US20130323072A1 - Axial fan - Google Patents

Axial fan Download PDF

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Publication number
US20130323072A1
US20130323072A1 US13/991,188 US201113991188A US2013323072A1 US 20130323072 A1 US20130323072 A1 US 20130323072A1 US 201113991188 A US201113991188 A US 201113991188A US 2013323072 A1 US2013323072 A1 US 2013323072A1
Authority
US
United States
Prior art keywords
hub
fan
axial fan
region
trailing edge
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.)
Abandoned
Application number
US13/991,188
Other languages
English (en)
Inventor
Uwe Aschermann
Uwe Blass
Frederic Guilbaud
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.)
Mahle Behr GmbH and Co KG
Original Assignee
Behr GmbH and Co KG
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 Behr GmbH and Co KG filed Critical Behr GmbH and Co KG
Assigned to BEHR GMBH & CO. KG reassignment BEHR GMBH & CO. KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GUILBAUD, FREDERIC, BLASS, UWE, ASCHERMANN, UWE
Publication of US20130323072A1 publication Critical patent/US20130323072A1/en
Abandoned legal-status Critical Current

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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
    • F04D19/00—Axial-flow pumps
    • F04D19/002—Axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/022—Units comprising pumps and their driving means comprising a yielding coupling, e.g. hydraulic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/329—Details of the hub

Definitions

  • the invention relates to an axial fan for delivering cooling air, in particular for an internal combustion engine of a motor vehicle, as per the preamble of patent claim 1 .
  • a generic axial fan is disclosed in the prior patent application of the applicant with the official file reference 2010 042 325.4.
  • the axial fan has fan blades which are fastened to a hub ring and which, on their pressure side, have a hub ramp, and on their suction side, have air-guiding elements, also referred to as stabilizers, which serve for influencing the fan flow.
  • the fan blades have in each case a leading edge, also referred to as flow impingement edge, and a trailing edge, also referred to as flow-off edge.
  • the trailing edge of the fan blade has substantially two radially extending portions, specifically an outer portion arranged outside the hub ramp and an inner portion arranged within the hub ramp.
  • the inner portion of the trailing edge is, for weight-saving reasons, angled inward, that is to say in the direction of the hub ring, so as to form a recess for the trailing edge and thus a reduction of the width of the fan blade. It has been found that, as a result of said recess of the trailing edge, a transverse flow and/or backflow of the fan blade flow occurs, which adversely affects the flow on the pressure side of the adjacent fan blade. Said backflow and/or transverse flow gives rise, in the region of the hub ramp, to a vortex structure which results in a decrease in efficiency.
  • EP 0 515 839 A1 discloses an axial fan having fan blades, on the pressure side of which is arranged a hub ramp which rises counter to the flow direction.
  • the hub ramp in effect fills out the stagnant area in the region of the vane root and thus prevents a loss-afflicted vortex flow.
  • the fan blade has a trailing edge with two portions, wherein a first, outer portion is situated radially outside the hub ramp and a second, inner portion is situated radially within the hub ramp.
  • the trailing edge it is advantageous for the trailing edge to have, in the outer region radially outside the hub ramp, a profile which continues in substantially unchanging fashion radially inward across the radial position of the hub ramp into the inner region, and which, in the radially innermost region, runs toward the hub.
  • the radially innermost region is advantageous for the radially inner component of the radius of the radially inner region.
  • said component is also advantageous for said component to be approximately one third, approximately one quarter or preferably less than approximately one fifth of the radius of the inner region of the trailing edge.
  • the trailing edge it is advantageous for the trailing edge to have, in the outer region radially outside the hub ramp, a profile which continues in substantially unchanging fashion radially inward across the radial position of the hub ramp into the so-called intermediate region of the inner region, and which, in the radially innermost region, runs toward the hub.
  • said “running toward the hub” may mean curved or angled etc.
  • the fan blade advantageously also has substantially the same blade depth in the inner region as in the outer region, that is to say in particular the blade trailing edge merges substantially rectilinearly from the outer portion into the inner portion, such that overall, a straight trailing edge is formed as far as into the vane root region.
  • a certain curvature of the leading edge is not detrimental; for simplicity, however, said leading edge has been assumed in this examination as being straight, wherein a non-straight, curved leading edge would likewise be admissible.
  • blade depth is to be understood to mean the axial extent of the fan blade.
  • the blade depth is the projection of the blade width in the circumferential direction, wherein the blade width is the spacing between the blade leading edge and blade trailing edge, measured in the direction of the chord.
  • the trailing edge in the innermost region, is rounded. A reduced-stress transition of the blade trailing edge into the hub region is made possible in this way.
  • the blade trailing edge in its innermost region, merges—via a rounding—into the free edge of the hub ramp.
  • An increase of the strength in the vane root region for the connection of the fan blade to the hub is attained in this way.
  • a streamlined duct is formed between the suction side and the pressure side in the vane root and hub ramp region.
  • the free edge of the hub ramp is to be understood to mean that edge of the hub ramp which faces away from the fan blade and which projects from the fan blade.
  • stabilizers are arranged on the suction side of the fan blades, which stabilizers are preferably situated radially within the hub ramp. The downstream region of the stabilizer thus issues into the inner portion of the blade trailing edge.
  • the stabilizers in conjunction with the hub ramps between the two vanes yield a further stabilization of the flow in the vane root region.
  • the hub is in the form of a hub ring which has a significantly smaller axial extent than the fan blades. There is thus no longer a cylindrical hub in the classic sense.
  • the axial extent of the fan blades as represented by a projection of the blade width in the circumferential direction is referred to as the blade depth.
  • the fan blades project both with their leading edges and also with their trailing edges beyond the end faces of the hub ring. In this respect, the trailing edge which runs rectilinearly as far as into the innermost region forms an axial projecting length of the fan blade with respect to the hub ring.
  • the axial fan has a hub ratio D i /D a of greater than 42%, wherein the hub ratio is the quotient of hub diameter and outer diameter of the fan blades.
  • the axial projecting length of the blade trailing edge in the inner region has a particularly advantageous effect in the case of fans with a relatively large hub ratio, because this has an adverse effect on the efficiency and on the volume flow rate delivered by the fan—in this respect, compensation is generated here.
  • the relatively large hub ratio may arise here owing to a relatively small outer diameter if the fan blades are shortened owing to performance gradation.
  • the axial fan is fixedly connected via its hub ring to a liquid friction clutch, which in turn is driven by the internal combustion engine and drives the fan with a regulated drive output rotational speed.
  • a liquid friction clutch which in turn is driven by the internal combustion engine and drives the fan with a regulated drive output rotational speed.
  • the diameter of the liquid friction clutch and thus the hub diameter increases, which may lead to a larger hub ratio.
  • the projecting blade length according to the invention which leads to an increase in efficiency and in volume flow rate, has a particularly positive effect here.
  • the fan blades are angled in the region of the blade root, whereby the form of a vane for the fan blade is defined.
  • Advantages here are a low material accumulation in the region of the connection of fan blade and hub ring, and an increased strength.
  • FIG. 1 shows a fan blade design according to the prior art
  • FIG. 2 shows a fan blade design according to the invention with stabilized flow
  • FIG. 3 shows a detail of a fan according to the invention in a three-dimensional illustration
  • FIG. 4 shows a radial section through the fan hub
  • FIG. 5 shows a partial view of the axial fan in the section plane VI-VI
  • FIG. 6 shows a sectional illustration as per section plane VI-VI in FIG. 5 .
  • FIG. 1 shows an arrangement of fan blades 1 , 2 of an axial fan according to the prior art.
  • the direction of rotation of the fan is indicated by an arrow D.
  • the fan blades 1 , 2 have hub ramps 3 , 4 in each case on their pressure side, and have blade trailing edges 1 a , 2 a .
  • the trailing edges or flow-off edges 1 a , 2 a each have cutouts or recesses 5 , 6 in their radially inner region, that is to say within the hub ramp 3 , 4 .
  • Such recesses and shortenings of the fan blade width were implemented in the prior art because they firstly yield a weight saving, and secondly, it was believed that no further increase in performance of the fan blade is attained in the vane root region.
  • FIG. 2 schematically shows a design according to the invention of fan blades 7 , 8 and the blade trailing edges 7 a , 8 a thereof.
  • the direction of rotation of the axial fan is again denoted by an arrow D.
  • hub ramps 9 , 10 which divide the blade trailing edges 7 a , 8 a into a radially outer region and a radially inner region.
  • the radially inner region of the blade trailing edge 7 a runs substantially straight, that is to say there is a substantially straight profile from the transition from the outer region to the inner region.
  • the vane width of the fan blade 7 is increased in the radially inner region in relation to the vane width of the fan blade 1 according to the prior art, such that no recess is provided.
  • Said enlarged region is highlighted by a contour 7 b illustrated in bold.
  • the effect of the increased vane width in the region 7 b is a prevention of the loss-afflicted transverse flow and/or backflow illustrated in FIG. 1 .
  • the flow radially outside the hub ramp 10 at the fan blade 8 is substantially not disrupted.
  • a relatively stable and turbulence-free flow is generated below the hub ramp 10 , as indicated by arrows P.
  • the elongation of the blade trailing edge in the radially inner region 7 b that is to say the enlargement of the vane width, yields a significant increase in volume flow rate and in efficiency, and a noise reduction.
  • vane width or “blade width” are to be understood to mean the distance between the leading edge and trailing edge or the length of the chord of the vane or of the blade.
  • the depth of the vane is to be understood to mean the projection of the vane width in the circumferential direction.
  • FIG. 3 shows a detail of an axial fan 11 according to the invention in a three-dimensional illustration.
  • the illustration shows a hub ring 12 on which fan blades 13 , 14 , are fastened, that is to say integrally formed by injection molding.
  • the fan blades 13 , 14 , 15 have, on their pressure side in each case, hub ramps 13 a , 14 a , 15 a which rise counter to the direction of rotation indicated by an arrow D.
  • the hub ramps 13 a , 14 a , 15 a are connected on their underside to the hub ring by ribs.
  • the fan blades 13 , 14 , 15 each have trailing edges 16 , 17 , 18 , also referred to as flow-off edges 16 , 17 , 18 , which run substantially rectilinearly from radially outside to radially inside.
  • the downstream end of the hub ramps 13 a , 14 a , 15 a divides the trailing edges 16 , 17 , 18 into two portions, specifically radially outer portions or regions 16 a , 17 a , 18 a and radially inner portions or regions 16 b , 17 b , 18 b .
  • a fan structure is thus created which is optimized with regard to strength and which is capable of absorbing the forces, in particular centrifugal forces, that arise during the operation of the fan.
  • the suction sides of the fan blades have fin-like stabilizers 19 .
  • FIG. 4 shows a radial section (section in a radial plane) through the hub ring 12 of the axial fan 11 , wherein the same reference signs as those in FIG. 3 are used for identical parts.
  • the air flow direction is indicated by an arrow L.
  • the hub ring 12 has an axial extent a and the fan blade 14 has a depth t which—as mentioned above—is defined as a projection of the vane width in the circumferential direction. From the diagrammatic illustration, it is clear that the blade depth t is considerably greater than the axial extent a of the hub ring 12 . In a preferred exemplary embodiment, the blade depth t is approximately twice as large as the axial extent a of the hub ring 12 .
  • the trailing edge 17 of the fan blade 14 runs substantially rectilinearly in the radial direction, wherein the innermost portion of the trailing edge 17 is rounded.
  • the hub ramp appears as a sectioned surface denoted by 14 a.
  • FIG. 5 shows a view of an incompletely illustrated axial fan 20 , viewed in the direction of its front side or the suction sides of the fan blades 21 , on which air-guiding elements 22 are arranged.
  • the axial fan 20 comprises a metallic carrier ring 23 which is connected at one side to the plastic hub of the axial fan 20 and which can be fastened at the other side to a clutch (not illustrated), preferably a liquid friction clutch.
  • the fan blades denoted by the reference signs 21 a , 21 b , 21 c have been cut away in the section plane VI-VI.
  • FIG. 6 is a sectional illustration of the axial fan as per section plane VI-VI.
  • the illustration shows different sectioned surfaces of the fan blades 21 a , 21 b , 21 c .
  • the fan blades 21 a , 21 b , 21 c are sectioned in different planes in relation to their radial central line, wherein the section plane for the central blade 21 b can be regarded as a tangential section and is situated radially within the hub ramp.
  • the sectioned surface of the blade 21 c in FIG. 6 is situated above the hub ramp, which in this case is denoted by the reference sign 24 and is not visible in FIG.
  • the sectioned surface of the middle fan blade 21 b shows the vane width b, that is to say the distance between the leading and trailing edges.
  • the projection of the vane width b in the circumferential direction yields the vane depth t (not indicated) which is approximately constant over the entire radial range, specifically in the case of an approximately rectilinearly running blade trailing edge.
  • the fan blades may be kinked in the direction of their blade roots and for the angled, inner region to be drawn downward onto the hub ring.
  • the angled formation yields a vane-like form of the fan blade and a transition, which is optimized in terms of stresses, between the fan blade and hub ring.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/991,188 2010-12-01 2011-12-01 Axial fan Abandoned US20130323072A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102010062301.6 2010-12-01
DE102010062301A DE102010062301A1 (de) 2010-12-01 2010-12-01 Axiallüfter
PCT/EP2011/071579 WO2012072779A1 (de) 2010-12-01 2011-12-01 Axiallüfter

Publications (1)

Publication Number Publication Date
US20130323072A1 true US20130323072A1 (en) 2013-12-05

Family

ID=45065912

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/991,188 Abandoned US20130323072A1 (en) 2010-12-01 2011-12-01 Axial fan

Country Status (9)

Country Link
US (1) US20130323072A1 (de)
EP (1) EP2646695B1 (de)
JP (1) JP6245437B2 (de)
KR (1) KR20140002690A (de)
CN (1) CN103270311B (de)
BR (1) BR112013015751B1 (de)
DE (1) DE102010062301A1 (de)
RU (1) RU2608800C2 (de)
WO (1) WO2012072779A1 (de)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9869190B2 (en) 2014-05-30 2018-01-16 General Electric Company Variable-pitch rotor with remote counterweights
USD809121S1 (en) * 2016-04-26 2018-01-30 Parker-Hannifin Corporation Fan with integral airflow guide
US10072510B2 (en) 2014-11-21 2018-09-11 General Electric Company Variable pitch fan for gas turbine engine and method of assembling the same
US10100653B2 (en) 2015-10-08 2018-10-16 General Electric Company Variable pitch fan blade retention system
US20190120246A1 (en) * 2017-04-21 2019-04-25 Evapco, Inc. Cooling towers axial fan in a hollowed disc/ring configuration
US10280935B2 (en) * 2016-04-26 2019-05-07 Parker-Hannifin Corporation Integral fan and airflow guide
USD860427S1 (en) 2017-09-18 2019-09-17 Horton, Inc. Ring fan
US10508652B2 (en) 2014-09-22 2019-12-17 Mahle International Gmbh Axial fan for conveying cooling air, in particular for an internal combustion engine of a motor vehicle
US20210115939A1 (en) * 2018-04-12 2021-04-22 Resource West, Inc. Impeller for ambient water evaporators, and related system and method
US11313380B2 (en) * 2017-06-12 2022-04-26 Valeo Systemes Thermiques Motor vehicle fan
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11767761B2 (en) 2018-08-02 2023-09-26 Horton, Inc. Low solidity vehicle cooling fan
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system

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FR3014150B1 (fr) * 2013-11-29 2018-03-02 Safran Aircraft Engines Soufflante, en particulier pour une turbomachine
FR3014151B1 (fr) * 2013-11-29 2015-12-04 Snecma Soufflante, en particulier pour une turbomachine
DE102014204043A1 (de) * 2014-03-05 2015-09-10 MAHLE Behr GmbH & Co. KG Lüfterrad eines Axiallüfters
CN103953567A (zh) * 2014-05-16 2014-07-30 佟宝义 一种用于大中型柴油发动机散热器的碳纤维风扇叶片
EP3354904B1 (de) 2015-04-08 2020-09-16 Horton, Inc. Lüfterflügel mit oberflächenmerkmalen
CN110892159B (zh) * 2017-04-21 2022-05-03 艾威普科公司 空心盘/环形结构的冷却塔轴流风机
CN110107530B (zh) * 2019-06-19 2023-12-29 苏州睿昕汽车配件有限公司 多段式导流轮毂结构风扇
CN111927825B (zh) * 2020-07-24 2022-06-28 东风马勒热系统有限公司 开口风扇
DE102022119333A1 (de) 2022-08-02 2024-02-08 Technische Universität Darmstadt, Körperschaft des öffentlichen Rechts Strömungsmaschine mit einer verstellbaren Axiallaufradanordnung
CN115596706A (zh) * 2022-10-31 2023-01-13 东风马勒热系统有限公司（Cn） 轴流风扇

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US6692231B1 (en) * 2001-02-28 2004-02-17 General Shelters Of Texas S.B., Ltd. Molded fan having repositionable blades
US20070031250A1 (en) * 2005-08-03 2007-02-08 Mitsubishi Heavy Industries, Ltd. Shroud and rotary vane wheel of propeller fan and propeller fan
US20070122287A1 (en) * 2005-11-29 2007-05-31 Pennington Donald R Fan blade assembly
US20100092297A1 (en) * 2007-05-10 2010-04-15 Borgwamer Inc. Synergistic blade and hub structure for cooling fans

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Publication number Priority date Publication date Assignee Title
US6010305A (en) * 1997-03-14 2000-01-04 Behr Gmbh & Co. Axial-flow fan for the radiator of an internal combustion engine
US6692231B1 (en) * 2001-02-28 2004-02-17 General Shelters Of Texas S.B., Ltd. Molded fan having repositionable blades
US20070031250A1 (en) * 2005-08-03 2007-02-08 Mitsubishi Heavy Industries, Ltd. Shroud and rotary vane wheel of propeller fan and propeller fan
US20070122287A1 (en) * 2005-11-29 2007-05-31 Pennington Donald R Fan blade assembly
US20100092297A1 (en) * 2007-05-10 2010-04-15 Borgwamer Inc. Synergistic blade and hub structure for cooling fans

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9869190B2 (en) 2014-05-30 2018-01-16 General Electric Company Variable-pitch rotor with remote counterweights
US10508652B2 (en) 2014-09-22 2019-12-17 Mahle International Gmbh Axial fan for conveying cooling air, in particular for an internal combustion engine of a motor vehicle
US10072510B2 (en) 2014-11-21 2018-09-11 General Electric Company Variable pitch fan for gas turbine engine and method of assembling the same
US10100653B2 (en) 2015-10-08 2018-10-16 General Electric Company Variable pitch fan blade retention system
USD914865S1 (en) 2016-04-26 2021-03-30 Parker-Hannifin Corporation Fan with integral airflow guide
US10280935B2 (en) * 2016-04-26 2019-05-07 Parker-Hannifin Corporation Integral fan and airflow guide
USD809121S1 (en) * 2016-04-26 2018-01-30 Parker-Hannifin Corporation Fan with integral airflow guide
US20190120246A1 (en) * 2017-04-21 2019-04-25 Evapco, Inc. Cooling towers axial fan in a hollowed disc/ring configuration
US10808717B2 (en) * 2017-04-21 2020-10-20 Evapco, Inc. Cooling towers axial fan in a hollowed disc/ring configuration
US11313380B2 (en) * 2017-06-12 2022-04-26 Valeo Systemes Thermiques Motor vehicle fan
USD860427S1 (en) 2017-09-18 2019-09-17 Horton, Inc. Ring fan
US20210115939A1 (en) * 2018-04-12 2021-04-22 Resource West, Inc. Impeller for ambient water evaporators, and related system and method
US11767761B2 (en) 2018-08-02 2023-09-26 Horton, Inc. Low solidity vehicle cooling fan
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system

Also Published As

Publication number Publication date
EP2646695B1 (de) 2017-07-12
RU2608800C2 (ru) 2017-01-24
JP6245437B2 (ja) 2017-12-13
BR112013015751B1 (pt) 2020-10-20
CN103270311A (zh) 2013-08-28
KR20140002690A (ko) 2014-01-08
EP2646695A1 (de) 2013-10-09
WO2012072779A1 (de) 2012-06-07
JP2013544337A (ja) 2013-12-12
RU2013129920A (ru) 2015-01-10
CN103270311B (zh) 2017-05-31
BR112013015751A2 (pt) 2016-09-27
DE102010062301A1 (de) 2012-06-06

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