CN1598325A - Low-noise strong blast volume axial-flow fan - Google Patents
Low-noise strong blast volume axial-flow fan Download PDFInfo
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- CN1598325A CN1598325A CN 200410012490 CN200410012490A CN1598325A CN 1598325 A CN1598325 A CN 1598325A CN 200410012490 CN200410012490 CN 200410012490 CN 200410012490 A CN200410012490 A CN 200410012490A CN 1598325 A CN1598325 A CN 1598325A
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Abstract
The invention relates to a pumping current blower fan with low noise and high wind rate, which belongs to non-positive-displace pump technical field. The shape of fan blade is back-swept, and its sectional plane is airfoil. The especial is that central axis is the center of rotation of the vane, it is cut by different radius cylinder face, geometry of the vane is fixed on by the numerical value of the chord An which is from the vane leading edge to its slurry radix axle wire, chord is spread by the sectional plane, X and Y in the sectional plane airfoil developed pattern. The advantage of the invention is big air output, low noise, high static pressure, and light weight.
Description
Technical field
The present invention relates to a kind of ventilation equipment, particularly a kind of axial-flow blower belongs to non-displacement pump technical field.
Background technique
Blower fan is the machinery that is used for conveying gas, and axial-flow blower is widely used in all trades and professions with characteristics such as it are simple in structure, easily manufactured, flow is big, is especially requiring the little ventilation occasion of power.How to improve fan efficiency, reduce the target that noise is this class blower fan research.Fan noise is based on aerodynamic noise, and this is because blade in the process of high speed rotating, is subjected to reasons such as gas percussion and eddy current, makes gas produce the caused air pulsing sound of vibration.According to the mechanism of production difference of power noise, be divided into rotation (impact) noise and eddy current noise again, Rotation Noise is because the gas medium of blade around in the high speed rotating process, hitting, and causes the pulsation of gas pressure and produces.Thereby the eddy current noise then is the turbulent boundary layer that produces when the airflow passes blade and vortex division lift-off to be caused the pulsation of blade upward pressure and causes.Show that by aerodynamic studies the size of fan delivery and noise and the aerodynamic characteristic of impeller are closely related, and the geometrical shape of blade is the principal element of decision impeller aerodynamic characteristic to axial-flow blower.The eddy current that produces as plate shaped blade is bigger, so eddy current crack is also bigger; And straight-vaned rotational noise is bigger.Therefore, rationally improving the fan blade geometrical shape, is the effective means that reduces noise, increases air quantity.
Summary of the invention
Provide a kind of thereby the present invention is used to overcome the defective of prior art and change the big air quantity axial-flow blower of low noise that the blade surface airflow characteristic effectively reduces noise, increases air quantity by changing blade geometric shape.
The alleged problem of the present invention is that following technological scheme solves:
The big air quantity axial-flow blower of a kind of low noise, form by housing and blade, blade is a sweepback, its sectional shape is a wing blade, its specialization is: the geometrical shape of described blade is determined by following parameter: with the center of rotation of blade 5 be central shaft, with the cylndrical surface cut blade of 4 different radiis, each cross section of gained is launched again, respectively launched cross section chord length Bn and the blade inlet edge 7 chord length An to blade slurry root medial axis 6, its numerical value is as follows respectively:
(1-1) cross section: R1=240mm B1=340mm A1=199mm
(2-2) cross section: R2=293mm B2=397mm A2=195mm
(3-3) cross section: R3=346mm B3=435mm A3=162mm
(4-4) cross section: R4=400mm B4=472mm A4=114mm
The sectional shape of blade is determined by following parameter: setting up plane right-angle coordinate on each cross section unfolded drawing, is the true origin of X-axis with the blade inlet edge, is the Y-axis true origin with blade slurry root medial axis, and the coordinate figure of each cross section respective point is:
1-1 cross section: X/B1 (%) X Y
OnY
On
0 0 -34 -34
2.5 8.5 -28～-29 -38～-39
5 17 -25～-26 -39～-40
10 34 -21～-22 -39～-40
20 68 -15～-16 -40～-41
30 102 -11～-12 -39～-40
40 136 -9～-10 -38～-39
50 170 -7～-8 -36～-37
60 204 -6～-7 -34～-35
70 238 -4～-5 -29～-30
80 272 -1～-2 -21～-22
90 306 5～6 -7～-8
100 340 15 15
2-2 cross section: X/B2 (%) X Y
OnY
Down
0 0 0 0
2.5 10 -6～-7 -38～-39
5 20 -9～-10 -39～-40
10 40 -14～-15 -39～-40
20 79 -21～-22 -40～-41
30 119 -24～-25 -39～-40
40 159 -27～-28 -38～-39
50 198 -29～-30 -39～-40
60 238 -25～-26 -34～-35
70 278 -16～-17 -33～-34
80 318 -11～-12 -27～-28
90 357 -7～-8 -20～-21
100 397 0 0；
3-3 cross section: X/B3 (%) X Y
OnY
Down
0 0 22 22
2.5 11 23～24 14～15
5 22 22～23 9～10
10 44 19～20 1～2
20 87 12～13 -12～-13
30 131 4～5 -23～-24
40 174 -3～-4 -33～-34
50 218 -11～-12 -41～-42
60 261 -19～-20 -48～-49
70 305 -24～-25 -51～-52
80 348 -28～-29 -49～-50
90 392 -27～-28 -41～-42
100 435 -23 -23；
4-4 cross section: X/B4 (%) X Y
OnY
Down
0 0 28 28
2.5 12 27～28 18～19
5 24 25～26 11～12
10 47 18～19 0～1
20 94 6～7 -18～-19
30 142 -6～-7 -34～-35
40 189 -18～-19 -49～-50
50 236 -30～-31 -61～-62
60 283 -40～-41 -71～-72
70 330 -49～-50 -77～-78
80 378 -55～-56 -78～-79
90 425 -56～-57 -71～-72
100 472 -55 -55
Wherein X, Y
On, Y
OnNumerical value unit is millimeter.
The big air quantity axial-flow blower of above-mentioned low noise, described blade is made of outside focce-bearing layer 10 and inner encapsulant layer 11, and described focce-bearing layer is fiber reinforced plastic, and inner encapsulant layer is a polyurethane foam.
The big air quantity axial-flow blower of low noise according to claim 2, it is characterized in that: the thickness of described blade focce-bearing layer is successively decreased to blade tip by root of blade, 9～11 millimeters of root focce-bearing layer thickness, 2～4 millimeters of tip focce-bearing layer thickness.
The present invention is according to the aerodynamic principle in the blade high speed rotating process, improve through the blade of repetition test axial-flow blower, its characteristics are mainly reflected in following aspect: 1. pass through the wing design of blade profile, the air-flow of blade surface of flowing through when making the blade high speed rotating can form less eddy current, thereby reduces eddy current crack to greatest extent; 2. adopt wide-angle sweepback blade profile, can effectively reduce the impact of blade and air-flow, reduce impact noise; 3. blade adopts double-layer composite material to make, and can improve blade stiffness and intensity, alleviates the blade deadweight, and the distortion when reducing the blade high speed rotating makes blade rotation more steady.Show that through comparative trial the present invention compares with similar blower fan, noise is little, air quantity is big, static pressure is high, in light weight, is particularly useful for the transformer cooler blower fan.
Description of drawings
Fig. 1 is the blade structure schematic representation;
Fig. 2 is the wing unfolded drawing of blade profile;
Fig. 3 is a blade assembling schematic representation.
Each parts label is as follows among the figure: 1-1,2-2,3-3,4-4 represent with the radius to be the cylndrical surface of R1, R2, R3, R4 and the tangent plane of blade cut gained respectively; 5. blade; 6. blade is starched the root medial axis; 7. blade inlet edge; 8. trailing edge; 9. blade is starched root; 10. focce-bearing layer; 11. encapsulant layer.
Embodiment
Referring to Fig. 1, Fig. 2, axial-flow blower of the present invention is made up of housing and blade, and blade 5 is a kind of wide-angle sweepback type blades, and its blade profile shape can be determined by the numerical value of X and Y in the wing unfolded drawing in parameters R n, An, Bn and cross section.By accompanying drawing as seen, blade slurry root center is crossed in blade slurry root medial axis, and along the blower fan center of rotation radially, it is an important parameter of determining blade geometric shape.Rn be with the cylndrical surface radius of blade rotation center coaxial line, cylndrical surface cut blade with these different radiis, again each cross section of gained is launched, respectively launched cross section chord length Bn and blade inlet edge 7 chord length An to blade slurry root medial axis 6, numerical value according to X and Y in the wing unfolded drawing of numerical value and cross section of blade slurry root medial axis, An, can determine the position of the several points of blade inlet edge, with these several profiles that promptly obtain blade inlet edge 7 that connect by smoothed curve.According to the numerical value of X and Y in the wing unfolded drawing of numerical value and cross section of the profile of blade inlet edge 7 and Bn, the geometric profile of trailing edge 8 can also be determined.N=4 in the present embodiment, the size of Rn, An, Bn is respectively: R1=240mm, B1=340mm, A1=199mm; R2=293mm, B2=397mm, A2=195mm; R3=346mm, B3=435mm, A3=162mm; R4=400mm, B4=472mm, A4=114mm.
Mounted blade of the present invention is wing to be airfoil, Figure 3 shows that with the radius to be the cylndrical surface cut blade of Rn, resulting cross section is launched the wing unfolded drawing in cross section of formation, this figure is put into a plane right-angle coordinate, with the blade inlet edge is the true origin of X-axis, with blade slurry root medial axis is the Y-axis true origin, and what record blade airfoil has a related parameter Y
On, Y
Down,,, can determine the spatial geometric shape (promptly according to the recovery of the wing sectional view of aviation with draw principle) of blade airfoil the smooth connection of determining by these parameters of spatial point in conjunction with Rn, An, Bn parameter.In the present embodiment, n=4, the parameter of 4 tangent planes is as described above.Amplify with the geometric similarity ratio according to above-mentioned parameter or with above-mentioned parameter or dwindle and the blade produced can also realize that the utility model reduces noise, increases the effect of air quantity, so all fall into protection domain of the present invention.
Referring to Fig. 2, another improvement of the present invention is that blade adopts sandwich structure.For the rigidity that improves blade and intensity and reduce the deadweight of blade as far as possible, blade of the present invention adopts the structure of peripheral hardware focce-bearing layer 10 and inner encapsulant layer 11, focce-bearing layer adopts fiber reinforced plastic or other high strength composite, and inner encapsulant layer is polyurethane foam or other lightweight filler.Consider that each position stressing conditions of blade does not wait, the thickness of focce-bearing layer is successively decreased to blade tip by root of blade, 9～11 millimeters of root focce-bearing layer thickness, 2～4 millimeters of tip focce-bearing layer thickness.
Product of the present invention and like product compare test and show that it has the advantages that air quantity is big, noise is low, static pressure is high, are very suitable for the cooling blower as high-power transformer.
Several specific embodiments are provided below:
If n=4, the size of Rn, An, Bn is respectively: R1=240mm, B1=340mm, A1=199mm; R2=293mm, B2=397mm, A2=195mm; R3=346mm, B3=435mm, A3=162mm; R4=400mm, B4=472mm, A4=114mm.
X, Y in the embodiment 1:(following parameters
On, Y
DownUnit is millimeter)
4-4 cross section, 3-3 cross section, 2-2 cross section, 1-1 cross section
X/B1 (%) X Y
OnY
DownX Y
OnY
DownX Y
OnY
DownX Y
OnY
Down
0 0 -34 -34 0 0 0 0 22 22 0 28 28
2.5 8.5 -28 -38 10 -6 -38 11 23 14 12 27 18
5 17 -25 -39 20 -9 -39 22 22 9 24 25 11
10 34 -21 -39 40 -14 -39 44 19 1 47 18 0
20 68 -15 -40 79 -21 -40 87 12 -12 94 6 -18
30 102 -11 -39 119 -24 -39 131 4 -23 142 -6 -34
40 136 -9 -38 159 -27 -38 174 -3 -33 189 -18 -49
50 170 -7 -36 198 -29 -39 218 -11 -41 236 -30 -61
60 204 -6 -34 238 -25 -34 261 -19 -48 283 -40 -71
70 238 -4 -29 278 -16 -33 305 -24 -51 330 -49 -77
80 272 -1 -21 318 -11 -27 348 -28 -49 378 -55 -78
90 306 5 -7 357 -7 -20 392 -27 -41 425 -56 -71
100 340 15 15 397 0 0 435 -23 -23 472 -55 -55。
X, Y in the embodiment 2:(following parameters
On, Y
DownUnit is millimeter)
4-4 cross section, 3-3 cross section, 2-2 cross section, 1-1 cross section
X/B1 (%) X Y
OnY
DownX Y
OnY
DownX Y
OnY
DownX Y
OnY
Down
0 0 -34 -34 0 0 0 0 22 22 0 28 28
2.5 8.5 -29 -39 10 -7 -39 11 24 15 12 28 19
5 17 -26 -40 20 -10 -40 22 23 10 24 26 12
10 34 -22 -40 40 -15 -40 44 20 2 47 19 1
20 68 -16 -41 79 -22 -41 87 13 -13 94 7 -19
30 102 -12 -40 119 -25 -40 131 5 -24 142 -7 -35
40 136 -10 -39 159 -28 -39 174 -4 -34 189 -19 -50
50 170 -8 -37 198 -30 -40 218 -12 -42 236 -31 -62
60 204 -7 -35 238 -26 -35 261 -20 -49 283 -41 -72
70 238 -5 -30 278 -17 -34 305 -25 -52 330 -50 -78
80 272 -2 -22 318 -12 -28 348 -29 -50 378 -56 -79
90 306 6 -8 357 -8 -21 392 -28 -42 425 -57 -72
100 340 15 15 397 0 0 435 -23 -23 472 -56 -55，
Above-mentioned parameter is the numerical value of round.
The present invention is through comparative trial, and it is as follows to record relevant data:
Blower fan contrast blower fan of the present invention
Power (kw) 2.0 1.5
Rotating speed (r/min) 950 960
Air quantity m
3/ h static pressure (Pa) noise db (A) air quantity m
3/ h static pressure (Pa) noise db (A)
26651 61.7 72 22251 39.4 80
25727 99.9 71 21109 65.8 77.5
24440 126 70 20312 86.7 76.5
23081 158 69 19055 117 75
21637 182 68.5 17708 149 73.5
20089 200 69 16250 168 74
18412 224.5 70 14647 193 72.5
16566 244.7 71 12847 211 73
14487 247 73 10748 241 75
12054 244 74 8125 267 76。
Claims (3)
1. big air quantity axial-flow blower of low noise, form by housing and blade, blade is a sweepback, its sectional shape is a wing blade, it is characterized in that: the geometrical shape of described blade is determined by following parameter: with the center of rotation of blade (5) be central shaft, with the cylndrical surface cut blade of 4 different radiis, each cross section of gained is launched again, respectively launched cross section chord length Bn and blade inlet edge (7) to blade slurry root medial axis (6) chord length An, its numerical value is as follows respectively:
(1-1) cross section: R1=240mm B1=340mm A1=199mm
(2-2) cross section: R2=293mm B2=397mm A2=195mm
(3-3) cross section: R3=346mm B3=435mm A3=162mm
(4-4) cross section: the sectional shape of R4=400mm B4=472mm A4=114mm blade is determined by following parameter: set up plane right-angle coordinate on each cross section unfolded drawing, with the blade inlet edge is the true origin of X-axis, with blade slurry root medial axis is the Y-axis true origin, and the coordinate figure of each cross section respective point is:
(1-1) cross section: X/B1 (%) X Y
OnY
On
0 0 -34 -34
2.5 8.5 -28～-29 -38～-39
5 17 -25～-26 -39～-40
10 34 -21～-22 -39～-40
20 68 -15～-16 -40～-41
30 102 -11～-12 -39～-40
40 136 -9～-10 -38～-39
50 170 -7～-8 -36～-37
60 204 -6～-7 -34～-35
70 238 -4～-5 -29～-30
80 272 -1～-2 -21～-22
90 306 5～6 -7～-8
100 340 15 15
(2-2) cross section: X/B2 (%) X Y
OnY
Down
0 0 0 0
2.5 10 -6～-7 -38～-39
5 20 -9～-10 -39～-40
10 40 -14～-15 -39～-40
20 79 -21～-22 -40～-41
30 119 -24～-25 -39～-40
40 159 -27～-28 -38～-39
50 198 -29～-30 -39～-40
60 238 -25～-26 -34～-35
70 278 -16～-17 -33～-34
80 318 -11～-12 -27～-28
90 357 -7～-8 -20～-21
100 397 0 0；
(3-3) cross section: X/B3 (%) X Y
OnY
Down
0 0 22 22
2.5 11 23～24 14～15
5 22 22～23 9～10
10 44 19～20 1～2
20 87 12～13 -12～-13
30 131 4～5 -23～-24
40 174 -3～-4 -33～-34
50 218 -11～-12 -41～-42
60 261 -19～-20 -48～-49
70 305 -24～-25 -51～-52
80 348 -28～-29 -49～-50
90 392 -27～-28 -41～-42
100 435 -23 -23；
(4-4) cross section: X/B4 (%) X Y
OnY
Down
0 0 28 28
2.5 12 27～28 18～19
5 24 25～26 11～12
10 47 18～19 0～1
20 94 6～7 -18～-19
30 142 -6～-7 -34～-35
40 189 -18～-19 -49～-50
50 236 -30～-31 -61～-62
60 283 -40～-41 -71～-72
70 330 -49～-50 -77～-78
80 378 -55～-56 -78～-79
90 425 -56～-57 -71～-72
100 472 -55 -55，
Wherein X, Y last,, the last numerical value unit of Y is millimeter.
2. the big air quantity axial-flow blower of low noise according to claim 1, it is characterized in that: described blade is made of outside focce-bearing layer (10) and inner encapsulant layer (11), described focce-bearing layer is fiber reinforced plastic, and inner encapsulant layer is a polyurethane foam.
3. the big air quantity axial-flow blower of low noise according to claim 2, it is characterized in that: the thickness of described blade focce-bearing layer is successively decreased to blade tip by root of blade, 9～11 millimeters of root focce-bearing layer thickness, 2～4 millimeters of tip focce-bearing layer thickness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100124903A CN1316164C (en) | 2004-08-19 | 2004-08-19 | Low-noise strong blast volume axial-flow fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100124903A CN1316164C (en) | 2004-08-19 | 2004-08-19 | Low-noise strong blast volume axial-flow fan |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1598325A true CN1598325A (en) | 2005-03-23 |
| CN1316164C CN1316164C (en) | 2007-05-16 |
Family
ID=34662833
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2004100124903A Expired - Fee Related CN1316164C (en) | 2004-08-19 | 2004-08-19 | Low-noise strong blast volume axial-flow fan |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1316164C (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101749268B (en) * | 2010-02-24 | 2011-07-27 | 天津市华邦科技发展有限公司 | Axial flow pump impeller matched with chemical reactor for use |
| CN101666329B (en) * | 2009-09-17 | 2012-02-01 | 上海交通大学 | Combined-wing type axial flow fan blade |
| CN102410253A (en) * | 2011-11-28 | 2012-04-11 | 上海交通大学 | Blade profile of sheet-shaped axial flow fan formed by adopting squeezing, pulling and cutting process |
| CN102979758A (en) * | 2012-12-28 | 2013-03-20 | 天津市华邦科技发展有限公司 | Axial flow pump impeller for chemical reactor |
| CN103511342A (en) * | 2012-06-19 | 2014-01-15 | 通用电气公司 | Airfoil shape for use in a compressor |
| CN105298912A (en) * | 2015-11-10 | 2016-02-03 | 南京航空航天大学 | Bump front edge inlet guider blade |
| CN106949095A (en) * | 2017-04-20 | 2017-07-14 | 浙江理工大学 | The optimization method of Low-pressure axial fan impeller blade |
| CN108757562A (en) * | 2018-05-31 | 2018-11-06 | 广东泛仕达农牧风机有限公司 | A kind of novel livestock fan blade and the herding wind turbine including the fan blade |
| WO2022193869A1 (en) * | 2021-03-15 | 2022-09-22 | 追觅科技(上海)有限公司 | Rotor, fan, and stand fan |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2262128Y (en) * | 1995-06-26 | 1997-09-10 | 袁仲文 | Front bended sweepforward assembled axial-flow blower |
| JP3754244B2 (en) * | 1999-09-17 | 2006-03-08 | 三洋電機株式会社 | Wing design method for axial flow fan and axial flow fan |
| TW438953B (en) * | 1999-09-20 | 2001-06-07 | Mitsubishi Electric Corp | Blower, blower system and the blowing method of blower system |
| CN2464535Y (en) * | 2000-10-09 | 2001-12-12 | 胡德诚 | Aerofoil shape blade made of composite material integral moulded by vacuum injection |
| CN2495836Y (en) * | 2001-04-24 | 2002-06-19 | 胡德诚 | Airplane wing like blade made of composite material |
| CN2721930Y (en) * | 2004-08-19 | 2005-08-31 | 保定多田冷却设备有限公司 | Low-noise axial-flow fan with big blowing rate |
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2004
- 2004-08-19 CN CNB2004100124903A patent/CN1316164C/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101666329B (en) * | 2009-09-17 | 2012-02-01 | 上海交通大学 | Combined-wing type axial flow fan blade |
| CN101749268B (en) * | 2010-02-24 | 2011-07-27 | 天津市华邦科技发展有限公司 | Axial flow pump impeller matched with chemical reactor for use |
| CN102410253A (en) * | 2011-11-28 | 2012-04-11 | 上海交通大学 | Blade profile of sheet-shaped axial flow fan formed by adopting squeezing, pulling and cutting process |
| CN102410253B (en) * | 2011-11-28 | 2013-07-17 | 上海交通大学 | Blade profile of sheet-shaped axial flow fan formed by adopting squeezing, pulling and cutting process |
| CN103511342A (en) * | 2012-06-19 | 2014-01-15 | 通用电气公司 | Airfoil shape for use in a compressor |
| CN102979758A (en) * | 2012-12-28 | 2013-03-20 | 天津市华邦科技发展有限公司 | Axial flow pump impeller for chemical reactor |
| CN105298912A (en) * | 2015-11-10 | 2016-02-03 | 南京航空航天大学 | Bump front edge inlet guider blade |
| CN106949095A (en) * | 2017-04-20 | 2017-07-14 | 浙江理工大学 | The optimization method of Low-pressure axial fan impeller blade |
| CN106949095B (en) * | 2017-04-20 | 2018-12-07 | 浙江理工大学 | The optimization method of Low-pressure axial fan impeller blade |
| CN108757562A (en) * | 2018-05-31 | 2018-11-06 | 广东泛仕达农牧风机有限公司 | A kind of novel livestock fan blade and the herding wind turbine including the fan blade |
| WO2022193869A1 (en) * | 2021-03-15 | 2022-09-22 | 追觅科技(上海)有限公司 | Rotor, fan, and stand fan |
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| Publication number | Publication date |
|---|---|
| CN1316164C (en) | 2007-05-16 |
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