CN102341603A - Propeller fan - Google Patents

Propeller fan Download PDF

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Publication number
CN102341603A
CN102341603A CN2009801577155A CN200980157715A CN102341603A CN 102341603 A CN102341603 A CN 102341603A CN 2009801577155 A CN2009801577155 A CN 2009801577155A CN 200980157715 A CN200980157715 A CN 200980157715A CN 102341603 A CN102341603 A CN 102341603A
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China
Prior art keywords
blade
mentioned
radius
air
execution
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Granted
Application number
CN2009801577155A
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Chinese (zh)
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CN102341603B (en
Inventor
新井俊胜
中岛诚治
菊地仁
盐野入公宣
荒木克己
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Mitsubishi Electric Corp
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Mitsubishi Electric Corp
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Priority to CN201410473050.1A priority Critical patent/CN104214137B/en
Publication of CN102341603A publication Critical patent/CN102341603A/en
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Publication of CN102341603B publication Critical patent/CN102341603B/en
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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • 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
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Abstract

Provided is a propeller fan comprising a hub fitted on a spindle, and a plurality of wings mounted radially on the hub for blowing a wind in the spindle direction. In a first region of the wing from the spindle to a predetermined radius, the edge line of the maximum camber in the cylindrical section of the wing, which is cut from the spindle along an arbitrary radius, is within 50 % of a wing chord length from a wing front edge. In a second region of the wing from the predetermined radius to a wing outer-edge, the edge line of the maximum camber in the cylindrical section of the wing, which is cut from the spindle along the arbitrary radius, is connected at the predetermined radial position to the edge line of the maximum camber of the first region, and is positioned, as radially enlarged, on the side of a wing trailing-edge, so that the edge line is within 50 % of the wing chord length from a wing front edge at the wing outer-edge.

Description

Propeller type fan
Technical field
The present invention relates to be used for the propeller type fan of ventilation fan, air-conditioning etc.
Background technique
In the past; Disclose following propeller type fan; Its peripheral part at the hub that is installed on running shaft is provided with a plurality of blades; Dissecing the cylinder section of above-mentioned blade along any radius from above-mentioned running shaft, the maximum position of amount of warpage is positioned at vane trailing edge side (for example, with reference to patent documentation 1) along with the increase of radius.
In addition; Also disclose a kind of axial fan; It has the driving force of bearing and the propeller boss that rotates be attached at this propeller boss around blade, above-mentioned blade is thin wall vane and has warpage, the maximum camber (camber) of this warpage is set in 5%～8% the scope of blade chord length; And maximum camber position is arranged in 20%～40% the scope of blade chord length (for example, with reference to patent documentation 2).
Patent documentation 1: No. 3608038 communiques of Japan Patent
Patent documentation 2: japanese kokai publication hei 2-233899 communique
But,, produce big blade outer rim eddy current in the blade outer rim according to above-mentioned technology in the past.Therefore, the problem that exists air-supply-noise properties to worsen.
Summary of the invention
The present invention makes in view of the above problems, and its purpose is to obtain blade outer rim eddy current that a kind of blade outer rim that has suppressed at propeller type fan produced and the propeller type fan that has improved air-supply-noise properties.
In order to address the above problem, reach the object of the invention, propeller type fan of the present invention comprises: propeller boss, itself and running shaft are chimeric; A plurality of blades; Said a plurality of blade is and is arranged at above-mentioned propeller boss radially and blows along the running shaft direction; Said propeller type fan is characterised in that; In the 1st zone of the above-mentioned blade till radius from above-mentioned running shaft to regulation; Maximum camber crest line the cylinder section of the above-mentioned blade that dissects from above-mentioned running shaft along radius arbitrarily apart from blade inlet edge be positioned at the blade chord length 50% in, the 2nd zone of the above-mentioned blade till from the radius of afore mentioned rules to the blade outer rim, the maximum camber crest line the cylinder section of the above-mentioned blade that dissects from above-mentioned running shaft along radius arbitrarily is connected with the above-mentioned the 1st regional maximum camber crest line in the radial location of afore mentioned rules; Be positioned at the trailing edge side along with the increase of radius, and blade outer rim place be positioned at apart from blade inlet edge blade chord length 50% in.
Propeller type fan of the present invention has the blade outer rim eddy current that can be suppressed at the blade outer rim and produce, the effect of improving air-supply-noise properties.
Description of drawings
Fig. 1 is the stereogram of the general propeller type fan of expression.
Fig. 2-the 1st, the plan view of the propeller type fan of mode of execution 1 of the present invention.
Fig. 2-the 2nd, the figure of the cylinder section in the 1st zone of the blade of mode of execution 1.
Fig. 3-the 1st schematically representes the stereogram of air-flow of suction surface side of the blade of mode of execution 1.
Fig. 3-the 2nd is along the sectional view of the F-F line among Fig. 3-1.
Fig. 4-the 1st, expression has the figure of the air-flow around the blade of blade of the camber CLD in the past among Fig. 2-2.
Fig. 4-the 2nd, expression has the figure of the air-flow around the blade of blade of camber CLD ' of the mode of execution 1 among Fig. 2-2.
Fig. 5 be relatively and expression have maximum camber crest line CL ' shown in Fig. 2-1, mode of execution 1 blade the ratio noise properties and have the figure of ratio noise properties of the blade of maximum camber crest line CL in the past.
Fig. 6 is the stereogram of propeller type fan that expression has the blade of mode of execution 2, and the blade of mode of execution 2 makes that the perimembranous front edge side forms waveform in the blade of blade of the maximum camber crest line CL ' with mode of execution 1.
Fig. 7 is the stereogram of air-flow of suction surface side of schematically representing the blade of mode of execution shown in Figure 62.
Fig. 8 is the stereogram of propeller type fan that expression has the blade of mode of execution 3, and the blade of mode of execution 3 makes that perimembranous trailing edge side forms waveform in the blade of blade of the maximum camber crest line CL ' with mode of execution 1.
Fig. 9 is the stereogram of air-flow of suction surface side of schematically representing the blade of mode of execution shown in Figure 83.
Figure 10 is a presentation graphs 6 and the figure of the ratio noise of blade shown in Figure 8.
Figure 11 is the stereogram that expression has the propeller type fan of the crooked blade of the upstream side of blade periphery lateral airflow.
Figure 12 is the stereogram of air-flow of schematically representing the suction surface side of blade shown in Figure 11.
Figure 13 projects to the plan view on the plane with rotating shaft direct cross with propeller type fan shown in Figure 1.
Figure 14 is with the figure of radius R rotating and projection to the vertical plane that comprises running shaft and OX axle with the track of each the chord of blade center point P r among Figure 13.
Figure 15 is the figure of the chord of blade center line Pr1 of the crooked blade of the upstream side of expression blade periphery lateral airflow.
Figure 16 be the crooked blade of the upstream side of expression blade periphery lateral airflow chord of blade center line Pr1 define method, with the same figure of Figure 15.
Figure 17 is the figure of air-flow of the suction surface side of the blade of representing that schematically the upstream side of blade periphery lateral airflow is crooked, and wherein, above-mentioned blade is the blade of crest line CL ' with camber of the mode of execution 1 shown in Fig. 2-1.
Figure 18 is the figure of ratio noise of the propeller type fan of expression mode of execution 4 of the present invention.
Figure 19 is the figure of fan efficiency of the propeller type fan of expression mode of execution 4.
Embodiment
Below, specify the mode of execution of propeller type fan of the present invention according to accompanying drawing.In addition, the present invention is not limited to this mode of execution.
Mode of execution 1
Fig. 1 is the stereogram of the general propeller type fan of expression, Fig. 2-the 1st, the plan view of the propeller type fan of mode of execution 1 of the present invention, Fig. 2-the 2nd, the cylinder sectional drawing in the 1st zone of the blade of mode of execution 1.
Propeller type fan shown in Figure 1 has 3 blades, but does not limit the sheet number of blade in the present invention, also can be other a plurality of sheet number.In following explanation, the shape that is primarily aimed at 1 blade describes, and the shape of other blade also is same shape.
As shown in Figure 1, the blade 1 with three-dimensional shape is the peripheral part that is installed on columned propeller boss 2 radially, and this propeller boss 2 is driven by not shown motor rotation, around the direction rotation of running shaft 3 along sense of rotation B.In addition, propeller boss 2 is cylindric, forms blade 1 radially but be on the peripheral part of the hub that also can form at the bending sheet metal.Through the rotation of blade 1, produce the air-flow of airflow direction A.The face of the upstream side of blade 1 becomes suction surface, and the face in downstream side becomes pressure surface.
If blade 1 shown in Figure 1 project to running shaft 3 plane orthogonal on, then form the such shape of the blade 1 shown in Fig. 2-1.Dotted line CL shown in Fig. 2-1 is the maximum camber crest line (track on the summit of camber) in the past of blade 1, is positioned at the central authorities of the blade inlet edge 1b and the trailing edge 1c of blade 1.The camber of blade 1 all is the such circular shape of dotted line CLD (camber in the past) shown in Fig. 2-2 in the cylinder section of radius R 1 arbitrarily.
In the blade 1 of mode of execution 1, maximum camber crest line CL ' is the boundary with the radius R 2 of regulation, makes maximum camber crest line be positioned at CL1 ' in interior all sides of radius R 2, makes maximum camber crest line be positioned at CL2 ' at the outer circumferential side of radius R 2.Promptly; Interior all sides at radius R 2; Maximum camber crest line CL1 ' compares with the maximum camber crest line CL in the past of the central authorities of blade inlet edge 1b that is positioned at blade 1 and trailing edge 1c and is positioned at blade inlet edge 1b side, becomes the such non-circular shape of solid line CLD ' (camber of mode of execution 1) shown in Fig. 2-2.
Fig. 3-the 1st schematically representes the stereogram of air-flow of suction surface side of the blade of mode of execution 1, and Fig. 3-the 2nd is along the sectional view of the F-F line of Fig. 3-1.When blade 1 during along the rotation of the direction of sense of rotation B, air flows along the direction A of air-flow.Between the suction surface 1f of blade 1 and pressure surface 1g, produce pressure difference, shown in Fig. 3-2,, produce from pressure surface 1g side and sew air-flow and blade outer rim eddy current G towards suction surface 1f side at blade outer rim 1d.On the other hand, all sides in blade produce roughly along all air-flow E in the blade of suction surface 1f.Like this, the air-flow of the suction surface 1f side of the propeller type fan 91 of mode of execution 1 roughly is divided into these two kinds of air-flows that form is different of all air-flow E in blade periphery air-flow D and the blade.
Fig. 4-the 1st, expression has the figure of the air-flow around the blade of blade of the camber CLD in the past among Fig. 2-2, Fig. 4-the 2nd, expression has the figure of the air-flow around the blade of blade of camber CLD ' of the mode of execution 1 among Fig. 2-2.
Shown in Fig. 4-1, when sense of rotation B rotates, produce from the air-flow of blade inlet edge 1b towards trailing edge 1c at blade 1.The suction surface air-flow H of camber CLD in the past with maximum camber crest line CL produces eddy current along with become unstable near trailing edge 1c, at trailing edge 1c, produces big trailing edge eddy current J with pressure side air-flow interflow.Because eddy current and trailing edge eddy current J among such suction surface air-flow H produce noise.
On the other hand; Shown in Fig. 4-2, in the suction surface air-flow H ' of the camber CLD ' of mode of execution 1, compare along suction surface 1f with in the past camber CLD from blade inlet edge 1b leaked-in air and to flow with maximum camber crest line CL '; Suppressed the generation of eddy current; The scale of the trailing edge eddy current J ' that is produced at trailing edge 1c also diminishes, and compares with the blade with camber CLD in the past, and noise diminishes.
As above-mentioned; Form the shape of camber CLD ' that kind through the shape with blade 1, disorder minimizing and the noise of suction surface air-flow H ' reduce, but shown in Fig. 3-1; In propeller type fan 91; Produce big blade outer rim eddy current G at blade periphery air-flow D, therefore, very big with the flowing state difference of all air-flow E in the blade.So if make the camber of blade peripheral part likewise form camber CLD ', then blade outer rim eddy current G significantly changes, air-supply-noise properties is worsened.
Therefore; In the propeller type fan 91 of mode of execution 1; Shown in Fig. 2-1; Make the maximum camber crest line CL ' of blade 1 form CL1 ' and the so different crest line of form of CL2 ', make maximum camber crest line CL1 ' apart from blade inlet edge 1b be positioned at the blade chord length 50% in, the maximum camber crest line CL2 ' of blade peripheral part is begun from the position that is connected with maximum camber crest line CL1 '; Along with the change of radius is positioned at trailing edge 1c side greatly and more and more, and blade outer rim 1d place be positioned at the blade chord length 50% in.Reference number C Lt shown in Fig. 2-1 is the maximum camber position of blade outer rim, and reference number C Lb is the maximum camber position of the blade inner edge of blade in the past, and reference number C Lb ' is the maximum camber position of blade inner edge of the blade of mode of execution 1.
Fig. 5 be relatively and expression have maximum camber crest line CL ' shown in Fig. 2-1, mode of execution 1 blade the ratio noise properties and have the figure of ratio noise properties of the blade of maximum camber crest line CL in the past.The maximum camber crest line CL ' of mode of execution 1 shown in Figure 5; The 1st zone till the radius R 2=0.675 * Rt from blade inner edge 1e to blade (Rt is a blade outer rim radius); Be positioned at apart from blade inlet edge 1b is 35% position of blade chord length; The 2nd zone till from R2=0.675 * Rt to blade outer rim 1d is from being that 35% position of blade chord length begins apart from blade inlet edge 1b, along with the change of radius is positioned at trailing edge 1c side greatly and more and more; At blade outer rim 1d, be positioned at 50% position of blade chord length.The blade in the past that is used for comparison is that maximum camber crest line CL is positioned at apart from blade inlet edge 1b is the blade of 50% position of blade chord length.
In addition, than noise K TDefine through following formula.
K T＝SPL A-10Log(Q·P T 2.5)
Q: air quantity [m 3/ min]
P T: integral pressure [Pa]
SPL A: noise properties (A proofreaies and correct the back) [dB]
In Fig. 5, the longitudinal axis representes that than noise 1 scale shown in the dotted line is represented the poor of 1 [dBA], and transverse axis is represented air quantity.As shown in Figure 5, have the side of blade of the maximum camber crest line CL ' of mode of execution 1, the noise maximum can reduce about-1 [dBA].
Mode of execution 2
Fig. 6 is the stereogram of propeller type fan 92 that expression has the blade 21 of mode of execution 2, and the blade 21 of mode of execution 2 makes that the perimembranous front edge side forms waveform 21m in the blade of blade of the maximum camber crest line CL ' with mode of execution 1.The waveform of blade inlet edge 21b becomes maximum waveform, becomes small form gradually towards the blade central part.
Fig. 7 is the stereogram of air-flow of suction surface side of schematically representing the blade 21 of mode of execution shown in Figure 62.As shown in Figure 7, in the air that flows into blade inlet edge 21b,, make that all air-flow E become the few air-flow E2 of disorder in the blade, thereby can reduce the noise that the disorder because of air-flow causes because the waveform 21m of blade 21 produces vertical eddy current.
Mode of execution 3
Fig. 8 is the stereogram of propeller type fan 93 that expression has the blade 31 of mode of execution 3, and the blade 31 of mode of execution 3 will have that perimembranous trailing edge side forms waveform 31m in the blade of blade of maximum camber crest line CL ' of mode of execution 1.The waveform of trailing edge 31c is maximum waveform, becomes small form gradually towards the blade central part.
Fig. 9 is the stereogram of air-flow of suction surface side of schematically representing the blade 31 of mode of execution shown in Figure 83.As shown in Figure 9, through the vertical eddy current that produces by the waveform 31n of blade 31, the disorder of the caused air of eddy current that produces at trailing edge 31c is reduced, become disorderly air-flow E3 still less, thereby reduce the noise that the disorder because of air-flow causes.
Figure 10 is a presentation graphs 6 and the figure of the ratio noise of blade 21,31 shown in Figure 8.Shown in figure 10, in the big zone of air quantity, the side's noise maximum that makes all sides in the blade form the blade 21,31 of waveform can reduce about-0.5 [dBA].
Mode of execution 4
Figure 11 is the stereogram that expression has the propeller type fan of the crooked blade of the upstream side of blade periphery lateral airflow, and Figure 12 is the stereogram of air-flow of schematically representing the suction surface side of blade shown in Figure 11.The propeller type fan that Figure 11 and shown in Figure 12 has the crooked blade of the upstream side of blade periphery lateral airflow weakens the blade outer rim eddy current that produces at blade outer rim suction surface; Can reduce the noise that causes because of blade outer rim eddy current; But because the upstream side of blade periphery lateral airflow is crooked; The part of the composition that boosts that is produced by the rotation of blade leaks into the suction surface side, and fan efficiency is reduced a little.
In addition, the noise source of the blade of Fig. 1 and that kind shown in Figure 11 comprises: the noise that the blade outer rim eddy current that is produced in the blade outer rim causes; The noise that the disorder of blade suction surface air-flow causes; The noise that the trailing edge eddy current causes.In the crooked blade of the upstream side of blade periphery lateral airflow, the ratio of the noise that blade outer rim eddy current causes diminishes, and relatively, becomes big by the ratio of all noise generated by air flow in the blade.Therefore, be necessary to improve all air-flows in the blade, research brings the shape of the blade of influence can for blade periphery air-flow.
In the crooked blade of the upstream side of blade periphery lateral airflow; Through forming maximum camber crest line CL ' such shown in Fig. 2-1; Can blade periphery air-flow not reduced the noise that blade outer rim eddy current causes with exerting an influence yet; Improve all air-flows in the blade and further realize low noiseization, improve fan efficiency.
Figure 13 projects to the plan view on the plane with rotating shaft direct cross with propeller type fan shown in Figure 1; Figure 14 is with the figure of radius R rotating and projection to the vertical plane that comprises running shaft and OX axle with the track of each the chord of blade center point P r among Figure 13; Figure 15 is the figure of the chord of blade center line Pr1 of the crooked blade of the upstream side of expression blade periphery lateral airflow, Figure 16 be the crooked blade of the upstream side of expression blade periphery lateral airflow chord of blade center line Pr1 define method, with the same figure of Figure 15.
The definition of the shape of the blade that the upstream side of blade periphery lateral airflow is crooked is described with reference to Figure 13～Figure 16.If with blade shown in Figure 11 project to running shaft 3 plane orthogonal Sc (with reference to Figure 14) on, then become the shape of blade shown in Figure 13 1.Point Pb shown in Figure 13 representes the chord of blade central point (mid point) from the blade inlet edge 1b on the periphery of propeller boss 2 to trailing edge 1c.
Likewise, Pt representes the chord of blade central point (mid point) from the blade inlet edge 1b on the blade outer rim 1d to trailing edge 1c.Line Pr shown in Figure 13 representes the track (chord of blade center line) of each the chord of blade central point on the radius R arbitrarily of the chord of blade center point P t from the chord of blade center point P b on the propeller boss to the blade outer rim.
Figure 14 is the figure from the chord of blade center point P b of propeller boss to the track (chord of blade center line) of each the chord of blade central point of the chord of blade center point P t of blade outer rim of expression among Figure 13; Promptly; Expression is about chord of blade center point P b-Pr-Pt, with the figure of each the chord of blade center point P r on the radius R arbitrarily with the track (chord of blade center line) of each the chord of blade center point P r of radius R rotating and projection to the vertical plane that comprises running shaft 3 and OX axle.
Shown in figure 14; The top rake δ z chord of blade center line Pr (track of each chord of blade center point P r) of rotating and projection to the vertical plane that comprises running shaft 3 and OX axle, the chord of blade center point P t from the chord of blade center point P b of propeller boss 2 to the blade outer rim, that tilt to the upstream side of air-flow; Can be to represent with the angled line of planar S c; Wherein, above-mentioned planar S c and running shaft 3 quadratures.
The chord of blade center line Pr that in Figure 15, is represented by dotted lines is the track of the chord of blade central point of blade 1 shown in Figure 14, that top rake δ z is several angle; In the zone of chord of blade center line Pr1 till from the chord of blade center point P b of propeller boss to the chord of blade center point P t of blade outer rim; Be positioned under the certain situation of top rake chord of blade center line Pr and the chord of blade center point P b that passes propeller boss and with the folded zone of the OX axle of running shaft 3 quadratures (top rake=0 °); Wherein, said chord of blade center line Pr1 representes the track of blade peripheral part to the chord of blade central point of the crooked blade of the upstream side of air-flow.
The chord of blade center point P t of the chord of blade center point P b of the propeller boss of chord of blade center line Pr and chord of blade center line Pr1 and blade outer rim is positioned at same position, and the distance of the chord of blade center point P t anomaly face Sc of blade outer rim is H.
In Figure 16, show track and the top rake of blade peripheral part to each chord of blade center point P r2 of the blade of the crooked mode of execution 4 of the upstream side of air current A.To be made as Pr2 from the chord of blade central point on any radius R of running shaft 3 beginning, the distance that will be positioned at chord of blade center point P r2 distance and running shaft 3 plane orthogonal Sc on the chord of blade center line Pr1 is made as Ls.
In the blade 41 of mode of execution shown in Figure 16 4; The 1st zone till the bending point Pw from propeller boss 2 (radius R b) to intermediate portion radially is with the 1st certain top rake δ zw tilt upstream, and further tilt upstream of above-mentioned the 1st zone is compared in the 2nd zone till from bending point Pw to the blade outer rim.
The radius of bending point Pw on the chord of blade center line Pr1 is made as Rw, with the line Pr of the chord of blade center point P b on the periphery that links chord of blade center point P t and propeller boss 2 on the blade outer rim, be made as δ zt as the 2nd top rake at the tilt angle of side upstream.The 1st top rake δ zw representes through following formula.
δzw＝tan -1(Ls/(R-Rb))
(Rb＜R≤Rw)
As follows, the chord of blade center point P r2 pairing tilt angle δ zd on the radius R arbitrarily in the zone of the 2nd from bending point Pw to the blade outer rim (radius R t) forms n the function (1≤n) of radius R.
δzd＝α(R-Rb) n+δzw
α＝(δzt-δzw)/(Rt-Rw) n
(Rw＜R≤Rt)
In addition, also can not make above-mentioned tilt angle δ zd is n the function (1≤n), but the chord of blade center line Pr1 that makes the 2nd zone is with certain top rake shape ground tilt upstream linearly of radius R.
Figure 17 schematically representes the figure of blade peripheral part to the air-flow of the suction surface side of the crooked blade 41 of the upstream side of air-flow, and wherein, this blade 41 has the crest line CL ' of the maximum camber of the mode of execution 1 shown in Fig. 2-1.Shown in figure 17, according to the blade 41 of mode of execution 4, can improve all air-flows in blade periphery air-flow and the blade simultaneously, improve air-supply-noise properties.
Figure 18 is the figure of ratio noise of the propeller type fan of expression mode of execution 4 of the present invention, and Figure 19 is the figure of fan efficiency of the propeller type fan of expression mode of execution 4.The blade 41 of the propeller type fan of mode of execution 4 is in the 1st zone of blade inner edge R=0.675 * Rt; It is 35% position of blade chord length that maximum camber crest line CL ' is positioned at apart from blade inlet edge; In the 2nd zone till from R=0.675 * Rt to the blade outer rim; Maximum camber crest line CL ' is configured in like upper/lower positions, that is, be 50% position of blade chord length apart from 35% position of blade chord length in the blade outer rim.
In addition; At blade with the maximum camber crest line CL in the past that is used for comparison; It is 50% position of blade chord length that maximum camber crest line CL is positioned at apart from blade inlet edge; Making the bending point radius is Rw=0.7 * Rt; 2 functions through radius R decide from bending point Pw to the blade outer rim chord of blade center point P r2 pairing tilt angle δ zd on the radius R arbitrarily in the zone of the 2nd till (radius R t), and the tilt angle of tangent line 15 on the blade string of a musical instrument center point P t of blade outer rim, chord of blade center line Pr1 is δ zs=45 ° (with reference to Figure 16).The air quantity Q that Figure 18 representes to try to achieve through experiment with than noise K TThe result of relation, Figure 19 representes the air quantity Q and the fan efficiency E that try to achieve through experiment TThe result of relation.
Like Figure 17 and shown in Figure 180, the propeller type fan 94 of mode of execution 4 is compared to the crooked propeller type fan in the past of the upstream side of air-flow with the blade peripheral part, in the scope of practical application, than noise K TLowered (1dBA), and fan efficiency E T(maximum+2～3 about point) improves.
In addition, fan efficiency E TDefine through following formula.
E T＝(P T·Q)/(60·P W)
Q: air quantity [m 3/ min]
P T: integral pressure [Pa]
P W: axle power [W]
Utilizability in the industry
As stated, propeller type fan of the present invention is applicable to ventilation fan, air-conditioning etc.
Description of reference numerals
1,21,31,41 blades
1b, 21b blade inlet edge
1c, 31c trailing edge
1d blade outer rim
1e blade inner edge
The 1f suction surface
The 1g pressure surface
21m, 31n waveform
2 propeller boss
3 running shafts
The direction of A air-flow
The B sense of rotation
Radius arbitrarily in R1 blade the 1st zone
The border radius in R2 blade the 1st zone and blade the 2nd zone
The maximum camber crest line of CL blade in the past
The maximum camber crest line of the blade of CL ' mode of execution 1
The camber of CLD blade in the past
The camber of the blade of CLD ' mode of execution 1
The maximum camber crest line in blade the 1st zone of CL1 ' mode of execution 1
The maximum camber crest line in blade the 2nd zone of CL2 ' mode of execution 1
The maximum camber position of CLt blade outer rim
The maximum camber position of the blade inner edge of CLb blade in the past
The maximum camber position of the blade inner edge of the blade of CLb ' mode of execution 1
D blade periphery air-flow
All air-flows in the E blade
E2, E3 air-flow
G blade outer rim eddy current
The suction surface air-flow of H blade in the past
The suction surface air-flow of the blade of H ' mode of execution 1
The trailing edge eddy current of J blade in the past
The trailing edge eddy current of the blade of J ' mode of execution 1
91,92,93,94 propeller type fans.

Claims (3)

1. propeller type fan, it comprises: propeller boss, said propeller boss and running shaft are chimeric; A plurality of blades, said a plurality of blades are and are arranged at above-mentioned propeller boss radially and along running shaft direction air-supply, it is characterized in that,
In the 1st zone of above-mentioned blade till radius from above-mentioned running shaft to regulation, the maximum camber crest line the cylinder section of the above-mentioned blade that dissects from above-mentioned running shaft along radius arbitrarily, apart from blade inlet edge be positioned at the blade chord length 50% in,
In the 2nd zone of the above-mentioned blade till from the radius of afore mentioned rules to the blade outer rim; Maximum camber crest line the cylinder section of the above-mentioned blade that dissects from above-mentioned running shaft along radius arbitrarily; Radial location at afore mentioned rules is connected with the maximum camber crest line in above-mentioned the 1st zone; Be positioned at the trailing edge side along with the increase of radius, the blade outer rim be positioned at apart from blade inlet edge the blade chord length 50% in.
2. propeller type fan according to claim 1 is characterized in that,
The interior Zhou Houyuan side of all front edge sides or blade forms waveform in the blade.
3. propeller type fan according to claim 1 is characterized in that,
The upstream side of blade periphery lateral airflow is crooked.
CN200980157715.5A 2009-04-28 2009-04-28 Propeller fan Active CN102341603B (en)

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104405679A (en) * 2012-04-10 2015-03-11 夏普株式会社 Propeller fan, fluid sending device, and mold for molding
CN106903875A (en) * 2017-03-16 2017-06-30 青岛科技大学 A kind of 3D printing small-sized screw plasticizing apparatus
CN110036209A (en) * 2016-12-28 2019-07-19 大金工业株式会社 Propeller fan
CN110431311A (en) * 2017-04-14 2019-11-08 大金工业株式会社 Propeller fan
US11333165B2 (en) 2016-12-28 2022-05-17 Daikin Industries, Ltd. Propeller fan

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103629156B (en) * 2013-11-28 2015-10-28 浙江亿利达风机股份有限公司 A kind of central air conditioner outdoor unit but axial-flow blower of low-noise high-efficiency
JP6373439B1 (en) * 2017-03-31 2018-08-15 テラル株式会社 Axial fan
WO2018193545A1 (en) * 2017-04-19 2018-10-25 三菱電機株式会社 Propeller fan and air-conditioning device outdoor unit

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH02233899A (en) * 1989-03-06 1990-09-17 Nippondenso Co Ltd Axial fan
CN2086337U (en) * 1990-12-04 1991-10-09 况荣春 Fan vane type with wide gas flow
JP2001227498A (en) * 2000-02-14 2001-08-24 Hitachi Ltd Propeller fan
JP2002021787A (en) * 2000-07-05 2002-01-23 Fujitsu General Ltd Impeller of axial blower
JP2005307788A (en) * 2004-04-20 2005-11-04 Mitsubishi Electric Corp Axial fan
JP2008255966A (en) * 2007-04-09 2008-10-23 Mitsubishi Electric Corp Propeller fan

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5818097U (en) * 1981-07-30 1983-02-03 日産デイ−ゼル工業株式会社 internal combustion engine cooling fan
JPH0264300A (en) * 1988-08-31 1990-03-05 Hitachi Ltd Blade for fan
US6129528A (en) * 1998-07-20 2000-10-10 Nmb Usa Inc. Axial flow fan having a compact circuit board and impeller blade arrangement
JP3629702B2 (en) * 2001-12-21 2005-03-16 ダイキン工業株式会社 Blower
EP2131041B1 (en) * 2007-03-27 2018-08-22 Mitsubishi Electric Corporation Sirocco fan and air conditioner

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH02233899A (en) * 1989-03-06 1990-09-17 Nippondenso Co Ltd Axial fan
CN2086337U (en) * 1990-12-04 1991-10-09 况荣春 Fan vane type with wide gas flow
JP2001227498A (en) * 2000-02-14 2001-08-24 Hitachi Ltd Propeller fan
JP2002021787A (en) * 2000-07-05 2002-01-23 Fujitsu General Ltd Impeller of axial blower
JP2005307788A (en) * 2004-04-20 2005-11-04 Mitsubishi Electric Corp Axial fan
JP2008255966A (en) * 2007-04-09 2008-10-23 Mitsubishi Electric Corp Propeller fan

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104405679A (en) * 2012-04-10 2015-03-11 夏普株式会社 Propeller fan, fluid sending device, and mold for molding
US9816521B2 (en) 2012-04-10 2017-11-14 Sharp Kabushiki Kaisha Propeller fan, fluid feeder, and molding die
CN110036209A (en) * 2016-12-28 2019-07-19 大金工业株式会社 Propeller fan
EP3553320A4 (en) * 2016-12-28 2020-07-22 Daikin Industries, Ltd. Propeller fan
CN110036209B (en) * 2016-12-28 2020-11-20 大金工业株式会社 Propeller fan
US11333165B2 (en) 2016-12-28 2022-05-17 Daikin Industries, Ltd. Propeller fan
CN106903875A (en) * 2017-03-16 2017-06-30 青岛科技大学 A kind of 3D printing small-sized screw plasticizing apparatus
CN110431311A (en) * 2017-04-14 2019-11-08 大金工业株式会社 Propeller fan
US11333168B2 (en) 2017-04-14 2022-05-17 Daikin Industries, Ltd. Propeller fan

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TW201038825A (en) 2010-11-01
KR20110104548A (en) 2011-09-22
JPWO2010125645A1 (en) 2012-10-25
TWI400391B (en) 2013-07-01
WO2010125645A1 (en) 2010-11-04
JP5425192B2 (en) 2014-02-26
CN102341603B (en) 2014-09-24

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