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EP1996818B1 - Lüfterpropeller, insbesondere für kraftfahrzeuge - Google Patents

Lüfterpropeller, insbesondere für kraftfahrzeuge Download PDF

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Publication number
EP1996818B1
EP1996818B1 EP07726892.8A EP07726892A EP1996818B1 EP 1996818 B1 EP1996818 B1 EP 1996818B1 EP 07726892 A EP07726892 A EP 07726892A EP 1996818 B1 EP1996818 B1 EP 1996818B1
Authority
EP
European Patent Office
Prior art keywords
blade
thickness
leading edge
fan impeller
blades
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.)
Active
Application number
EP07726892.8A
Other languages
English (en)
French (fr)
Other versions
EP1996818A1 (de
Inventor
Stéphane MOREAU
Antoine Levasseur
Aurélien LEVASSEUR
Manuel Henner
Bruno Demory
Cédric LEBERT
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 Systemes Thermiques SAS
Original Assignee
Valeo Systemes Thermiques SAS
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 Thermiques SAS filed Critical Valeo Systemes Thermiques SAS
Priority to PL07726892T priority Critical patent/PL1996818T3/pl
Publication of EP1996818A1 publication Critical patent/EP1996818A1/de
Application granted granted Critical
Publication of EP1996818B1 publication Critical patent/EP1996818B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form

Definitions

  • a fan impeller includes a hub and blades extending radially outwardly from the hub, the blades having a flattened cross section with an airfoil profile with a leading edge and an edge between which a rope is defined.
  • Such propellers are used in particular for cooling the drive motor of motor vehicles, the propeller producing a flow of air through a heat exchanger, namely the cooling radiator of the drive motor.
  • the hub of the propeller also called “bowl” is adapted to be wedged on the shaft of a motor, which can be an electric motor driven by a control electronics.
  • flatened transverse section here means the plane closed curve obtained by cutting the blade by a cylindrical surface of revolution about the axis of the helix, and by unrolling this cylindrical surface flat.
  • the string is then defined as the line segment connecting the leading edge and the trailing edge.
  • Fan propellers are generally made by molding a plastic material. To reduce manufacturing costs, it is usual to make the blades of the propeller in the form of an airfoil profile of thickness as low as possible.
  • Thin blade propellers are compatible with a decrease in axial size, but are however better adapted to the cooling of motor vehicle engines in the case where the propeller is at a significant distance (typically several centimeters) from the radiator cooling beam.
  • thin-blade propellers as taught for example by FR-A-2,781,843 and US 2005/232778 have their aeraulic and acoustic performance degraded when they are at a close distance from the beam of a heat exchanger, for example a cooling radiator. This degradation is mainly due to the disturbances caused by the strong turbulence resulting from the heat exchangers.
  • Near distance here means a distance that is typically of the order of 1 cm.
  • the invention provides a solution to these problems.
  • a fan propeller of the type defined above in which the blade has a relative thickness which reaches its maximum value in the first quarter of the length of the rope from the leading edge, the relative thickness being defined by the ratio between the thickness of the blade and the length of the rope.
  • the blade has its maximum thickness in the first quarter of the rope from the leading edge. Furthermore, it is advantageous that this maximum relative thickness is at least 12%.
  • the blade of the propeller of the invention has a more massive profile, of the bulbous type, in the region immediately following the leading edge.
  • the leading edge has a radius of curvature as large as possible. This contributes to giving the profile of the blade a bulbous shape in the region following the leading edge.
  • the aircraft wing profile has a mean line (neutral fiber) without inflection point.
  • the airfoil profile comprises a lower surface having a curvature inversion. This characteristic makes it possible in particular to limit the disturbances and noise generated by the trailing edge.
  • the radially outer ends of the blades are interconnected by a ferrule.
  • the propeller 10 as represented on the Figures 1 to 3 comprises a multiplicity of blades 12, here nine in number, which extend generally radially from a central hub 14, also called “bowl”, and connected together, at the periphery of the propeller, by a ferrule 16.
  • the hub, the blades and the ferrule are formed integrally by molding, in particular a plastics material.
  • the hub 14 has a cylindrical wall of revolution 18 to which the feet of the blades 12 are connected and a flat front wall 20 facing upstream relative to the direction of the air flow produced by the rotation of the propeller.
  • the direction of rotation of the helix is indicated by the arrow F on the figures 1 and 3 .
  • a hole 22 to allow to wedge the propeller on a drive shaft (not shown) connected to an electric motor (not shown).
  • the blades 12 are generally identical and have a generally curved shape from the wall 18 of the hub 14 to the shell 16.
  • the cross section of the blade has a general airfoil profile with a leading edge 24 and a trailing edge 26.
  • airfoil profile is meant here an aerodynamic profile with rounded leading and trailing edges with no protruding angle and / or continuously varying thickness.
  • the rope 28 that is to say the line segment extending between the leading edge 24 and the trailing edge 28, is inclined at an acute angle with respect to a plane radial P, that is to say a plane perpendicular to the axis of the helix.
  • This acute angle generally varies over the length of the blade, from the root of the blade which is fixed to the hub to the head of the blade which is fixed to the ferrule.
  • the length of the rope 28, between the leading edge 24 and the trailing edge 26, has a value L which is reported on the figure 4 .
  • FIG 5 generally illustrates a blade profile, not in accordance with the invention.
  • the figure 5 shows the flattened cross section of the blade, according to the previous definition, which has an airfoil profile.
  • the rope C of the profile extends between the leading edge BA and the trailing edge BF and has a length L.
  • the wing has an upper surface Ext ("extrados") and a lower surface Int ("intrados").
  • the profile comprises a mean line LM, also called “neutral fiber", which extends substantially halfway between the intrados and the extrados.
  • the thickness E of the blade is defined with respect to a circle whose center is located on the middle line (neutral fiber) and which comes into contact with the intrados and the extrados.
  • the points of tangency P 1 and P 2 of the circle with respectively the extrados and the intrados delimit a line segment which defines the thickness E at the considered points.
  • a relative thickness E rel is also possible to define as being the ratio between the thickness E of the profile and the length L of the rope.
  • the profile of the aircraft wing type has a thickness that is generally greater than the similar profiles of the prior art (see in particular FR-A-2,781,843 ).
  • the blade has a relative thickness E rel that reaches its maximum value E max in the first quarter of the length of the rope from the leading edge 24.
  • This maximum relative thickness E max is at least 12%. According to the invention, it may have a value of up to 20%, and which will most often be of the order of 15%.
  • the profile has, on the leading edge side, a characteristic bulbous shape, that is to say a more massive shape than in the case of the blades of the prior art. To favor this bulbous shape, the leading edge 24 has the largest possible radius of curvature.
  • the trailing edge 26 has a thickness as small as possible. This means that after the zone where the thickness is maximum, the upper surface 30 and the lower surface 32 are progressively closer to one another. In the example, the intrados 32 has an inversion of curvature, which makes it possible to reduce the thickness of the blade as one approaches the trailing edge 26.
  • the figure 7 is a similar representation, the difference being that the maximum thickness is on the abscissa. It can be seen that the yield or efficiency (dashed curve) has a peak in the position corresponding to substantially 12%. In addition, the sound pressure level decreases and reaches acceptable values between 12% and 20%. This shows that for values of E max between 12% and 20%, the sound pressure level is particularly low. On the other hand, the efficiency is greatest when one is close to the value of 12%. It then tends to decrease as we approach the value of 20%.
  • the invention finds particular application to the cooling helices of motor vehicle engines.

Landscapes

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

Claims (6)

  1. Lüfterrad zur Kühlung des Antriebsmotors eines Kraftfahrzeugs, das eine Nabe (14) und sich ausgehend von der Nabe radial nach außen erstreckende Blätter (12) aufweist, wobei die Blätter einen abgeflachten Querschnitt mit Flugzeugflügelprofil mit einer Vorderkante (24) und einer Hinterkante (26) haben, zwischen denen eine Sehne (28) definiert ist,
    dadurch gekennzeichnet, dass das Blatt (12) eine relative Dicke (Erel) hat, die ihren maximalen Wert (Emax) im ersten Viertel der Länge der Sehne (28) ausgehend von der Vorderkante (24) erreicht, wobei die relative Dicke durch das Verhältnis zwischen der Dicke (E) des Blatts und der Länge (L) der Sehne (28) definiert wird, und dass die maximale relative Dicke (Emax) zwischen 12% und 20% liegt.
  2. Lüfterrad nach Anspruch 1, dadurch gekennzeichnet, dass die maximale relative Dicke (Emax) in der Größenordnung von 15% liegt.
  3. Lüfterrad nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass die Vorderkante (24) einen größtmöglichen Krümmungsradius aufweist.
  4. Lüfterrad nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass das Flugzeugflügelprofil eine Mittellinie (LM) ohne Knickpunkt aufweist.
  5. Lüfterrad nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass das Flugzeugflügelprofil eine Unterseite (32) aufweist, die eine Krümmungsumkehr aufweist.
  6. Lüfterrad nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die radial äußeren Enden der Blätter (12) miteinander durch einen Ring (16) verbunden sind.
EP07726892.8A 2006-03-23 2007-03-14 Lüfterpropeller, insbesondere für kraftfahrzeuge Active EP1996818B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL07726892T PL1996818T3 (pl) 2006-03-23 2007-03-14 Śmigło wentylatora, w szczególności dla pojazdów samochodowych

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0602510A FR2898943B1 (fr) 2006-03-23 2006-03-23 Helice de ventilateur, en particulier pour vehicules automobiles
PCT/EP2007/052401 WO2007107489A1 (fr) 2006-03-23 2007-03-14 Helice de ventilateur, en particulier pour vehicules automobiles

Publications (2)

Publication Number Publication Date
EP1996818A1 EP1996818A1 (de) 2008-12-03
EP1996818B1 true EP1996818B1 (de) 2014-03-05

Family

ID=37428624

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07726892.8A Active EP1996818B1 (de) 2006-03-23 2007-03-14 Lüfterpropeller, insbesondere für kraftfahrzeuge

Country Status (7)

Country Link
US (1) US8186957B2 (de)
EP (1) EP1996818B1 (de)
CN (1) CN101427030B (de)
ES (1) ES2467890T3 (de)
FR (1) FR2898943B1 (de)
PL (1) PL1996818T3 (de)
WO (1) WO2007107489A1 (de)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2950660B1 (fr) 2009-09-29 2017-08-25 Valeo Systemes Thermiques Helice, dispositif de refroidissement moteur comprenant une telle helice, procede et moule de fabrication de ladite helice
USD670803S1 (en) * 2010-11-04 2012-11-13 Spal Automotive S.R.L. Fan
CN101988522B (zh) * 2010-12-01 2012-08-29 鑫贺精密电子(东莞)有限公司 散热风扇
US9404511B2 (en) * 2013-03-13 2016-08-02 Robert Bosch Gmbh Free-tipped axial fan assembly with a thicker blade tip
JP5825339B2 (ja) * 2013-12-27 2015-12-02 ダイキン工業株式会社 クロスフローファンの翼
CN105351248B (zh) * 2015-12-17 2017-12-12 新昌县三新空调风机有限公司 一种风扇用高性能翼型
USD911512S1 (en) 2018-01-31 2021-02-23 Carrier Corporation Axial flow fan
CN111120399A (zh) * 2020-01-21 2020-05-08 浙江银轮机械股份有限公司 风扇的风叶及冷却风扇
CN114673685B (zh) * 2020-12-25 2024-07-12 广东美的白色家电技术创新中心有限公司 风机叶片叶型构建方法、风机叶片、风机设备和储存介质

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE509627A (de) *
JPS5688995U (de) * 1979-12-12 1981-07-16
US5328330A (en) 1993-08-02 1994-07-12 Hudson Products Corporation Extruded aluminum fan blade
IT1271651B (it) * 1994-06-27 1997-06-04 Cofimco Srl Pala non svergolata per ventilatore assiale
US5996685A (en) * 1995-08-03 1999-12-07 Valeo Thermique Moteur Axial flow fan
US5769607A (en) * 1997-02-04 1998-06-23 Itt Automotive Electrical Systems, Inc. High-pumping, high-efficiency fan with forward-swept blades
FR2781843B1 (fr) 1998-07-28 2000-10-20 Valeo Thermique Moteur Sa Helice de ventilateur compacte optimisee
US6398802B1 (en) * 1999-06-21 2002-06-04 Scimed Life Systems, Inc. Low profile delivery system for stent and graft deployment
GB2362927A (en) * 2000-03-07 2001-12-05 Elta Fans Ltd A hub for a fan blade
EP1337758B1 (de) * 2000-11-08 2006-02-08 Robert Bosch Corporation Hocheffizienter, zustromangepasster axiallüfter
ITMI20010131A1 (it) * 2001-01-25 2002-07-26 Giorgio Cipelletti Ventilatore assiale con pale a torsione differenziata
CN2470590Y (zh) * 2001-02-22 2002-01-09 安徽天大(集团)股份有限公司工程塑料厂 一种轴流风扇
NL1019437C2 (nl) * 2001-11-26 2003-05-27 Ventilatoren Sirocco Howden Bv Rotorbladprofiel.
JP2005282492A (ja) * 2004-03-30 2005-10-13 Mitsubishi Fuso Truck & Bus Corp 翼形状作成プログラム及び方法

Also Published As

Publication number Publication date
JP5362545B2 (ja) 2013-12-11
JP2009530539A (ja) 2009-08-27
US8186957B2 (en) 2012-05-29
WO2007107489A1 (fr) 2007-09-27
PL1996818T3 (pl) 2014-09-30
US20090311101A1 (en) 2009-12-17
EP1996818A1 (de) 2008-12-03
CN101427030A (zh) 2009-05-06
FR2898943A1 (fr) 2007-09-28
FR2898943B1 (fr) 2012-08-31
CN101427030B (zh) 2013-01-23
ES2467890T3 (es) 2014-06-13

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