CN101044324A - Fan stator - Google Patents

Fan stator Download PDF

Info

Publication number
CN101044324A
CN101044324A CNA2005800361761A CN200580036176A CN101044324A CN 101044324 A CN101044324 A CN 101044324A CN A2005800361761 A CNA2005800361761 A CN A2005800361761A CN 200580036176 A CN200580036176 A CN 200580036176A CN 101044324 A CN101044324 A CN 101044324A
Authority
CN
China
Prior art keywords
fan
leading edge
aerofoil profile
equipment
hub
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
CNA2005800361761A
Other languages
Chinese (zh)
Other versions
CN101044324B (en
Inventor
G·斯坦利
K·沙
B·布罗伊利
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.)
Intel Corp
Original Assignee
Intel Corp
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 Intel Corp filed Critical Intel Corp
Publication of CN101044324A publication Critical patent/CN101044324A/en
Application granted granted Critical
Publication of CN101044324B publication Critical patent/CN101044324B/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes

Landscapes

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

Abstract

According to some embodiments, an apparatus includes a housing (10), a hub (20), and a plurality of airfoils (30), each of the plurality of airfoils having a leading edge, a trailing edge, a first end, and a second end, wherein the first end of each of the plurality of airfoils (30) is fixedly coupled to the hub and wherein the second end of each of the plurality of airfoils is fixedly coupled to the housing (10).

Description

Fan stator
Background technique
Electronic unit can produce the power of heat to dissipate and to be received.These functions of components can be damaged or slacken to this heat.Adopted various cooling systems with cooling dynamic dissipation parts, these cooling systems can comprise processor, chip set, voltage regulator components and other parts.Some cooling systems adopt fan to discharge the air that is heated from the casing that includes the dynamic dissipation parts.Other cooling system adopts fan to produce air-flow and air-flow is guided so that the cooling to it to be provided towards the dynamic dissipation parts.
Description of drawings
Fig. 1 is the representative side view that partly cuts according to some embodiments' system.
Fig. 2 is preceding (import) perspective exploded view according to some embodiments' system.
Fig. 3 is preceding (import) perspective view according to some embodiments' system.
Fig. 4 is back (outlet) perspective view according to some embodiments' system.
Fig. 5 is the improved plotted curve that is shown with according to some embodiments' system condition point.
Fig. 6 is the plotted curve that is shown with according to some embodiments' air velocity vector transformation.
Fig. 7 is preceding (import) perspective view according to some embodiments' thermal module.
Fig. 8 is the perspective view according to some embodiments' system.
Embodiment
Fig. 1 to 4 shows the various views of cooling system.Especially, Fig. 1 cuts side view for representational part, and Fig. 2 is a perspective exploded view, and Fig. 3 is preceding (import) perspective view, and Fig. 4 is back (outlet) perspective view according to some embodiments' system 1.System 1 can comprise a kind of system, with by air being directed to itself and cooling unit.System 1 can engage use with suitable application, and these suitable application comprise the cooling electronic device that singly is not limited to be encapsulated in the casing.
System 1 comprises shell 10 and hub 20.A plurality of stator vanes 30 are connected in shell 10 and hub 20.According to some embodiments, each stator vane 30 is the aerofoil profile (airfoil) that comprises leading edge, trailing edge, first end and second end.First end of this each aerofoil profile is fixedly connected to hub 20, and this second end is fixedly connected to shell 10.
Shell 10, hub 20 and blade 30 can be formed by any material that is suitable for its use, include but not limited to plastics, resin, polymer and metal.The physical size of shell 10, hub 20 and blade 30 also can change according to the regulation that specific application and/or system 1 attempt to follow.Shell 10, according to some embodiments, hub 20 and blade 30 comprise a single body unit.Such unit can adopt injection molding technology production.
According to some embodiments, fan 40 is engaged to hub 20.Shown in the figure of institute, motor 60 can be arranged in the fan 40, and by hub 20 supportings.The blade 50 of motor 60 drive fan 40 is to be sent to air the leading edge of blade 30.As shown in Figure 1, because the rotation of blade 50 is in pressure P 0Input air 70 admitted and quickened.This air that is accelerated presents static pressure P 1The tangential velocity vector, axial-velocity vector and the radial velocity vector that comprise the position of design, rotating speed that depends on fan 40 at least and the air that is accelerated discharge fan blade 50.
Blade 30 is admitted and is accelerated air.According to some embodiments, for the given axial velocity from blade 30 leading edges to blade 30 trailing edges, blade 30 increases from P 1To P 2Static air pressure power.The air of discharge blade 30 trailing edges is denoted as air 80 in Fig. 1.
For particular fan speed, air 80 flow and/or pressure can be greater than the situation that will be provided by fan 40 when the on-bladed 30.For given casing, Fig. 5 shows the operating point O of the system that only comprises fan 40 1Operating point O with system 1 2As shown, operating point O 2For being associated with than operating point O 1Big big flowing and big static pressure.Therefore, system 1 can be to cool off components downstream than independent fan 40 higher efficient.
The leading edge of blade 30 is admitted the air that is accelerated from fan 40.In certain embodiments, the leading edge of at least one blade 30 has defined first bending, and vane trailing edge has defined second bending.The example of this first crooked and second bending is surrounded with the dotted line 32 of the dotted line 31 of Fig. 2 and Fig. 4 respectively and is represented.This bending can reduce the radial velocity vector and increase the static pressure of import to the air of being admitted of outlet.According to some embodiments, first bending of this at least one blade 30 is arranged to the trailing edge of given radius perpendicular to the fan blade 50 of this at least one given radius.Should after layout can reduce the interactional gross area between any set point place's wheel blade and the blade in time, therefore, compare selectable other layout and reduced noise.
As mentioned above, blade 30 can comprise the aerofoil profile according to some embodiments.If the air that is accelerated from fan 40 meets with the suitable angle of attack and the leading edge of blade 30, this air foil shape can produce lift so, is transformed into pressure to help the tangential velocity with at least some air of admitting.In certain embodiments, blade is followed airfoil geometry configuration 93xx, 94xx, 83xx or the 84xx of NACA (NACA) four figures series.The example of this geometrical configuration comprises airfoil geometry configuration 9304,9404,8304 or 8404.According to these embodiments, blade be defined as maximum camber (camber) for length of blade 8% or more than.
Fig. 6 shows at least in part because the distortion of the air velocity vector of admitting due to the air foil shape of above-mentioned bending and blade 30.The blade 50 of fan 40 is shown the cross section in the drawings.Blade 50 is admitted and is in pressure P 0Air 70 and rotate with generation and be in big pressure P 1Under air.The air that this produced is represented with vector Figure 90.As shown, the velocity vector V of air TotaloComprise axial component V Axialo, tangential (or " sense of rotation ") component V TangentialoWith radial component V perpendicular to the page Radialo
Then, air that is accelerated and blade 30 meet, and also illustrate with the cross section.The air 80 of discharging from the trailing edge of blade 30 presents from P 1To P 2The situation that increases of static pressure, and axial velocity component V Axial1Remain and be substantially equal to axial component V AxialoYet, tangential speed component V Tangential1With radial component V RadialoThe size of the two is all less than the respective component V of the air of being admitted by the leading edge of blade 30 TangentialoAnd V Radial0
The angle of air shock blade 30 leading edges that are accelerated can reduce along with the distance of leaving hub 20.Therefore, one or more blades 30 can be by " distortion " becomes to make and be somebody's turn to do " that blade angle " changes along with radius.When adopting this distortion, first end of one of these one or more blades 30 not with the second end coplane of this this one or more blades 30.This blade angle is measured by connect a line (being called string) between the leading edge of blade and trailing edge, and wherein this line intersects with horizontal plane when this hub 15 is horizontally disposed with.
This blade angle can be used as the function of radius and increases.In certain embodiments, the blade angle of this at least one blade 30 is 55 degree at hub 20 places, and is 75 degree at shell 10 places.It is 43 degree at hub 20 places that some embodiments can provide the blade angle of at least one blade 30, and is 73 degree at shell 10 places.
According to some embodiments, the quantity of blade 50 is N, and the quantity of blade 30 is not the integral multiple of N.Arrange that than other this layout can provide the acoustic interference of increase and therefore reduce operational noise of system 1.In a kind of specific example, the quantity of blade equals N+1.Arrange that than other for the air-flow of specified rate, some embodiments also can be by allowing fan 40 with lower rotating speed operation reduction noise.
Fig. 7 is for adopting the perspective view of the thermal module 200 of system 1 according to some embodiments.Thermal module 200 also comprises shell 210, electronic component 300 and radiator 310.The relevant portion of shell 210 is drawn into transparent, with permission electronic component 300 and radiator 310 is observed.According to some embodiments, thermal module 200 adopts the air 80 that is produced by system 1 with cooling radiator 310.
Electronic component 300 can comprise any radiating component, and these radiating components include but not limited to intergrated circuit (as microprocessor, chip set) and power switch component.Radiator 310 can comprise any material (as copper, aluminium) and can comprise any cooling unit of currently or later knowing.As shown, radiator 310 comprises that heat conducting and radiating sheet 315 will be loosing in surrounding atmosphere from the heat of electronic component 300.
Than other system, the axial velocity component of above-mentioned air 80 can reduce the rotation loss of radiating fin 315 edges with respect to the increase of its tangential speed component.Can cause more effective cooling to member 300.In addition, for the fan 40 of given speed, the static air pressure power of discharging module 200 can be greater than previous available.
Fig. 8 is the perspective view according to some embodiments' system 400.System 400 can comprise the desktop computer platform.System 400 has adopted the air 80 that is produced by thermal module 200 to cool off a plurality of system units.
System 400 comprises module 200, casing 410 and motherboard 420.Casing 410 is shown the transparent parts of system 400 being observed with permission.Except the vertical extension at 420 times method, systems 1 of motherboard, the module 200 of Fig. 7 can be identical with the module 200 of Fig. 6.The part that this vertical extension can allow air 80 advances to volume between motherboard 420 and casing 410 from blade 30.
Various parts can be installed to motherboard 420, these parts comprise store controller Line concentrator 430, I/O controller Line concentrator 440, and plug-in type additional card 450,452,454 stores card 460 and I/O interface 470.System 400 also comprises removable media drive 480, hard disk drive 490 and power source 500.Any other system unit and structure can be used in combination with some embodiments.
One or above parts can be used for cooling system 400 from the air 80 of thermal module.In some instances, air 80 can flow above the heat-dissipating part that is installed on the drawing plug-in type additional card 450, flows in the top of Line concentrator 430,440, and can discharge by the rear board (figure does not show) of casing 410.Flow with respect to tangential, can reduce by the loss due to the radiator 310, therefore make more air pressure can be used for cooling off other parts from the axial flow of the increase of the air 80 of system 1.If do not need extra air pressure, system 1 can move with lower fan speed and sound level, with the air-flow of transmission with the conventional system same amount that moves with higher fan speed and sound level.
Several embodiment as described herein only is intended to example.The embodiment of element described herein can comprise any current or form of after this knowing.Therefore, those skilled in the art will recognize from this description and can adopt other embodiment who carries out various modifications and changes.

Claims (30)

1. equipment comprises:
Shell;
Hub; And
A plurality of aerofoil profiles, each these a plurality of aerofoil profile all has leading edge, trailing edge, first end, and second end,
Wherein first end of each these a plurality of aerofoil profile is fixedly connected to this hub, and wherein second end of each these a plurality of aerofoil profile is fixedly connected to this shell.
2. according to the equipment of claim 1, wherein the maximum camber of at least one a plurality of aerofoil profile be these at least one a plurality of aerofoil profiles length 8% or more than.
3. according to the equipment of claim 2, wherein each these a plurality of aerofoil profile is followed NACA93xx, 94xx, and 83xx, or 84xx airfoil geometry configuration is at least a.
4. according to the equipment of claim 1, wherein the leading edge of at least one a plurality of aerofoil profile has defined first bending to reduce the tangential velocity vector and to increase the static air pressure vector of force that receives at the leading edge place.
5. according to the equipment of claim 4, also comprise:
Fan, air is sent to the leading edge of these a plurality of aerofoil profiles, this fan comprises a plurality of fan blade,
Wherein this first bending is arranged to the trailing edge of given radius perpendicular to the fan blade of at least one these a plurality of given radius.
6. according to the equipment of claim 1, wherein the leading edge of at least one these a plurality of aerofoil profile has defined first bending to reduce the radial velocity vector and to increase the static air pressure vector of force that receives at the leading edge place.
7. according to the equipment of claim 6, also comprise:
Fan, to transmit the leading edge of air to a plurality of aerofoil profiles, this fan comprises a plurality of fan blade,
Wherein this first bending is arranged to be substantially perpendicular to given radius the trailing edge of the fan blade of at least one these a plurality of given radius.
8. according to the equipment of claim 1, wherein this first end not with this second end coplane.
9. according to the equipment of claim 8, wherein the blade angle of at least one a plurality of aerofoil profile is 55 degree and be 75 degree at this shell place at this hub place.
10. according to the equipment of claim 8, wherein the blade angle of at least one a plurality of aerofoil profile is 43 degree and be 73 degree at this shell place at this hub place.
11. according to the equipment of claim 8, wherein this blade angle increases along with the distance of leaving this hub.
12. according to the equipment of claim 8, wherein the leading edge of at least one a plurality of aerofoil profile has defined first bending, to reduce radial velocity vector and tangential velocity vector and to increase the static air pressure vector of force that receives at the leading edge place.
13. the equipment according to claim 1 also comprises:
Fan, to transmit the leading edge of air to a plurality of aerofoil profiles, this fan comprises N fan blade, wherein this equipment only comprises M aerofoil profile, and
Wherein M is not the integral multiple of N.
14. the equipment according to claim 13 also comprises:
Be arranged in this fan and join the fan motor of this hub to, wherein this fan joins this fan motor to.
15. according to the equipment of claim 13, wherein M equals N+1.
16. a system comprises:
Shell;
Hub;
A plurality of aerofoil profiles, each these a plurality of aerofoil profile has leading edge, trailing edge, first end and second end;
Microprocessor; And
Be connected to the aerobronze composite heat sink of microprocessor, this radiator is used to hold the air from these a plurality of airfoil trailing edges, wherein first end of each these a plurality of aerofoil profile be fixedly connected to this hub and wherein second end of each these a plurality of aerofoil profile be fixedly connected to this shell.
17. according to the system of claim 16, wherein the maximum camber of at least one a plurality of aerofoil profile for the length of at least one these a plurality of aerofoil profile 8% or more than.
18. according to the system of claim 17, wherein each these a plurality of aerofoil profile is followed NACA93xx, 94xx, and 83xx, or 84xx airfoil geometry configuration is at least a.
19. according to the system of claim 16, wherein the leading edge of at least one a plurality of aerofoil profile has defined first bending to reduce the tangential velocity vector and to increase the static air pressure vector of force that receives at the leading edge place.
20. the system according to claim 19 also comprises:
Fan, to transmit the leading edge of air to a plurality of aerofoil profiles, this fan comprises a plurality of fan blade,
Wherein this first bending is arranged to the trailing edge of given radius perpendicular to the fan blade of at least one these a plurality of given radius.
21. according to the system of claim 16, wherein the leading edge of at least one these a plurality of aerofoil profile has defined first bending, to reduce the radial velocity vector and to increase the static air pressure vector of force that receives at the leading edge place.
22. the system according to claim 21 also comprises:
Fan, to transmit the leading edge of air to a plurality of aerofoil profiles, this fan comprises a plurality of fan blade,
Wherein this first bending is arranged to be substantially perpendicular to given radius the trailing edge of the fan blade of at least one these a plurality of given radius.
23. according to the system of claim 16, wherein this first end not with this second end coplane.
24. according to the system of claim 23, wherein the blade angle of at least one a plurality of aerofoil profile is 55 degree and be 75 degree at this shell place at this hub place.
25. according to the system of claim 23, wherein the blade angle of at least one a plurality of aerofoil profile is 43 degree and be 73 degree at this shell place at this hub place.
26. according to the system of claim 23, wherein this blade angle increases along with the distance of leaving this hub.
27. according to the system of claim 23, wherein the leading edge of at least one a plurality of aerofoil profile has defined first bending, to reduce radial velocity vector and tangential velocity vector and to increase the static air pressure vector of force that receives at the leading edge place.
28. the system according to claim 16 also comprises:
Fan, to transmit the leading edge of air to a plurality of aerofoil profiles, this fan only comprises N fan blade,
Wherein this equipment only comprises M aerofoil profile, and
Wherein M is not the integral multiple of N.
29. the system according to claim 28 also comprises:
Be arranged in this fan and be connected to the fan motor of this hub,
Wherein this fan joins this fan motor to.
30. according to the system of claim 28, wherein M equals N+1.
CN2005800361761A 2004-10-29 2005-10-27 Fan stator Expired - Fee Related CN101044324B (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US10/976,634 2004-10-29
US10/976,634 US20060093476A1 (en) 2004-10-29 2004-10-29 Fan stator
PCT/US2005/039315 WO2006050285A1 (en) 2004-10-29 2005-10-27 Fan stator

Publications (2)

Publication Number Publication Date
CN101044324A true CN101044324A (en) 2007-09-26
CN101044324B CN101044324B (en) 2012-06-13

Family

ID=35883470

Family Applications (1)

Application Number Title Priority Date Filing Date
CN2005800361761A Expired - Fee Related CN101044324B (en) 2004-10-29 2005-10-27 Fan stator

Country Status (5)

Country Link
US (1) US20060093476A1 (en)
CN (1) CN101044324B (en)
DE (1) DE112005002393T5 (en)
TW (1) TWI312267B (en)
WO (1) WO2006050285A1 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140251238A1 (en) * 2014-05-19 2014-09-11 Perkins Engines Company Limited Heat exchanging system for internal combustion engine
TWI578670B (en) * 2015-05-20 2017-04-11 Visionary Dynamics Co Ltd A hub motor with a guide seat
US10989221B2 (en) * 2016-06-29 2021-04-27 Quanta Computer Inc. Cooling system for streamlined airflow
US11884128B2 (en) 2017-12-18 2024-01-30 Carrier Corporation Fan stator construction to minimize axial depth
US10451447B2 (en) 2018-01-04 2019-10-22 Mitsubishi Electric Research Laboratories, Inc. Polarization-dependent position encoder
DE102019110934A1 (en) * 2019-04-29 2020-10-29 Ebm-Papst Mulfingen Gmbh & Co. Kg Guide device for an axial fan

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2191341A (en) * 1937-02-26 1940-02-20 Jeffrey Mfg Co Ventilator
DE3605086A1 (en) * 1986-02-18 1987-08-27 Rhein Flugzeugbau Gmbh TRAINING OF COMPONENTS LOCATED INTO THE INFLOW TO AIR SCREWS, COVER SCREWS AND / OR FANS TO REDUCE THE ADDITIONAL NOISE YOU MAKE AND TO REDUCE THE ALTERNATE LOAD ON THE PROPELLER BLOWERS
EP0458880A4 (en) * 1989-02-14 1992-02-12 Airflow Research & Manufacturing Corp. Centrifugal fan with airfoil vanes in annular volute envelope
US6045327A (en) * 1998-05-04 2000-04-04 Carrier Corporation Axial flow fan assembly and one-piece housing for axial flow fan assembly
US6206635B1 (en) * 1998-12-07 2001-03-27 Valeo, Inc. Fan stator
US6199624B1 (en) * 1999-04-30 2001-03-13 Molex Incorporated Folded fin heat sink and a heat exchanger employing the heat sink
US20020094271A1 (en) * 2001-01-16 2002-07-18 Yeuan Jian J. Axial flow fan structure
TW568508U (en) * 2001-03-27 2003-12-21 Delta Electronics Inc Fan with good heat dissipation
US20030007867A1 (en) * 2001-07-05 2003-01-09 Enlight Corporation CPU cooling structure with a ventilation hood
US6749043B2 (en) * 2001-10-22 2004-06-15 General Electric Company Locomotive brake resistor cooling apparatus

Also Published As

Publication number Publication date
TW200628059A (en) 2006-08-01
DE112005002393T5 (en) 2007-09-20
WO2006050285A1 (en) 2006-05-11
US20060093476A1 (en) 2006-05-04
CN101044324B (en) 2012-06-13
TWI312267B (en) 2009-07-11

Similar Documents

Publication Publication Date Title
EP1616102B1 (en) High performance axial fan
CN101044324B (en) Fan stator
WO1999035404A1 (en) Air supplying device
US7802969B2 (en) Fan and impeller thereof
CN1966993A (en) Fan blade unit for centrifugal fan
CN110159564B (en) Axial flow fan with low specific speed
US7959413B2 (en) Fan and impeller thereof
US20060237169A1 (en) Aerodynamically enhanced cooling fan
CN1900528A (en) Cooling fan and shroud with modified profiles
CN1932303A (en) Fan frame with flow guiding stator blade and fan
US20080292453A1 (en) Fan and frame thereof
CN200982304Y (en) Supercharging fan module
CN1932304A (en) Fan frame with flow-guiding stator blade and fan
CN1201090C (en) Blower and air conditioner with the same
CN2733049Y (en) Radiating fan applied in radiator
CN1309065C (en) Radiation device for electronic element
CN1746511A (en) Fan
CN100343784C (en) Fan vane unit of centrifugal fan
CN2670644Y (en) Serial fan assembled mechanism
CN1238640C (en) Air-supply apparatus with multistage vane
CN221195498U (en) Fan blade structure
CN2543204Y (en) Cooling fan
CN2544330Y (en) Heat sink structure for electronic device
CN1940309A (en) Wind fluid pressure controller
CN2553151Y (en) Horizontal convection fan structure

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant
C17 Cessation of patent right
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20120613

Termination date: 20131027