CN113250997A - Fan blade - Google Patents
Fan blade Download PDFInfo
- Publication number
- CN113250997A CN113250997A CN202110634581.4A CN202110634581A CN113250997A CN 113250997 A CN113250997 A CN 113250997A CN 202110634581 A CN202110634581 A CN 202110634581A CN 113250997 A CN113250997 A CN 113250997A
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- CN
- China
- Prior art keywords
- blade
- fan
- ratio
- hub
- blades
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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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 discloses a fan blade, which has a hub ratio of 0.091, a root-tip ratio of 1.25 and a blade surface area of 0.1m2Root setting angle 55.12, tip setting angle 24.3. Wherein, the hub diameter is 132mm, and the impeller diameter is 1443 mm. For a fan with a certain hub ratio and blade chord length, the optimal number of blades is provided, and the number of blades of the fan is 3. The invention aims to provide a high-efficiency fan, which selects blade profiles with good aerodynamic characteristics as much as possible and determines a proper installation angle, thereby reducing flow loss, avoiding stall and ensuring that the design index is reached.
Description
Technical Field
The invention relates to an axial fan blade design.
Background
The geometry of the blade cascade of the impeller of the axial fan on different radii is shaped according to a triangle of the selected and calculated speed, and the movement of the air flow is ensured by the adaptive blade profile and blade cascade.
In order to design a high-efficiency fan, the blade profile with good aerodynamic characteristics is selected as much as possible and a proper mounting angle beta is determinedAThereby reducing flow loss to avoid stall and ensure that the design index is reached.
When the pneumatic calculation of the impeller cascade is carried out, main structural parameters of the impeller, such as a hub ratio upsilon and an outer diameter D, must be reasonably selectedtAnd the number Z of blades, the radial gap delta and the like, so as to ensure that the pressure, the flow rate and the like required by the axial flow fan are realized.
1) Hub ratio v
When designing an axial fan, it is necessary to determine a hub ratio υ Dh/Dt(Dh-hub diameter; dt-impeller outer diameter). The hub ratio is importantAnd (4) structural parameters. It has an effect on the pressure, flow, efficiency, etc. of the fan. Therefore, the hub ratio v cannot be arbitrarily selected when the pressure, flow rate and rotation speed of the ventilating fan are constant.
2) Impeller outer diameter Dt
DtDirectly affects the performance and structure of the fan. At a given speed, the impeller size D of the fan is given for a given fan full pressure and flow ratetIs also substantially determined.
3) Number of blades Z
For the selected isolated blade profile, the lift coefficient c is determined under the rated working conditionySince the number of blades is constant, the change of the number of blades means the change of the blade chord length b. B decreases as the number of blades Z increases, and b increases as Z decreases. For a fan with a certain hub ratio and blade chord length, there is an optimum number of blades.
According to the design index, the basic structure parameters and the selected airfoil data, variable ring volume design can be adopted, the main geometric parameters of the blade are obtained through calculation, and the shape of the fan blade is determined.
Disclosure of Invention
The technical problems solved by the invention are as follows: a fan blade is provided.
In order to solve the technical problems, the invention provides the following technical scheme: a fan blade has a hub ratio of 0.091, a root-tip ratio of 1.25 and a blade surface area of 0.1m2Root setting angle 55.12, tip setting angle 24.3.
Wherein, the hub ratio is the ratio of the hub diameter to the impeller outer diameter. Alternatively, the hub diameter is 132mm and the impeller diameter is 1443 mm.
Wherein, the root-tip ratio is the ratio of the chord length of the blade root to the chord length of the blade tip. For a fan with a certain hub ratio and blade chord length, there is an optimum number of blades. Alternatively, the number of blades is 3.
The invention aims to provide a high-efficiency fan, which selects blade profiles with good aerodynamic characteristics as much as possible and determines a proper installation angle, thereby reducing flow loss, avoiding stall and ensuring that the design index is reached.
Detailed Description
A fan blade having a geometry: the number of blades is 3, the diameter of a hub is 132mm, the diameter of an impeller is 1443mm, the hub ratio is 0.091, the root-tip ratio (the ratio of the chord length of the blade root to the chord length of the blade tip) is 1.25, and the surface area of each blade is 0.1m2Root setting angle 55.12, tip setting angle 24.3.
The blade airfoil is composed of curves of an upper surface and a lower surface, and the geometrical size is as follows:
coordinates of upper surface curve:
the upper surface curve satisfies the equation:
y=p1+p2*x+p3/x+p4*x^2+p5/x^2+p6*x^3+p7/x^3+p8*x^4+p9/x^4+p10*x^5
coordinates of lower surface curve:
the lower surface curve satisfies the equation:
y=(p1+p3*x+p5*x^2+p7*x^3+p9*x^4+p11*x^5+p13*x^6)/(1+p2*x+p4*x^2+p6*x^3+p8*x^4+p10*x^5+p12*x^6+p14*x^7)
the above description is only a preferred embodiment of the present invention, and for those skilled in the art, the present invention should not be limited by the description herein, since various changes and modifications can be made in the details of the embodiment and the application range according to the spirit of the present invention.
Claims (4)
1. A fan blade, characterized by: hub ratio of 0.091, root tip ratio of 1.25, blade surface area of 0.1m2, root setting angle of 55.12, tip setting angle of 24.3.
2. A fan blade according to claim 1, wherein: the hub diameter is 132mm, and the impeller diameter is 1443 mm.
3. A fan blade according to claim 1, wherein: the number of the blades is 3.
4. A fan blade according to claim 1, wherein: the blade airfoil is formed by curves of an upper surface and a lower surface, and the coordinates of the curves of the upper surface are as follows:
1.11014456733358e-002 5.41816826146390e-002
5.40159893956340e-002 1.34439335570192e-001
1.08073402096019e-001 2.68837247835632e-001
1.73273683774492e-001 4.57375419410961e-001
2.59351311047595e-001 5.63336232964666e-001
3.34244646037861e-001 6.24249202601384e-001
4.25251646576364e-001 6.48212584399983e-001
5.15409469367466e-001 6.08570481753034e-001
5.96537011722795e-001 5.51074934758295e-001
6.97278488877843e-001 4.38320699225384e-001
7.85572262955139e-001 3.07837289258937e-001
8.73866037032434e-001 1.77353879292490e-001
9.31237314112920e-001 8.43585601259269e-002
9.79288347624373e-001 3.71567043618740e-002
the upper surface curve satisfies the equation:
y=p1+p2*x+p3/x+p4*x^2+p5/x^2+p6*x^3+p7/x^3+p8*x^4+p9/x^4+p10*x^5
p1 -13.0422326399054
p2 54.2736810554122
p3 1.8731783035922
p4 -120.232437827001
p5 -0.137468370047483
p6 150.953103076343
p7 0.00422501052820496
p8 -102.80067583801
p9 -3.23346656468568E-5
p10 29.1311932655333
coordinates of lower surface curve:
1.05422310591939e-002 -7.30707095812104e-002
5.25661737293401e-002 -4.73261256783066e-002
9.34509755188269e-002 -2.15401184706516e-002
1.43324634439336e-001 3.11917484776936e-002
2.19398533615012e-001 8.29708794167599e-002
2.88761857420985e-001 1.07721304005634e-001
3.53320077875813e-001 1.87191914170913e-001
3.96400314817116e-001 2.31079905554865e-001
4.47578807837289e-001 2.47400687626859e-001
5.19510376537840e-001 2.08421357855930e-001
5.91441945238391e-001 1.69442028085001e-001
6.85058613976223e-001 1.20583240130898e-001
7.83231846236693e-001 7.15587589577897e-002
8.75626527484363e-001 4.09262250942380e-002
9.44182096847687e-001 -7.02125015533739e-003
9.77300028996313e-001 -2.64073567789238e-002
9.95609129696367e-001 -4.52549604407440e-002
the lower surface curve satisfies the equation:
y=(p1+p3*x+p5*x^2+p7*x^3+p9*x^4+p11*x^5+p13*x^6)/(1+p2*x+p4*x^2+p6*x^3+p8*x^4+p10*x^5+p12*x^6+p14*x^7)
p1 -0.07730942947012
p2 -12.9892065093964
p3 1.49140380839415
p4 61.5474835248723
p5 -10.5506752864614
p6 -111.454430681359
p7 36.8954944023718
p8 22.3923650825415
p9 -71.6829458488619
p10 107.004556271359
p11 83.8609549845417
p12 39.586807978503
p13 -40.9206115720164
p14 -87.1757545567409。
Priority Applications (1)
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CN202110634581.4A CN113250997B (en) | 2021-06-08 | 2021-06-08 | Fan blade |
Applications Claiming Priority (1)
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CN202110634581.4A CN113250997B (en) | 2021-06-08 | 2021-06-08 | Fan blade |
Publications (2)
Publication Number | Publication Date |
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CN113250997A true CN113250997A (en) | 2021-08-13 |
CN113250997B CN113250997B (en) | 2022-11-18 |
Family
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Family Applications (1)
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Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2003120589A (en) * | 2001-10-15 | 2003-04-23 | Yanmar Co Ltd | Radiator fan and engine cooling device using it |
CN1526957A (en) * | 2003-03-05 | 2004-09-08 | 汉�空调株式会社 | Axial-flow fan |
CN2767722Y (en) * | 2004-10-20 | 2006-03-29 | 深圳市风百胜风机制造有限公司 | Highly effective low-noise condensing axial flow fan of air conditioner for automobile |
CN101113740A (en) * | 2006-07-27 | 2008-01-30 | 西北工业大学 | Vane of axial-flow electric fan and manufacturing method thereof |
CN101863306A (en) * | 2010-03-18 | 2010-10-20 | 西北工业大学 | Omnidirectional vectored thrust cycloidal propeller |
CN101936308A (en) * | 2010-09-12 | 2011-01-05 | 美的集团有限公司 | Fan blade |
CN102116315A (en) * | 2011-03-04 | 2011-07-06 | 美的集团有限公司 | Fan blade |
CN103291561A (en) * | 2013-05-06 | 2013-09-11 | 南京航空航天大学 | Wind turbine blade with split winglet at apex |
CN106050739A (en) * | 2016-07-22 | 2016-10-26 | 西安航空制动科技有限公司 | High-performance wing section for cooling fan |
CN106438470A (en) * | 2016-11-03 | 2017-02-22 | 合肥华凌股份有限公司 | Axial-flow fan and refrigeration equipment |
CN110821886A (en) * | 2019-11-27 | 2020-02-21 | 四川长虹空调有限公司 | Axial fan and air condensing units |
CN112360811A (en) * | 2020-10-23 | 2021-02-12 | 浙江三新科技有限公司 | Airfoil type design of centrifugal fan blade with high lift-drag ratio |
-
2021
- 2021-06-08 CN CN202110634581.4A patent/CN113250997B/en active Active
Patent Citations (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2003120589A (en) * | 2001-10-15 | 2003-04-23 | Yanmar Co Ltd | Radiator fan and engine cooling device using it |
CN1526957A (en) * | 2003-03-05 | 2004-09-08 | 汉�空调株式会社 | Axial-flow fan |
US20040175269A1 (en) * | 2003-03-05 | 2004-09-09 | Halla Climate Control Corporation | Axial-flow fan |
CN2767722Y (en) * | 2004-10-20 | 2006-03-29 | 深圳市风百胜风机制造有限公司 | Highly effective low-noise condensing axial flow fan of air conditioner for automobile |
CN101113740A (en) * | 2006-07-27 | 2008-01-30 | 西北工业大学 | Vane of axial-flow electric fan and manufacturing method thereof |
CN101863306A (en) * | 2010-03-18 | 2010-10-20 | 西北工业大学 | Omnidirectional vectored thrust cycloidal propeller |
CN101936308A (en) * | 2010-09-12 | 2011-01-05 | 美的集团有限公司 | Fan blade |
CN102116315A (en) * | 2011-03-04 | 2011-07-06 | 美的集团有限公司 | Fan blade |
CN103291561A (en) * | 2013-05-06 | 2013-09-11 | 南京航空航天大学 | Wind turbine blade with split winglet at apex |
CN106050739A (en) * | 2016-07-22 | 2016-10-26 | 西安航空制动科技有限公司 | High-performance wing section for cooling fan |
CN106438470A (en) * | 2016-11-03 | 2017-02-22 | 合肥华凌股份有限公司 | Axial-flow fan and refrigeration equipment |
CN110821886A (en) * | 2019-11-27 | 2020-02-21 | 四川长虹空调有限公司 | Axial fan and air condensing units |
CN112360811A (en) * | 2020-10-23 | 2021-02-12 | 浙江三新科技有限公司 | Airfoil type design of centrifugal fan blade with high lift-drag ratio |
Non-Patent Citations (2)
Title |
---|
叶立等: "汽车发动机冷却风扇气动性能研究和优化", 《能源工程》, no. 05, 20 October 2018 (2018-10-20) * |
柳品等: "小型轴流风扇内部流动特性研究", 《浙江理工大学学报》, no. 05, 10 September 2010 (2010-09-10) * |
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CN113250997B (en) | 2022-11-18 |
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