CN104696278A - Impeller and air blower - Google Patents
Impeller and air blower Download PDFInfo
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- CN104696278A CN104696278A CN201410721354.5A CN201410721354A CN104696278A CN 104696278 A CN104696278 A CN 104696278A CN 201410721354 A CN201410721354 A CN 201410721354A CN 104696278 A CN104696278 A CN 104696278A
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- Prior art keywords
- aileron
- distance
- blade
- impeller
- spin axis
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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
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides an impeller and an air blower. An axial impeller comprises a plurality of blades, and a first auxiliary wing and a second auxiliary wing which protrude from the blade surfaces of the blades and extend on the periphery direction. The first auxiliary wing is configured on the outer side of the radial direction of the second auxiliary wing, and is at least partially overlapped on a radially direction with the second auxiliary wing. The distance difference of the distance between the first front end on the forefront of a rotation direction of the first auxiliary wing and a rotation axis, and the distance between the second front end on the forefront of the rotation direction of the second auxiliary wing and the rotation axis, is larger than the distance difference of the distance between the first rear end of the hindmost of the rotation direction of the first auxiliary wing and the rotation axis, and the distance between the second rear end of the hindmost of the rotation direction of the second auxiliary wing and the rotation axis. Thus, when the impeller rotates, a part of axial airflow generated by the blades is concentrated between the two auxiliary wings, so that the airflow generates a large wind speed part. The result is that the large wind speed part absorbs gas on the outer side, and airflow volume facing the axial front side is increased.
Description
Technical field
The present invention relates to a kind of impeller and gas fan of axial flow.
Background technique
In the past, the known rotation by blade produces the gas fan of the axial flow such as fan, circulator, diffuser of air-flow.Further, except these gas fans for the purpose of air-conditioning, also known automobile, OA equipment etc., the gas fan of axial flow for cooling the various device such as motor and motor component is equipped on.About the gas fan of axial flow in the past, such as, described in Japan's public table No. 2011-513618, patent gazette.
In recent years, in the gas fan for the purpose of air-conditioning, along with the miniaturization of dwellings and office etc., also gas fan is proposed to the requirement of miniaturization.On the other hand, in the gas fan of device cooling object, due to the heating value increase etc. improved along with the performance of each device, need to improve air output while the volume not increasing gas fan.
In the gas fan in the past such as the cooling fan described in Japan's public table No. 2011-513618, patent gazette, not there is the mechanism of the air output in order to improve the wind that blade produces.Therefore, in gas fan in the past, the air quantity of the wind produced can only be determined by the shape of blade and area.But, if do not increase the volume of gas fan and make air output improve to the shape design of blade body, likely produce the problem of rigidity and resistance etc.Therefore, a kind of technology improving air output while the shape of little amplitude change blade body is needed.
Summary of the invention
The object of this invention is to provide a kind of impeller and the gas fan that can improve air output when not changing the shape of blade body.
One mode of execution of the example of the application, provides a kind of impeller of the axial flow rotated centered by spin axis, comprising: the multiple blades circumferentially arranged; And first aileron and the second aileron, described first aileron and described second aileron are outstanding and extend in the circumferential from the blade face of described blade; First aileron and the second aileron are configured in the pressurized plane side of blade and at least one party of suction surface side; First aileron is configured in the radial outside of the second aileron, and at least local radial is overlapping with the second aileron; Distance from first front end being positioned at sense of rotation forefront of the first aileron to described spin axis and the difference of the second front end to the distance of described spin axis being positioned at sense of rotation forefront from the second aileron, than the distance from first rear end being positioned at sense of rotation rearmost of the first aileron to described spin axis with large to the difference of the distance of described spin axis from second rear end being positioned at sense of rotation rearmost of the second aileron.
Preferably, identical with from the first rear end to the distance of spin axis from the first front end to the distance of spin axis or larger than the distance from the first rear end to spin axis.
Preferably, identical with from the second rear end to the distance of spin axis from the second front end to the distance of spin axis or less than the distance from the second rear end to spin axis.
Preferably, the first outer edge overlapping in the axial direction with the blade outer edge of the radial outside of blade at least partially of the radial outside of the first aileron.
Preferably, distance from the second inner end of the inner side of the radial direction the second aileron to spin axis and the difference of the blade outer end portion from the outermost radial outside blade to the distance of spin axis, than also little with the half of the difference from blade outer end portion to the distance of described spin axis to the distance of spin axis from the blade inner end of the inner side of the radial direction on blade.
Preferably, the first aileron and the second aileron are along with reducing gradually away from the blade face of blade vertically.
Preferably, sense of rotation rear is leaned on than the leading edge of blade in the first front end of the first aileron and the second front end of the second aileron.
Preferably, sense of rotation front is leaned on than the trailing edge of blade in the first rear end of the first aileron and the second rear end of the second aileron.
Preferably, sense of rotation rear is leaned on than the trailing edge of blade in the first rear end of the first aileron and the second rear end of the second aileron.
Preferably, axial opposite side is leaned on than the end of the axial side of blade in the end of the axial side of the first aileron, axial side is leaned on than the end of the axial opposite side of blade in the end of the axial opposite side of the first aileron, axial opposite side is leaned on than the end of the axial side of blade in the end of the axial side of the second aileron, and axial side is leaned on than the end of the axial opposite side of blade in the end of the axial opposite side of the second aileron.
Preferably, the part comprising the first front end of the first aileron and the part comprising the second front end of the second aileron have acerous curved surface.
Preferably, the allocation position of the first aileron can be switched between first orientation and second orientation, when being in first orientation, the first front end is to Distance geometry first rear end of spin axis to the difference of the distance of spin axis, different to the difference of the distance of spin axis to Distance geometry first rear end of spin axis from the first front end when being in second orientation.
Preferably, the allocation position of the second aileron can be switched between third party position and the 4th orientation, when being in third party position, the second front end is to Distance geometry second rear end of spin axis to the difference of the distance of spin axis, different to the difference of the distance of spin axis to Distance geometry second rear end of spin axis from the second front end when being in the 4th orientation.
Preferably, impeller is that resin is made, and shaping by molding and forming.
A kind of gas fan, comprising: the motor with the rotary part rotated centered by described spin axis; And the above-mentioned impeller together to rotate with described rotary part.
According to a mode of execution of the application's example, the distance of two ailerons narrows from sense of rotation front towards rear.By such structure, the air-flow of the axis produced by blade is concentrated between two ailerons, thus in this air-flow, produces the large part of wind speed.The gas of surrounding sucks due to Coanda effect by the large part of this wind speed, thus can increase towards the air quantity of the air-flow of axial face side.
Accompanying drawing explanation
Fig. 1 is the side view of the fan involved by the first mode of execution.
Fig. 2 is the stereogram of the impeller involved by the first mode of execution.
Fig. 3 is the plan view of the impeller involved by the first mode of execution.
Fig. 4 is the rear view of the impeller involved by the first mode of execution.
Fig. 5 is the partial side view of the impeller involved by the first mode of execution.
Fig. 6 is the plan view of the impeller involved by variation.
Fig. 7 is the rear view of the impeller involved by variation.
Fig. 8 is the partial side view of the impeller involved by variation.
Fig. 9 is the rear view of the impeller involved by variation.
Figure 10 is the rear view of the impeller involved by variation.
Figure 11 is the rear view of the impeller involved by variation.
Figure 12 is the rear view of the impeller involved by variation.
Figure 13 is the rear view of the impeller involved by variation.
Figure 14 is the rear view of the impeller involved by variation.
Embodiment
Below, be described with reference to the mode of execution of accompanying drawing to example of the present invention.In addition, in this application, the direction with rotation axis parallel is called " axis ", the direction orthogonal with spin axis is called " radial direction ", the direction along the circular arc centered by spin axis is called " circumference ".Further, in this application, using the pressurized plane side of the impeller for axial side as face side, using the suction surface side of the impeller of the opposite side for axis as back side, the shape of each several part and position relationship are described.But, the face side defined here and back side do not limit when impeller and gas fan use towards.
< 1. 1 kinds of mode of execution >
The overall structure > of < 1-1. fan
Fig. 1 is the side view of the fan involved by the first mode of execution of gas fan of the present invention.Fig. 2 is the stereogram of the impeller 3 of fan 1.Fig. 3 is the plan view of impeller 3.Fig. 4 is the rear view of impeller 3.In Fig. 1 to Fig. 4, represent sense of rotation with solid arrow.
This fan 1 is the device by the power of motor 2, impeller 3 being rotated and blow to the face side of impeller 3.Such as, fan 1 can be used for enjoying the cool directly to user's blowing.Further, fan 1 also can as the circulator used together with air-conditioning etc.As shown in Figure 1, the fan 1 of present embodiment has the impeller 3 of motor 2 and axial flow.
Motor 2 is the mechanisms of the power being provided for rotation for impeller 3.In the present embodiment, DC Brushless Motor selected by motor 2.There is not the deterioration of the performance caused because of the wearing and tearing of brush in DC Brushless Motor, therefore long than the brush motor life-span.Further, DC Brushless Motor easily reduces power consumption than the easy speed change of alternating current motor.
The rotary part 22 that motor 2 has stationary part 21 and rotates centered by spin axis 9.Stationary part 21 has the motor chassis 211 of the part holding the rotary parts 22 such as the armature of motor and rotor.
Rotary part 22 has: the rotor producing moment of torsion between armature; And along the axle 221 that spin axis 9 extends.Axle 221 is fixed in rotor in the inside of motor chassis 211.The end of the face side of axle 221 is more outstanding to face side than motor chassis 211, is fixed on the following central part 30 of impeller 3.Therefore, when motor 2 drives, impeller 3 rotates together with the rotary part 22 of motor 2 centered by spin axis 9.In addition, although, in the present embodiment, the end winding support of the face side of axle 221 at impeller 3, also can be the face side of axle 221 end beyond partial fixing at impeller 3.That is, the part of axle 221 and impeller 3 fix.
Impeller 3 is supported to can rotates relative to the stationary part 21 of motor 2.By making the sense of rotation of impeller 3 in Fig. 1 to Fig. 4 shown in solid arrow rotate, produce the air-flow from back side towards face side.As shown in Figures 1 to 4, impeller 3 has: central part 30, multiple blade 40, first aileron 50 and the second aileron 60.
The impeller 3 of present embodiment is made for resin, and it is shaping by molding and forming.Therefore, central part 30, multiple blade 40, first aileron 50 and the second aileron 60 are formed as single parts.In addition, impeller 3 also can be formed by other materials such as metals.Further, impeller 3 also can be formed by multiple component combination.
As shown in Fig. 2 and Fig. 4, the wall portion 302 that central part 30 has the discoideus plectane portion 301 centered by spin axis 9 and extends from the ora terminalis in plectane portion 301 to axial back side.That is, the central part 30 of present embodiment is for there being lid cylindric.Further, as shown in Figure 4, central part 30 also has cylindrical portion 303 and flank 304.Cylindrical portion 303 from plectane portion 301 rearwardly side in roughly cylindric outstanding.By this shape, the substantial middle of central part 30 side overleaf has the axis hole 31 as the inner space of cylindrical portion 303.The axle 221 of motor 2 is inserted into and is fixed in axis hole 31.Therefore, when motor 2 drives, impeller 3 rotates together with axle 221 centered by spin axis 9.Wall portion 302 is connected by the multiple flanks 304 radially extended with cylindrical portion 303.Thereby, it is possible to suppress crooked relative to spin axis 9 of cylindrical portion 303.That is, crooked relative to axle 221 of impeller 3 can be suppressed.
In addition, in the present embodiment, central part 30 is viewed as circular from face side, but the present invention is not limited thereto.It also can be the polygonal such as pentagon or Hexagon that central part 30 is observed from face side.Further, in the present embodiment, the end of the face side of axle 221 is configured in the inside of central part 30, as long as but axle 221 and central part 30 fixed, the end of the face side of axle 221 also can be outstanding to face side from central part 30.
As shown in Figure 3 and 4, multiple blade 40 extends from the side of central part 30 to radial outside respectively.Multiple blade 40 arranges roughly at equal intervals in circumference.But the interval of the circumference of multiple blade 40 need not be constant.As shown in Fig. 2 and Fig. 4, be configured with a pair aileron in suction surface 42 side of each blade 40, that is, the first aileron 50 and the second aileron 60.About detailed construction and the effect of the first aileron 50 and the second aileron 60, will be described below.
As shown in Figure 1 and Figure 2, each blade 40 tilts from back side to face side towards trailing edge 402 along with from leading edge 401.Here, leading edge 401 is the end edge portion of the sense of rotation front side of blade 40, and trailing edge 402 is the end edge portion of the sense of rotation rear side of blade.By this shape, when impeller 3 rotates, uprise as the air pressure near the pressurized plane 41 on the blade face of the face side of blade 40, as the air pressure step-down near the suction surface 42 on the blade face of the back side of blade 40.Thus, around blade 40, produce towards the air-flow of axis from back side to face side.
< 1-2. is about aileron >
Next, the detailed construction of the first aileron 50 and the second aileron 60 and effect are described.Fig. 5 is the partial side view of impeller 3.In addition, in Figure 5, not shownly crest line is connect.
As shown in Figure 2, the first aileron 50 and the second aileron 60 are rearwardly given prominence to side from the suction surface 42 of blade 40.Further, the first aileron 50 and the second aileron 60 extend in the circumferential.First aileron 50 is configured in the radial outside of the second aileron 60.Further, a part for the first aileron 50 is overlapping in radial direction with a part for the second aileron 60.
As shown in Figure 4, from in the planimetric map of end on observation, using the part being positioned at sense of rotation forefront of the first aileron 50 as the first front end 51, using the part being positioned at sense of rotation rearmost of the first aileron 50 as the first rear end 52, using the part being positioned at sense of rotation forefront of the second aileron 60 as the second front end 61, using the part being positioned at sense of rotation rearmost of the second aileron 60 as the second rear end 62.
From the first front end 51 to the distance D1 of the radial direction of spin axis 9 with from the second front end 61 to the difference of the distance D2 of the radial direction of spin axis 9, than from the first rear end 52 to the distance D3 of the radial direction of spin axis with large to the difference of the distance D4 of the radial direction of spin axis 9 from the second rear end 62.That is, the distance of the radial direction between the first aileron 50 and the second aileron 60 narrows from the front of sense of rotation towards rear.Thus, the air-flow of the axis produced by blade 40 is made to concentrate between the first aileron 50 and the second aileron 60.
Thus, as shown in Fig. 1 hollow core arrow, near the radial position being configured with the first aileron 50 and the second aileron 60, be configured with blade 40 other parts radial position compared with, the wind speed of the air-flow of the axis produced by blade 40 becomes large.Its result is, as shown in the hollow arrow of dotted line in Fig. 1, the gas of surrounding sucks due to Coanda effect by the air-flow that this wind speed is large.Therefore, the air quantity of the air-flow to face side towards axis is added.
That is, in this fan 1, by arranging the first aileron 50 and the second aileron 60, air output can be increased when not changing the body shape of blade 40 and not increasing the rotating speed of motor 2.
In the first aileron 50 of present embodiment, distance D1 is larger than distance D3.Thus, the first aileron 50 has the effect guided to radially inner side by the air-flow in the axis leaning on the position of radially inner side to be produced by blade 40 than the first aileron 50.Further, in the second aileron 60 of present embodiment, distance D2 is less than distance D4.Thus, the second aileron 60 has the effect guided to radial outside by the air-flow in the axis leaning on the position of radial outside to be produced by blade 40 than the second aileron 60.By such guiding function of the first aileron 50 and the second aileron 60, concentrate the high efficiency air flow of the axis produced by blade 40.Thus near the radial position of being surrounded by the first aileron 50 and the second aileron 60, the speed of axial air-flow is improve efficiently.
Further, the first aileron 50 of present embodiment configures along the blade outer edge 403 of the radial outside of blade 40.That is, the first outer edge 501 of the radial outside of the first aileron 50 is overlapping in the axial direction with blade outer edge 403.Thus, by being configured near the radial outside of blade 40 by the first aileron 50, in the air-flow that blade 40 is sent to axial face side, the wind speed of outermost part becomes large.Thus the air-flow large by this wind speed easily sucks than the air-flow of blade 40 by radial outside.That is, further increase towards the air quantity of the air-flow of axial face side.
In addition, in the present embodiment, the first outer edge 501 roughly overall overlapping in the axial direction with blade outer edge 403, but also can be that the very small percentage of the first outer edge 501 is overlapping in the axial direction with blade outer edge 403.
As shown in Figure 4, sense of rotation rear is leaned on than the leading edge 401 of blade 40 in the first front end 51 of the first aileron 50 and the second front end 61 of the second aileron 60.That is, the leading edge 401 of blade 40 not with the first front end 51 and the second front end 61 overlapping in the axial direction.Thus the same relative wind reverse with sense of rotation produced by the rotation of blade 40 can not contact leading edge 401, first front end 51 and the second front end 61 simultaneously.Thus, with leading edge 401 with compared with the overlapping in the axial direction situation in the first front end 51 and the second front end 61, interference sound when blade 40 and the first aileron 50 and the second aileron 60 break wind can be reduced.
Further, the part comprising the first front end 51 of the first aileron 50 has acerous curved surface.Owing to being band circularity near the first front end 51 of the first aileron 50, the interference sound of the broken wind near the first front end 51 thus can be suppressed.Further, compared with near the first front end 51 being the situation of the shape of point, improve the intensity of the first aileron 50.In addition, too, the part comprising the second front end 61 of the second aileron 60 has acerous curved surface to the second aileron 60.Therefore, the interference sound caused by the second aileron 60 can also be suppressed.Further, the intensity of the second aileron 60 is improve compared with near the second front end 61 being the situation of the shape of point.
Further, as shown in Figure 5, the first aileron 50 and the second aileron 60 along with from the suction surface 42 of blade 40 towards back side away from and reduce gradually.That is, the first aileron 50 and the second aileron 60 along with the blade face from blade 40 vertically away from and reduce gradually.Thereby, it is possible to suppress the generation of the sinuous flow near the first aileron 50 and the second aileron 60.Further, when carrying out shaping impeller 3 by molding and forming, can at the periphery of the first aileron 50 and the second aileron 60 to axial back side by mold releasability.Consequently, molding and forming becomes easy, can suppress the increase of the joint line produced because using complicated mould.
< 2. variation >
Above, the mode of execution of example of the present invention is illustrated, but protection scope of the present invention is not limited in above-mentioned mode of execution.
Fig. 6 is the plan view of the impeller 3A involved by a variation.In the example of fig. 6, the first aileron 50A and the second aileron 60A is outstanding from the pressurized plane 41A of blade 40A towards face side.Like this, the first aileron and the second aileron also can be configured in pressurized plane side.
In the example of fig. 6, from the first front end 51A to the distance of the radial direction of spin axis 9A with from the second front end 61A to the difference of the distance of the radial direction of spin axis 9A, than from the first rear end 52A to the distance of the radial direction of spin axis 9A with large to the difference of the distance of the radial direction of spin axis 9A from the second rear end 62A.
Thus, near the radial position being configured with the first aileron 50A and the second aileron 60A, be configured with blade 40A other parts radial position compared with, the wind speed of the air-flow of the axis produced by blade 40A becomes large.Consequently, the gas of surrounding is sucked by Coanda effect by the air-flow that this wind speed is large.Thus, add towards the air quantity of axial face side air-flow.
Fig. 7 is the rear view of the impeller 3B involved by other variation.Fig. 8 is the partial side view of the impeller 3B of the example of Fig. 7.In the example in figure 7, the first front end 51B of the first aileron 50B and the second front end 61B of the second aileron 60B leans on sense of rotation rear than the leading edge 401B of blade 40B.Further, the first rear end 52B of the first aileron 50B and the second rear end 62B of the second aileron 60B leans on sense of rotation front than the trailing edge 402B of blade 40B.That is, the first front end 51B, the first rear end 52B, the second front end 61B and the second rear end 62B are configured in the inner side of blade 40B from end on observation.
Therefore, when having been molded impeller 3B by molding and forming, joint line can not be produced at the first aileron 50B and the second aileron.Thus, compared with the situation that not there is the first aileron 50B and the second aileron 60B with blade 40B, the joint line of impeller 3B entirety can not be increased.
Further, as shown in Figure 8, the end 64B of the end 54B of the axial face side of the first aileron 50B and the axial face side of the second aileron 60B leans on axial back side than the end 43B of the axial face side of blade 40B respectively.Further, the end 65B of the end 55B of the axial back side of the first aileron 50B and the axial back side of the second aileron 60B leans on axial face side than the end 44B of the axial back side of blade 40B respectively.That is, the domain of the existence 66B of the domain of the existence 56B of the axis of the first aileron 50B and the axis of the second aileron 60B is positioned at the scope of the domain of the existence 45B of the axis of blade 40.
Thus, with impeller 3B, not there is the first aileron 50B and compare with the situation of the second aileron 60B, impeller 3B can not be shortened and be configured in the distance between the static part around impeller 3B.Therefore, it is possible to suppress the noise caused due to the interference with static part to become large.Further, the first aileron 50B and the second aileron 60B also can not restrict the space for configuring static part.In addition, as the static part be configured in around impeller 3B, it is contemplated that it is the casing etc. holding motor and impeller 3B.
Fig. 9 is the rear view of the impeller 3C involved by other variation.In the example of figure 9, the first rear end 52C of the first aileron 50C and the second rear end 62C of the second aileron 60C leans on sense of rotation rear than the trailing edge 402C of blade 40C.In the example of figure 9, the air-flow of the axis produced by blade 40C leave from the trailing edge 402C of blade 40C towards sense of rotation rear rear guide by the first aileron 50C and the second aileron 60C.Thus, the effect in the air flow collection making to be produced by blade 40C can be improved.
Further, from end on observation, the first rear end 52C and the second rear end 62C is configured in the outside of blade 40C, week side's length of the first aileron 50C and the second aileron 60C by such structure to prolong.Thereby, it is possible to improve the first aileron 50C and the second aileron 60C further to the guiding function of air-flow.
Figure 10 is the rear view of the impeller 3D involved by other variation.In the example of Figure 10, the first aileron 50D is not overlapping with the blade outer edge 403D of the radial outside of blade 40D.That is, the first aileron 50D is not positioned near the outermost radial outside of blade 40D.Like this, the first aileron 50D also can be positioned at the position leaning on radially inner side than the blade outer edge 403D of blade 40D.
Figure 11 is the rear view of the impeller 3E involved by other variation.In the example of fig. 11, radial outside is leaned on than the half of blade 40E in the position of the radial direction of the second aileron 60E.Meet following size relationship specifically.
From the planimetric map of end on observation, using the part being positioned at outermost radial outside of blade 40E as blade outer end portion 404E; By the part being positioned at radial inner side of blade 40E, that is, using the root portion of blade 40E as blade inner end 405E; Using the part being positioned at radial inner side of the second aileron 60E as the second inner end 63E.
In the example of fig. 11, the distance D5 of the second inner end 63E to the radial direction of spin axis 9E and the difference of blade outer end portion 404E to the distance D6 of the radial direction of spin axis 9E are also less with the half of the difference of distance D6 than the radial distance D7 of blade inner end 405E to spin axis 9E.If that is, using the distance from spin axis 9E be the position of the middle of distance D6 and distance D7 as position D0, then the second inner end 63E of the second aileron 60E than position D0 by radial outside.
Thus, in the air-flow that impeller 40E sends to axial face side, the part accelerated by the first aileron 50E and the second aileron 60E is more by radial outside.Thus, by this high velocity air, easier will than blade 40E by the air intake of radial outside.That is, the air quantity towards the air-flow of axial face side increases further.
Figure 12 is the rear view of the impeller 3F involved by other variation.In the illustration in fig 12, remove near the first front end 51F and near the first rear end 52F, the first aileron 50F is the thick constant planar of the wing.Further, too, except near the second front end 61F and near the second rear end 62F, the second aileron 60F is also the thick constant planar of the wing to the second aileron 60F.So, the wing of the first aileron 50F and the second aileron 60F is thick also can be constant.
Also be in the illustration in fig 12, from the first front end 51F to the distance of the radial direction of spin axis 9F with from the second front end 61F to the difference of the distance of the radial direction of spin axis 9F, than from the first rear end 52F to the distance of the radial direction of spin axis 9F with large to the difference of the distance of the radial direction of spin axis 9F from the second rear end 62F.
Thus, be configured with impeller 40F other parts radial position compared with, near the radial position being configured with the first aileron 50F and the second aileron 60F, the wind speed of the air-flow of the axis produced by impeller 40F is larger.Consequently, the gas of surrounding is sucked by Coanda effect by the air-flow that this wind speed is large.Therefore, add towards the air quantity of the air-flow of axial face side.
Figure 13 is the rear view of the impeller 3G involved by other variation.In the example in figure 13, impeller 40G, the first aileron 50G, the second aileron 60G are parts individually.And, switch between the first orientation P1 that the allocation position of the first aileron 50G can represent at solid line and the second orientation P2 that dotted line represents.Further, switch between the 4th orientation P4 that the allocation position of the second aileron 60G third party position P3 that can represent at solid line and dotted line represent.
At this, using the distance of the radial direction of the first front end 51G during first orientation P1 and spin axis 9G as D11, using the distance of the radial direction of the first front end 51G during second orientation P2 and spin axis 9G as D12, using the distance of the radial direction of the first rear end 52G during first orientation P1 and spin axis 9G as D31, using the distance of the radial direction of the first rear end 52G during second orientation P2 and spin axis 9G as D32.
And, using the distance of the radial direction of the second front end 61G during the P3 of third party position and spin axis 9G as D21, using the distance of the radial direction of the second front end 61G during the 4th orientation P4 and spin axis 9G as D22, using the distance of the radial direction of the second rear end 62G during the P3 of third party position and spin axis 9G as D41, using the distance of the radial direction of the second rear end 62G during the 4th orientation P4 and spin axis 9G as D42.
Distance D11 is roughly the same with distance D31 or larger than distance D31.Thus, at first orientation P1, the first aileron 50G improves the straight movement of the air-flow of the axis produced by blade 40G or is guided to radially inner side by this air-flow.On the other hand, distance D12 is larger than distance D32.That is, at second orientation P2, the air-flow of the axis produced by blade 40G guides to radially inner side by the first aileron 50G.Further, distance D12 is larger with the difference of distance D31 than distance D11 with the difference of distance D32.Thus, at second orientation P2, compared with first orientation P1, the guiding function of the first aileron 50G to the air-flow of axis increases.
Distance D21 is less than distance D41.Further, distance D22 is less than distance D42.Thus, at third party position P3 and the 4th orientation P4, the air-flow of the axis produced by blade 40G guides to radial outside by the second aileron 60G.Further, distance D22 is larger with the difference of distance D41 than distance D21 with the difference of distance D42.Thus, at the 4th orientation P4, compared with the P3 of third party position, by the second aileron 60G leading axle to the effect of air-flow increase.
So, in the example in figure 13, the first aileron 50G first orientation P1 and second orientation P2 can be switched to, the second aileron 60G third party position P3 and the 4th orientation P4 can be switched to.Thereby, it is possible to according to the difference of purposes, switch the position of the radial direction in the air flow collection produced by blade 40G and the speed of this air-flow selectively.
Figure 14 is the rear view of the impeller 3H involved by other variation.In the example in figure 14, impeller 3H on each blade 40H except there is the first aileron 50H and the second aileron 60H also has the 3rd aileron 70H.
In the example in figure 14, the distance of the radial direction between the first aileron 50H and the second aileron 60H narrows from the front of sense of rotation towards rear.Further, the distance of the radial direction between the second aileron 60H and the 3rd aileron 70H narrows from the front of sense of rotation towards rear.Thus, the air-flow of the axis produced by blade 40 is made to concentrate between the first aileron 50H and the second aileron 60H and between the second aileron 60H and the 3rd aileron 70H.So, the aileron of more than three also can be configured on each blade.
In the fan of above-mentioned mode of execution, with d.c. motor as the power rotated for drives impeller.But gas fan of the present invention also can replace d.c. motor with alternating current motor.Further, gas fan of the present invention also can replace motor and make vane rotary by being connected with impeller by other driving sources such as motor.
Further, gas fan of the present invention is not necessarily the fan as object of enjoying the cool yet.Also can be, if the cooling fan etc. of ceiling fan, circulator, automobile is for the gas fan of other purposes.
Further, the shape forming the details of each parts of gas fan also can be different from the shape represented by each accompanying drawing of the application.Such as, at the impeller of above-mentioned mode of execution, there are 5 blades, but the blade of impeller also can be other sheet numbers such as 3,4,7.
Further, each key element described in above-mentioned mode of execution and variation etc. can suitably combine in the scope do not conflicted.
The present invention can be used for impeller and gas fan.
Claims (15)
1. an impeller for the axial flow rotated centered by spin axis, comprising:
Multiple blade, they circumferentially arrange; And
First aileron and the second aileron, described first aileron and described second aileron are given prominence to from the blade face of described blade, and extend in the circumferential,
Described first aileron and described second aileron are configured in the pressurized plane side of described blade and at least one party of suction surface side,
Described first aileron is configured in the radial outside of described second aileron, and at least local radial is overlapping with described second aileron,
The feature of described impeller is,
Distance from first front end being positioned at sense of rotation forefront of described first aileron to described spin axis and the difference of the second front end to the distance of described spin axis being positioned at sense of rotation forefront from described second aileron, than the distance from first rear end being positioned at sense of rotation rearmost of described first aileron to described spin axis with large to the difference of the distance of described spin axis from second rear end being positioned at sense of rotation rearmost of described second aileron.
2. the impeller described in claim 1, is characterized in that,
From described first front end to the distance of described spin axis with identical to the distance of described spin axis from described first rear end, or than large to the distance of described spin axis from described first rear end.
3. the impeller described in claim 1 or 2, is characterized in that,
From described second front end to the distance of described spin axis with identical to the distance of described spin axis from described second rear end, or than little to the distance of described spin axis from described second rear end.
4. impeller described any one of claims 1 to 3, is characterized in that,
First outer edge of the radial outside of described first aileron overlapping in the axial direction with the blade outer edge of the radial outside of described blade at least partially.
5. impeller described any one of Claims 1-4, is characterized in that,
Distance from the second inner end of the inner side of the radial direction described second aileron to described spin axis and the difference of the blade outer end portion from the outermost radial outside described blade to the distance of described spin axis, than the blade inner end from the inner side of the radial direction on described blade to the distance of described spin axis with also little to the half of the difference of the distance of described spin axis from described blade outer end portion.
6. impeller described any one of claim 1 to 5, is characterized in that,
Described first aileron and described second aileron are along with reducing gradually away from the described blade face of described blade vertically.
7. impeller described any one of claim 1 to 6, is characterized in that,
Sense of rotation rear is leaned on than the leading edge of described blade in described first front end of described first aileron and described second front end of described second aileron.
8. impeller described any one of claim 1 to 6, is characterized in that,
Sense of rotation front is leaned on than the trailing edge of described blade in described first rear end of described first aileron and described second rear end of described second aileron.
9. impeller described any one of claim 1 to 6, is characterized in that,
Sense of rotation rear is leaned on than the trailing edge of described blade in described first rear end of described first aileron and described second rear end of described second aileron.
10. impeller described any one of claim 1 to 9, is characterized in that,
Axial opposite side is leaned on than the end of the axial side of described blade in the end of the axial side of described first aileron,
Axial side is leaned on than the end of the axial opposite side of described blade in the end of the axial opposite side of described first aileron,
Axial opposite side is leaned on than the end of the axial side of described blade in the end of the axial side of described second aileron,
Axial side is leaned on than the end of the axial opposite side of described blade in the end of the axial opposite side of described second aileron.
11. impellers described any one of claim 1 to 10, is characterized in that,
The part comprising described first front end of described first aileron and the part comprising described second front end of described second aileron have acerous curved surface.
12. impellers described any one of claim 1 to 11, is characterized in that,
The allocation position of described first aileron can switch by described impeller between first orientation and second orientation,
First front end described in when being in first orientation to described spin axis Distance geometry described in the first rear end to the difference of the distance of described spin axis, from when being in second orientation described in the first front end to described spin axis Distance geometry described in the first rear end different to the difference of the distance of described spin axis.
13. impellers described any one of claim 1 to 12, is characterized in that,
The allocation position of described second aileron can switch by described impeller between third party position and the 4th orientation,
Second front end described in when being in third party position to described spin axis Distance geometry described in the second rear end to the difference of the distance of described spin axis, from when being in the 4th orientation described in the second front end to described spin axis Distance geometry described in the second rear end different to the difference of the distance of described spin axis.
14. impellers described any one of claim 1 to 13, is characterized in that,
Described impeller is that resin is made, and shaping by molding and forming.
15. 1 kinds of gas fans, comprising:
The motor of the rotary part that there is stationary part and rotate centered by spin axis; And
The impeller rotated together with described rotary part,
The feature of described gas fan is,
The impeller that described impeller is described any one of claim 1 to 14.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2013-252580 | 2013-12-06 | ||
| JP2013252580A JP6303461B2 (en) | 2013-12-06 | 2013-12-06 | Impeller and blower |
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| CN104696278A true CN104696278A (en) | 2015-06-10 |
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| CN201420745815.8U Active CN204553337U (en) | 2013-12-06 | 2014-12-02 | Impeller and gas fan |
| CN201410721354.5A Pending CN104696278A (en) | 2013-12-06 | 2014-12-02 | Impeller and air blower |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420745815.8U Active CN204553337U (en) | 2013-12-06 | 2014-12-02 | Impeller and gas fan |
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| JP (1) | JP6303461B2 (en) |
| CN (2) | CN204553337U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736426A (en) * | 2016-04-26 | 2016-07-06 | 浙江理工大学 | Axial flow fan comprising blade pressure surfaces with winglets and blade tops with blowing structures |
| CN105756975A (en) * | 2016-04-26 | 2016-07-13 | 浙江理工大学 | Axial flow fan with blade front edges having groove structures and with blade root blowing effect |
| CN109863673A (en) * | 2016-11-02 | 2019-06-07 | 三菱电机株式会社 | The rotor of vehicle-mounted dlternator |
| CN112513471A (en) * | 2018-08-06 | 2021-03-16 | 夏普株式会社 | Propeller fan and blower |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6303461B2 (en) * | 2013-12-06 | 2018-04-04 | 日本電産株式会社 | Impeller and blower |
| KR101630579B1 (en) * | 2015-11-11 | 2016-06-24 | (주) 금성풍력 | Impeller for fan |
| JP7076875B2 (en) | 2016-12-05 | 2022-05-30 | グローバル・ライフ・サイエンシズ・ソリューションズ・ユーエスエー・エルエルシー | Impeller for bioreactor system with one or more turbulence generators |
| JP2018112189A (en) * | 2017-01-12 | 2018-07-19 | 日本電産株式会社 | Serial axial flow fan |
| KR102261731B1 (en) | 2020-12-16 | 2021-06-07 | 주식회사 금성풍력 | Impeller for axial flow blower with wing tip axial and axial flow blower having the same |
| CN114593088B (en) * | 2022-03-21 | 2024-03-26 | 西安热工研究院有限公司 | improved design method for capacity-expansion transformation of movable blade of adjustable axial flow fan of power station movable blade |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190815510A (en) * | 1908-12-23 | 1909-07-22 | William Henry Ireland | Improvements in Screw Propellers and adaptable to any and all Vessels actuated by Propelling Power. |
| US4222710A (en) * | 1976-12-20 | 1980-09-16 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Axial flow fan having auxiliary blade |
| CN1088667A (en) * | 1992-12-16 | 1994-06-29 | 新典自动化股份有限公司 | The axial flow flabellum of tool deflecting wing rib |
| US5368508A (en) * | 1993-06-08 | 1994-11-29 | Whittington; Burl D. | Marine propeller with transversal converging ribs |
| CN1590778A (en) * | 2003-08-25 | 2005-03-09 | 乐金电子(天津)电器有限公司 | Axial fan |
| CN2839671Y (en) * | 2005-08-19 | 2006-11-22 | 林钧浩 | Booster axial-flow fan |
| CN204553337U (en) * | 2013-12-06 | 2015-08-12 | 日本电产株式会社 | Impeller and gas fan |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1758560A (en) * | 1928-12-26 | 1930-05-13 | Richard Just E | Aircraft propeller |
| JPS5637119Y2 (en) * | 1976-02-27 | 1981-08-31 | ||
| JPS53116516A (en) * | 1977-03-22 | 1978-10-12 | Aisin Seiki Co Ltd | Axial flow fan |
| JPS57202797U (en) * | 1981-06-18 | 1982-12-23 |
-
2013
- 2013-12-06 JP JP2013252580A patent/JP6303461B2/en active Active
-
2014
- 2014-12-02 CN CN201420745815.8U patent/CN204553337U/en active Active
- 2014-12-02 CN CN201410721354.5A patent/CN104696278A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190815510A (en) * | 1908-12-23 | 1909-07-22 | William Henry Ireland | Improvements in Screw Propellers and adaptable to any and all Vessels actuated by Propelling Power. |
| US4222710A (en) * | 1976-12-20 | 1980-09-16 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Axial flow fan having auxiliary blade |
| CN1088667A (en) * | 1992-12-16 | 1994-06-29 | 新典自动化股份有限公司 | The axial flow flabellum of tool deflecting wing rib |
| US5368508A (en) * | 1993-06-08 | 1994-11-29 | Whittington; Burl D. | Marine propeller with transversal converging ribs |
| CN1590778A (en) * | 2003-08-25 | 2005-03-09 | 乐金电子(天津)电器有限公司 | Axial fan |
| CN2839671Y (en) * | 2005-08-19 | 2006-11-22 | 林钧浩 | Booster axial-flow fan |
| CN204553337U (en) * | 2013-12-06 | 2015-08-12 | 日本电产株式会社 | Impeller and gas fan |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736426A (en) * | 2016-04-26 | 2016-07-06 | 浙江理工大学 | Axial flow fan comprising blade pressure surfaces with winglets and blade tops with blowing structures |
| CN105756975A (en) * | 2016-04-26 | 2016-07-13 | 浙江理工大学 | Axial flow fan with blade front edges having groove structures and with blade root blowing effect |
| CN109863673A (en) * | 2016-11-02 | 2019-06-07 | 三菱电机株式会社 | The rotor of vehicle-mounted dlternator |
| CN109863673B (en) * | 2016-11-02 | 2021-10-15 | 三菱电机株式会社 | Rotor of AC generator for vehicle |
| US11277055B2 (en) | 2016-11-02 | 2022-03-15 | Mitsubishi Electric Cornoration | Automotive alternator rotor |
| CN112513471A (en) * | 2018-08-06 | 2021-03-16 | 夏普株式会社 | Propeller fan and blower |
Also Published As
| Publication number | Publication date |
|---|---|
| CN204553337U (en) | 2015-08-12 |
| JP2015108361A (en) | 2015-06-11 |
| JP6303461B2 (en) | 2018-04-04 |
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Application publication date: 20150610 |