006913A1 (en) 2000-02-10
EP1034376B1 (en) 2003-04-23
DE69907134T2 (en) 2004-02-26
US6350104B1 (en) 2002-02-26
ES2198929T3 (en) 2004-02-01

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