EP1034376B1 - Fan blade - Google Patents
Fan blade Download PDFInfo
- Publication number
- EP1034376B1 EP1034376B1 EP99934796A EP99934796A EP1034376B1 EP 1034376 B1 EP1034376 B1 EP 1034376B1 EP 99934796 A EP99934796 A EP 99934796A EP 99934796 A EP99934796 A EP 99934796A EP 1034376 B1 EP1034376 B1 EP 1034376B1
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- European Patent Office
- Prior art keywords
- impeller
- hub
- blades
- impeller according
- less
- 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.)
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Classifications
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- 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
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- 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 to from the hub, the hub being suitable for being fixed on the shaft of a motor so as to allow the motor to transmit at least 150 watts of power to the propeller.
- Such propellers are used in particular for cooling motor vehicle driving engine, the propeller producing an air flow through a radiator cooling and are known for example from patent application EP 0 096 255 A1.
- 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):
- the 0 0.426262 - 5.14288.D + 23.1798.D 2 - 44.2505.D 3 + 30.8841.D 4 , D being the diameter of the propeller measured in meters.
- 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 propeller illustrated in Figures 1 to 4 includes, so classic, a multiplicity of blades 1 generally extending radially from a central hub 2 and connected between them, on the periphery of the propeller, by a ferrule 3.
- the hub, blades and ferrule are formed in one part by molding.
- the hub 2 has an annular wall cylindrical of revolution 4, to which the feet of the blades 1, and a flat front wall 5, turned upstream, the terms upstream and downstream referring here to direction of the air flow produced by the rotation of the propeller.
- the walls 4 and 5 are interconnected by a rounded 6 to profile in an arc of a radius of 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 represented.
- Reinforcement ribs 9 are provided at the interior of the hub 2.
- the ferrule 3 also has a cylindrical annular wall of revolution 10, to which connect the ends of the blades, and which continues, upstream side, by a rounded flare 11.
- the wall 5 of the hub which in FIG. 1 represents the end axial of the latter 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 moves gradually downstream from the foot 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 situated 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 arrow F1, relative to the point M p 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 F1, as well as the center line 23 along which moves, from the foot to the end of the blade, the point M located midway between the leading and trailing edges, the line 23 having the points M p and M s mentioned above as ends.
- the line 23 progressively deviates towards the rear of the axial plane P containing the latter, then gradually returns to cut the plane P at a point M i . It then gradually deviates from this same plane forward, up to point M s .
- the distance between the points M p and M i 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.
- Figure 4 shows the flat cross section of a pale, i.e. the closed plane curve obtained by cutting the blade by a cylindrical surface of revolution around the axis A of the propeller, and unrolling this surface flat cylindrical.
- This flattened cross section has a airplane wing profile, the rope 25 of which is inclined by 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 on the last 30% of the radial extent of the blade, i.e. from the cylindrical surface 27 indicated on the Figure 3 to wall 10, the distance between surface 27 and the wall 10 representing 30% of the distance between the walls 4 and 10.
- point 28 of the cross section flattened farthest from the rope 25 is found substantially equidistant from the ends thereof, while the distance h between point 28 and rope 25 is at least equal to 3% of the length 1 thereof, and in particular equal to 10% of this length.
- Figure 7 shows on a larger scale the region of the flattened cross section of the blade close to the edge attack.
- 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 for coordinates the diameter and the axial length, in millimeters, of the fan 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 were defined by the method of calculation known as “Computational Fluid Dynamics”(CFD), described by Éric Coggiola et al. In article AIAA 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, January 12-15, 1998.
- CFD computational 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)
Description
L'invention concerne une hélice de ventilateur comprenant un moyeu et des pales 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.The invention relates to a fan propeller comprising a hub and blades extending radially outward to from the hub, the hub being suitable for being fixed on the shaft of a motor so as to allow the motor to transmit at least 150 watts of power to the propeller.
De telles hélices sont utilisées notamment pour le refroidissement du moteur d'entraínement de véhicules automobiles, l'hélice produisant un flux d'air à travers un radiateur de refroidissement et sont connues par example de la demande de brevet EP 0 096 255 A1.Such propellers are used in particular for cooling motor vehicle driving engine, the propeller producing an air flow through a radiator cooling and are known for example from patent application EP 0 096 255 A1.
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 has been accepted so far that air flow performance and acoustics of such propellers are all the better as their diameter and their axial length are greater.
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 being generally very limited, it is desirable to have space-saving cooling propellers, 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 diameter given, the aeraulic and acoustic performances are not practically deteriorate only below a certain length optimal axial.
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:
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.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:
- 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.
- Le bord de fuite des pales est entièrement contenu dans ledit plan radial.
- 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.
- Les extrémités radialement extérieures des pales sont reliées entre elles par une virole.
- 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 α compris entre la moitié et les trois quarts environ dudit pas angulaire. Ceci concerne le cas des hélices dites symétriques.
- 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.
- L'angle aigu Ω entre la corde de la section transversale aplatie d'une pale et un plan radial décroít progressivement au moins sur les derniers 30 % de l'étendue radiale de la pale.
- 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 cylindrique et la paroi de fond étant raccordées entre elles par un arrondi convexe d'un rayon de courbure compris entre 4 et 8 mm.
- L'arrondi a sensiblement un profil en quart de cercle de
rayon 5 mm. - Les pales s'étendent sur toute la longueur axiale de la paroi cylindrique du moyeu.
- Le moyeu est creux et présente intérieurement des nervures.
- 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.
- The trailing edge of the blades is entirely contained in said radial plane.
- The axial ends of the blades and of the hub facing upstream of the air flow produced by the propeller are substantially contained in the same radial plane.
- The radially outer ends of the blades are interconnected by a ferrule.
- 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 α between about half and three quarters of said angular pitch. This concerns the case of so-called symmetrical propellers.
- The leading and trailing edges of each blade are curved in the direction of rotation of the propeller, the point located halfway between them gradually moving towards the rear of the axial plane containing its position at the 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 gradually moving away from this same plane forward on the remaining fraction.
- 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.
- The hub comprises a substantially cylindrical wall from which the blades extend, and a bottom wall arranged substantially in a radial plane, facing upstream of the air flow produced by the propeller, the cylindrical wall 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 substantially a 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.
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:
- la figure 1 est une vue axiale d'arrière d'une hélice de ventilateur selon l'invention;
- la figure 2 est une vue de côté en demi-coupe axiale de l'hélice;
- 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;
- 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
- 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 1 is an axial rear view of a fan propeller according to the invention;
- Figure 2 is a side view in axial half-section of the propeller;
- 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;
- 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; and
- 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'entraínement 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 includes, so
classic, a multiplicity of
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 turned towards
the downstream of the air flow and the trailing edge of the blades are
contained in the same
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 F1, par rapport
au point Mp 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 situated halfway between the leading
On voit également sur les figures 1 et 3 que le bord d'attaque
21 et le bord de fuite 20 de chaque pale sont bombés dans
le sens de rotation F1, 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 Mp et Ms précités.
A partir de Mp, 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 Mi. Elle
s'écarte ensuite progressivement de ce même plan vers
l'avant, jusqu'au point Ms. La distance entre les points Mp
et Mi 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
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, décroít 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.Figure 4 shows the flat cross section of a
pale, i.e. the closed plane curve obtained by cutting
the blade by a cylindrical surface of revolution around
the axis A of the propeller, and unrolling this surface flat
cylindrical. This flattened cross section has a
airplane wing profile, the
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,
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.Figure 7 shows on a larger scale the region of the
flattened cross section of the blade close to the edge
attack. According to the invention, the profile of the blade comprises
in this region an
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 Figure 5, each of the points marked by a cross, a triangle, a square or a circle has for coordinates the diameter and the axial length, in millimeters, of the fan 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.
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 were defined by the method of calculation known as "Computational Fluid Dynamics "(CFD), described by Éric Coggiola et al. In article AIAA 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, January 12-15, 1998.
Sur la figure 5, les points correspondant aux hélices
référencées 5 sont indiqués par des étoiles à huit branches.
La formule (I) n'est autre que l'équation de la courbe C1 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):
L0 et D étant mesurés en mètre. La droite représentative de cette équation est représentée en C2 sur la figure 5. Les courbes C1 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 higher, sometimes very significantly, than the value L 0 given by the formula I. We can also see 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 substantially larger axial size.
Claims (15)
- Fan impeller, particularly for cooling the engine that drives a motor vehicle, comprising a hub (2) and blades (1) extending radially outwards from the hub, the hub being able to be fixed to the shaft of a motor in such a way as to allow the motor to transmit to the impeller a power of at least 150 watts, characterized in that its axial length L, measured in metres, is less than or equal to the value L0 given by the following formula (I):
- Fan impeller, particularly for cooling the engine that drives a motor vehicle, comprising a hub (2) and blades (1) extending radially outwards from the hub, the hub being able to be fixed to the shaft of a motor in such a way as to allow the motor to transmit to the impeller a power of at least 150 watts, characterized in that its axial length L, measured in metres, is less than or equal to the value L0 given by the following formula (II):
- Impeller according to either of Claims 1 and 2, characterized in that L is more or less equal to L0.
- Impeller according to either of Claims 1 and 2, characterized in that L differs from L0 by no more than 20%.
- Impeller according to one of the preceding claims, characterized in that the axial ends of the blades and of the hub facing in the downstream direction of the airstream produced by the impeller are more or less contained in one and the same radial plane (19).
- Impeller according to Claim 5, characterized in that the trailing edge of the blades is entirely contained in the said radial plane.
- Impeller according to one of the preceding claims, characterized in that the axial ends of the blades and of the hub facing in the upstream direction of the airstream produced by the impeller are more or less contained in one and the same radial plane.
- Impeller according to one of the preceding claims, characterized in that the radially outer ends of the blades are joined together by a shroud (3).
- Impeller according to one of the preceding claims, characterized in that the blades are more or less mutually identical and uniformly spaced in the circumferential direction with an angular pitch β, the point (Ms) situated midway between the leading and trailing edges at the radially outer end being offset with respect to the corresponding point (Mp) at the blade root, in the opposite direction to the direction (F1) in which the impeller rotates, by an angle α of between half and about three-quarters of the said angular pitch.
- Impeller according to one of the preceding claims, characterized in that the leading and trailing edges of each blade are domed in the direction in which the impeller rotates, the point (M) situated midway between these diverging backwards progressively from the axial plane (P) containing its blade-root position (Mp) then gradually returning to this plane, over a fraction of between 20% and 70% of the radial extent of the blade and diverging forwards progressively from this same plane over the remaining fraction.
- Impeller according to one of the preceding claims, characterized in that the acute angle Ω between the chord (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.
- Impeller according to one of the preceding claims, characterized in that the hub comprises a more or less cylindrical wall (4) from which the blades extend, and an end wall (5) arranged more or less in a radial plane facing in the upstream direction of the airstream produced by the impeller, the cylindrical wall and the end wall being joined together by a convex rounded portion (6) with a radius of curvature of between 4 and 8 mm.
- Impeller according to Claim 12, characterized in that the rounded portion has more or less a profile of a quarter of a circle of radius 5 mm.
- Impeller according to either of Claims 12 and 13, characterized in that the blades extend over the entire axial length of the cylindrical wall (6) of the hub.
- Impeller according to one of the preceding claims, characterized in that the hub is hollow and has ribs (9) on the inside.
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)
| Publication Number | Publication Date |
|---|---|
| EP1034376A1 EP1034376A1 (en) | 2000-09-13 |
| EP1034376B1 true EP1034376B1 (en) | 2003-04-23 |
Family
ID=9529114
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP99934796A Revoked EP1034376B1 (en) | 1998-07-28 | 1999-07-28 | Fan blade |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US6350104B1 (en) |
| EP (1) | EP1034376B1 (en) |
| DE (1) | DE69907134T2 (en) |
| ES (1) | ES2198929T3 (en) |
| FR (1) | FR2781843B1 (en) |
| WO (1) | WO2000006913A1 (en) |
Families Citing this family (10)
| 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 |
| KR101018146B1 (en) * | 2006-05-31 | 2011-02-28 | 로베르트 보쉬 게엠베하 | 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 | Air-cooling integrated duct fan based on boundary layer ingestion |
Family Cites Families (13)
| 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. |
| DE69333845T2 (en) * | 1992-05-15 | 2006-04-27 | Siemens Vdo Automotive Inc., Chatham | Axial |
| 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 |
| DE69529379T2 (en) * | 1994-09-29 | 2003-10-09 | Valeo Thermique Moteur Le Mesn | 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 |
-
1998
- 1998-07-28 FR FR9809648A patent/FR2781843B1/en not_active Expired - Fee Related
-
1999
- 1999-07-28 ES ES99934796T patent/ES2198929T3/en not_active Expired - Lifetime
- 1999-07-28 WO PCT/FR1999/001861 patent/WO2000006913A1/en active IP Right Grant
- 1999-07-28 US US09/509,473 patent/US6350104B1/en not_active Expired - Lifetime
- 1999-07-28 EP EP99934796A patent/EP1034376B1/en not_active Revoked
- 1999-07-28 DE DE69907134T patent/DE69907134T2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| DE69907134D1 (en) | 2003-05-28 |
| FR2781843A1 (en) | 2000-02-04 |
| DE69907134T2 (en) | 2004-02-26 |
| EP1034376A1 (en) | 2000-09-13 |
| ES2198929T3 (en) | 2004-02-01 |
| US6350104B1 (en) | 2002-02-26 |
| FR2781843B1 (en) | 2000-10-20 |
| WO2000006913A1 (en) | 2000-02-10 |
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