CN113250997B - Fan blade - Google Patents
Fan blade Download PDFInfo
- Publication number
- CN113250997B CN113250997B CN202110634581.4A CN202110634581A CN113250997B CN 113250997 B CN113250997 B CN 113250997B CN 202110634581 A CN202110634581 A CN 202110634581A CN 113250997 B CN113250997 B CN 113250997B
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- CN
- China
- Prior art keywords
- blade
- fan
- ratio
- hub
- root
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
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- 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 0.1m 2 Root setting angle 55.12, tip setting angle 24.3. Wherein, the hub diameter is 132mm, and the impeller diameter is 1443mm. For a fan with a certain hub ratio and blade chord length, there is an optimum number of bladesThe number of the invented 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.
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 the proper installation angle beta is determined A Thereby 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 hub ratio upsilon and outer diameter D, must be reasonably selected t And 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 upsilon
In designing an axial flow fan, it is necessary to determine a hub ratio υ = D h /D t (D h -hub diameter; d t -impeller outer diameter). The hub ratio is an important structural parameter. 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 D t
D t Directly affects the performance and structure of the fan. The impeller size D of the fan at a given speed, given the required full fan pressure and flow t Is also substantially determined.
3) Number of blades Z
For the selected isolated blade profile, the lift coefficient c is determined under the rated working condition y Since 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 problem solved by the invention is 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 0.1m 2 Root 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 1443mm.
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 a blade root to the chord length of a blade tip) is 1.25, and the surface area of each blade is 0.1m 2 Root setting angle 55.12, tip setting angle 24.3.
The blade airfoil is formed by curves of an upper surface and a lower surface, and the geometrical size of the blade airfoil 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 it should not be understood that the present invention is limited to the above description and the accompanying drawings.
Claims (3)
1. A fan blade, characterized by: hub ratio of 0.091, root tip ratio of 1.25, blade surface area of 0.1m 2 A root setting angle of 55.12 and a tip setting angle of 24.3;
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:
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)
2. a fan blade according to claim 1, wherein: the hub diameter is 132mm, and the impeller diameter is 1443mm.
3. A fan blade according to claim 1, wherein: the number of the blades is 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110634581.4A CN113250997B (en) | 2021-06-08 | 2021-06-08 | Fan blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110634581.4A CN113250997B (en) | 2021-06-08 | 2021-06-08 | Fan blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113250997A CN113250997A (en) | 2021-08-13 |
| CN113250997B true CN113250997B (en) | 2022-11-18 |
Family
ID=77186984
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110634581.4A Active CN113250997B (en) | 2021-06-08 | 2021-06-08 | Fan blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113250997B (en) |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3919496B2 (en) * | 2001-10-15 | 2007-05-23 | ヤンマー株式会社 | RADIATOR FAN AND ENGINE COOLING DEVICE USING THE SAME |
| KR100820856B1 (en) * | 2003-03-05 | 2008-04-11 | 한라공조주식회사 | 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 | Axial flow fan blade and manufacturing method thereof |
| CN101863306B (en) * | 2010-03-18 | 2012-01-04 | 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 |
| CN106438470B (en) * | 2016-11-03 | 2019-03-29 | 合肥华凌股份有限公司 | Aerofoil 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
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| Publication number | Publication date |
|---|---|
| CN113250997A (en) | 2021-08-13 |
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