CN106050739A - High-performance wing section for cooling fan - Google Patents
High-performance wing section for cooling fan Download PDFInfo
- Publication number
- CN106050739A CN106050739A CN201610585380.9A CN201610585380A CN106050739A CN 106050739 A CN106050739 A CN 106050739A CN 201610585380 A CN201610585380 A CN 201610585380A CN 106050739 A CN106050739 A CN 106050739A
- Authority
- CN
- China
- Prior art keywords
- aerofoil profile
- wing section
- performance
- fan
- chord length
- 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
-
- 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
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
Abstract
The invention provides a high-performance wing section for a cooling fan. The maximum thickness is 12% of the chord length of the wing section. The position with the maximum thickness is located at the 30% chord length away from a leading edge. The maximum camber is 5% of the chord length. The position with the maximum camber is located at the 34% length away from the leading edge. When an origin of a coordinate system where the wing section is located is a leading edge point of the wing section, the X-axis and a chord line coincide, the X-axis points to a trailing edge of the wing section from the leading edge of the wing section, and the Y-axis is perpendicular to the X-axis and points to the curving direction of the mean camber line of the wing section. Coordinates corresponding to the upper surface and the lower surface of the wing section are given, and an interpolation method is adopted for connecting all coordinate points, so that the high-performance wing section for the cooling fan is obtained. The high-performance wing section can well adapt to the special working condition of a low-rotating-speed fan with the small work Reynolds number, moreover, after the high-performance wing section is applied to a practical fan blade, the efficiency of the fan can be improved remarkably, and noise of the fan is lowered. The increment of the lift-drag ratio can reach 20-40%, the strength is better, and the high-performance wing section is more suitable for practical machining and using.
Description
Technical field
The present invention relates to blower fan field, specifically a kind of cooling fan high-performance aerofoil profile.
Background technology
High-performance aerofoil profile, refers to aerofoil profile and has bigger lift-drag ratio under specific operating mode.Lift-drag ratio=the wing of aerofoil profile
Type lift/profile drag, this value is the biggest, shows that the pneumatic combination property of this aerofoil profile is the best, is specifically related to for low rotary speed fan,
The operating Reynolds number actual condition less than 106 and the aerofoil profile that designs
Along with the development of industrial technology, low rotary speed fan application in resident living with commercial production is more and more extensive,
Such as ceiling fan, air-conditioning fan, cooling fan etc..Fan blade is to determine the critical piece of fan performance, and the section shape of blade
(aerofoil profile) is again the key determining fan blade performance.Existing multiple aerofoil profile, the most state-of-the-art aerofoil profile in available data document
No more than the aircraft wing aerofoil profile used in aircraft industry, other industrial circle typically uses existing aviation aerofoil profile, and to the wing
The research of type puts into seldom.But owing to using the difference of the aspects such as the difference of condition, mainly Reynolds number, (aviation aerofoil profile works
Reynolds number is generally higher than 106), therefore use existing aviation aerofoil profile to do fan blade section shape, aerofoil profile can not be given full play to
Fine piece of writing is used.The existing aerofoil profile that low rotary speed fan is used is bad with actual condition matching, limits the raising of fan efficiency, and one
Determine to cause in degree the waste of resource.
A kind of car engine airfoil type oblique flow cooling is disclosed in the patent that Authorization Notice No. is CN 102945292 B
The determination method of fan；
A kind of airfoil type fan leaf and fan is disclosed in the innovation and creation of Publication No. CN 104295527 A；
A kind of fan high-performance aerofoil profile is disclosed in the innovation and creation of Publication No. CN 105351248 A；
A kind of airfoil type fan leaf and fan is disclosed in the patent that notification number is CN 204186641 U；
One group of fan variable curvature arc uniform thickness is disclosed in the innovation and creation of Application No. CN201210038403.6
Plate aerofoil profile；
AIRFOIL FOR HIGH EFFICIENCY/HIGH LIFT is disclosed in the patent of Patent No. 4692098
FAN；
FLADE FAN WITH DIFFERENT INNER AND is disclosed in the patent of Patent No. US7758303B1
OUTER AIRFOIL STAGGER ANGLES AT A SHROUD THERE BETWEEN；
A kind of FAN AIRFOIL SHEATH is disclosed in the innovation and creation of Publication No. US2011/0182740 A1；
A kind of FAN BLADE WITH is disclosed in the innovation and creation of Publication No. US2014/0154083 A1
FLEXIBLE AIRFOIL WING
A kind of AIRFOIL FOR BLADE is disclosed in the innovation and creation of Publication No. US2015/0037164 A1；
A kind of AIRFOIL WITH is disclosed in the innovation and creation of Publication No. US2016/00033048 A1
THICKENED BOOT AND FAN AND ENGINE INCORPORATING SAME。
One of which fan high-performance aerofoil profile (application publication number: CN 105351248 A) is bigger with application claims
Lift-drag ratio closest to, but its lift-drag ratio can not meet application claims, and implementation method is different.
Summary of the invention
Aerofoil profile by overcoming low rotary speed fan blade present in prior art to be used is the best with actual condition matching
Deficiency, the present invention proposes a kind of cooling fan high-performance aerofoil profile.
The maximum gauge of the present invention is the 12% of aerofoil profile chord length, and maximum gauge position is at leading edge 30% chord length, maximum
Camber is the 5% of chord length, and maximum camber position is at leading edge 34%.
When chord length is 100, the equation of aerofoil profile upper surface is:
Y=0.017+0.54x-2.081x2+4.562x3-3.269x4+1.023x5
When chord length is 100, the equation of aerofoil profile lower surface is:
Y=-0.005-0.546x+7.267x2-8.0647x3+9.2169x4-11.129x5+13.086x6
When the leading edge point that initial point is aerofoil profile of aerofoil profile place coordinate system, X-axis overlaps with the string of a musical instrument, and direction is referred to by aerofoil profile leading edge
To airfoil trailing edge, Y-axis is perpendicular to X-axis and points to the direction of airfoil mean line bending.
When the chord length of described aerofoil profile is 1, the coordinate corresponding to the upper and lower surface of aerofoil profile is as follows:
Use interpolation method each coordinate points to be connected, i.e. obtain cooling down fan high-performance aerofoil profile.
The present invention can be good at mating the special operation condition that low rotary speed fan operating Reynolds number is little, and is being applied to reality
After in fan blade, it is possible to significantly increase fan efficiency, reduce fan noise.
The present invention, from air-foil research, first combines the applying working condition of low rotary speed fan, uses aircraft industry
Aerodynamic analysis technology, designs and mates good high performance fan specific aerofoil profile with fan actual condition.Through theory analysis,
The actual application of numerical simulation, experimental verification and fan, designs a kind of cooling fan high-performance aerofoil profile.
The present invention uses the aviation aerodynamic two dimension correlation theory of Low Speed Airfoil, principle and method, in conjunction with this
The actually used working condition of bright aerofoil profile, have devised the fan aerofoil profile of high lift-drag ratio.
From Fig. 3, Fig. 4, Fig. 5, Fig. 6 and Biao 1, when design lift coefficient (C L≤0.7), the liter of aerofoil profile of the present invention
The lift-drag ratio of resistance existing CLARK-Y aerofoil profile frequently is big, and relative thickness of airfoil of the present invention is more than CLARK-Y aerofoil profile, intensity
More preferably, it is more suitable for actual processing to use.It addition, the lift-drag ratio of aerofoil profile of the present invention is also than the lift-drag ratio of existing RAF 6E aerofoil profile
The most much bigger.In a word, the performance (lift-drag ratio) of aerofoil profile of the present invention is higher than the liter of existing traditional airfoil (RAF-6E and CLARK-Y)
Resistance ratio, lift-drag ratio increment is up to 20～40%.
Table 1 present invention contrasts with other aerofoil profile lift-drag ratios
Accompanying drawing explanation
Fig. 1 is the generalized section of fan high-performance aerofoil profile.
Fig. 2 is the outline drawing of fan high-performance aerofoil profile.
Fig. 3 is lift CL～the resistance CD curve of different airfoil profiles；Wherein: reynolds number Re=6.5 × 10 of Fig. 3 a5, Fig. 3 b
Reynolds number Re=9.7 × 105, reynolds number Re=1.3 × 10 of Fig. 3 c4。
Fig. 4 is lift-drag ratio CL/CD～the lift CL curve of different airfoil profiles, wherein: reynolds number Re=6.5 × 10 of Fig. 4 a5；
Reynolds number Re=9.7 × 10 of Fig. 4 b5；Reynolds number Re=1.3 × 10 of Fig. 4 c4。
Fig. 5 is that the Theoretical Calculation lift-drag ratio of aerofoil profile of the present invention compares with wind tunnel experiment lift-drag ratio, wherein: the Reynolds number of Fig. 5 a
Re=6.5, wind speed V=20m/s × 105；Reynolds number Re=9.7 × 10 of Fig. 5 b5, wind speed V=30m/s；The reynolds number Re of Fig. 5 c
=1.3 × 104, wind speed V=40m/s.
Fig. 6 is that the design of aerofoil profile of the present invention calculates the comparison that pressure distribution is distributed with experimental pressure, wherein: the Reynolds of Fig. 6 a
Number Re=6.5 × 105, wind speed V=20m/s；Reynolds number Re=9.7 × 10 of Fig. 6 b5, wind speed V=30m/s；The Reynolds number of Fig. 6 c
Re=1.3 × 104, wind speed V=40m/s.
In figure:
1. aerofoil profile leading edge；2. aerofoil profile upper surface；3. aerofoil profile lower surface；4. the aerofoil profile string of a musical instrument；5. airfoil trailing edge；The wing the most of the present invention
Type；8.NACA0012 aerofoil profile；9.RAF-6E aerofoil profile；10.CLARK-Y aerofoil profile；11. test values；12. upper surface value of calculation；13. times
Surface value of calculation；The test value of 14. upper surfaces；The test value of 15. lower surfaces；F. aerofoil profile maximum camber；Xf. aerofoil profile maximum camber
The abscissa value at place；C. chord length；T. aerofoil profile maximum camber；Xt. the abscissa value at aerofoil profile maximum camber, the 6.NACA4412 wing
Type.
Detailed description of the invention
The present embodiment is a kind of cooling fan high-performance aerofoil profile, and its design principle is: use pneumatic point of aircraft industry
Analysis technology, designs and mates good high performance fan specific aerofoil profile with fan actual condition.Main performance due to aerofoil profile
It is heavily dependent on its upper and lower surface or the shape of mean camber line, especially Low Speed Airfoil, therefore by research further
The rule characteristic on the upper and lower surface of the high performance fans special airfoil of design, gives fan high-performance aerofoil profile upper and lower surface
The regularity of distribution, satisfied equation and shape, see Fig. 1.
According to above-mentioned design principle, the present embodiment proposes a kind of high performance fans aerofoil profile being named as 514-1.This wing
The maximum gauge of type is the 12% of aerofoil profile chord length, and maximum gauge position is at leading edge 30% chord length, and maximum camber is chord length
5%, maximum camber position is at leading edge 34%.
When definition chord length is 100, the equation of aerofoil profile upper surface is:
Y=0.017+0.54x-2.081x2+4.562x3-3.269x4+1.023x5
When definition chord length is 100, the equation of aerofoil profile lower surface is:
Y=-0.005-0.546x+7.267x2-8.0647x3+9.2169x4-11.129x5+13.086x6
The leading edge point that initial point is aerofoil profile of definition aerofoil profile place coordinate system, X-axis overlaps with the string of a musical instrument, and direction is referred to by aerofoil profile leading edge
To airfoil trailing edge, Y-axis is perpendicular to X-axis and points to the direction of airfoil mean line bending.
When the chord length of described aerofoil profile is 1, then the coordinate corresponding to the upper and lower surface of aerofoil profile is as follows:
Use interpolation method each coordinate points to be connected, i.e. obtain the cooling fan high-performance aerofoil profile of the present embodiment, see Fig. 2.
Claims (3)
1. a cooling fan high-performance aerofoil profile, it is characterised in that the maximum gauge of described cooling fan high-performance aerofoil profile
For the 12% of aerofoil profile chord length, maximum gauge position is at leading edge 30% chord length, and maximum camber is the 5% of chord length, maximum camber
Position is at leading edge 34%.
2. cool down fan high-performance aerofoil profile as claimed in claim 1, it is characterised in that
When chord length is 100, the equation of aerofoil profile upper surface is:
Y=0.017+0.54x-2.081x2+4.562x3-3.269x4+1.023x5
When justice chord length is 100, the equation of aerofoil profile lower surface is:
Y=-0.005-0.546x+7.267x2-8.0647x3+9.2169x4-11.129x5+13.086x6
When the leading edge point that initial point is aerofoil profile of aerofoil profile place coordinate system, X-axis overlaps with the string of a musical instrument, and aerofoil profile is pointed to by aerofoil profile leading edge in direction
Trailing edge, Y-axis is perpendicular to X-axis and points to the direction of airfoil mean line bending.
3. cool down fan high-performance aerofoil profile as claimed in claim 1, it is characterised in that
When the chord length of described aerofoil profile is 1, then the coordinate corresponding to the upper and lower surface of aerofoil profile is as follows:
Use interpolation method each coordinate points to be connected, i.e. obtain cooling down fan high-performance aerofoil profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610585380.9A CN106050739A (en) | 2016-07-22 | 2016-07-22 | High-performance wing section for cooling fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610585380.9A CN106050739A (en) | 2016-07-22 | 2016-07-22 | High-performance wing section for cooling fan |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106050739A true CN106050739A (en) | 2016-10-26 |
Family
ID=57417769
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610585380.9A Pending CN106050739A (en) | 2016-07-22 | 2016-07-22 | High-performance wing section for cooling fan |
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| Country | Link |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107489658A (en) * | 2017-08-31 | 2017-12-19 | 中国航天空气动力技术研究院 | Electric fan noise-reduction method and improved blade of electric fan structure based on blade remodeling |
| CN108583847A (en) * | 2018-04-26 | 2018-09-28 | 陈俊胤 | A kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft |
| CN109726462A (en) * | 2018-12-24 | 2019-05-07 | 北京理工大学 | A kind of angle of attack method for quickly identifying suitable for aerofoil profile |
| CN110555214A (en) * | 2018-05-30 | 2019-12-10 | 中国航发商用航空发动机有限责任公司 | compressor blade profile construction method and compressor blade |
| 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 |
| CN112576546A (en) * | 2020-12-15 | 2021-03-30 | 华中科技大学 | Optimization method of non-uniform-thickness airfoil axial flow blade |
| CN113250997A (en) * | 2021-06-08 | 2021-08-13 | 浙江三新科技有限公司 | Fan blade |
| CN114718903A (en) * | 2022-04-19 | 2022-07-08 | 成都航空职业技术学院 | High-performance wing section for heat dissipation axial flow fan |
| CN115076157A (en) * | 2022-08-19 | 2022-09-20 | 中国航发沈阳发动机研究所 | Final-stage stator blade of fan compressor of aircraft engine |
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| EP1619392A2 (en) * | 2004-07-21 | 2006-01-25 | Delta T Corporation | Fan blades |
| CN102094848A (en) * | 2011-03-22 | 2011-06-15 | 上海交通大学 | Airfoil for large-scale industrial high-pressure ratio axial flow compressor |
| US20150037164A1 (en) * | 2012-04-03 | 2015-02-05 | Delta Corporation | Airfoil for fan blade |
| CN105351248A (en) * | 2015-12-17 | 2016-02-24 | 新昌县三新空调风机有限公司 | High-performance airfoil for fan |
| CN205203371U (en) * | 2015-12-12 | 2016-05-04 | 中国航空工业集团公司西安飞机设计研究所 | Airborne propeller blades , screw and aircraft |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1619392A2 (en) * | 2004-07-21 | 2006-01-25 | Delta T Corporation | Fan blades |
| CN102094848A (en) * | 2011-03-22 | 2011-06-15 | 上海交通大学 | Airfoil for large-scale industrial high-pressure ratio axial flow compressor |
| US20150037164A1 (en) * | 2012-04-03 | 2015-02-05 | Delta Corporation | Airfoil for fan blade |
| CN205203371U (en) * | 2015-12-12 | 2016-05-04 | 中国航空工业集团公司西安飞机设计研究所 | Airborne propeller blades , screw and aircraft |
| CN105351248A (en) * | 2015-12-17 | 2016-02-24 | 新昌县三新空调风机有限公司 | High-performance airfoil for fan |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107489658A (en) * | 2017-08-31 | 2017-12-19 | 中国航天空气动力技术研究院 | Electric fan noise-reduction method and improved blade of electric fan structure based on blade remodeling |
| CN108583847A (en) * | 2018-04-26 | 2018-09-28 | 陈俊胤 | A kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft |
| CN110555214A (en) * | 2018-05-30 | 2019-12-10 | 中国航发商用航空发动机有限责任公司 | compressor blade profile construction method and compressor blade |
| CN110555214B (en) * | 2018-05-30 | 2023-08-11 | 中国航发商用航空发动机有限责任公司 | Construction method of blade profile of compressor blade and compressor blade |
| CN109726462A (en) * | 2018-12-24 | 2019-05-07 | 北京理工大学 | A kind of angle of attack method for quickly identifying suitable for aerofoil profile |
| CN109726462B (en) * | 2018-12-24 | 2021-05-04 | 北京理工大学 | Attack angle quick identification method suitable for wing profile |
| 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 |
| CN112576546A (en) * | 2020-12-15 | 2021-03-30 | 华中科技大学 | Optimization method of non-uniform-thickness airfoil axial flow blade |
| CN113250997A (en) * | 2021-06-08 | 2021-08-13 | 浙江三新科技有限公司 | Fan blade |
| CN114718903A (en) * | 2022-04-19 | 2022-07-08 | 成都航空职业技术学院 | High-performance wing section for heat dissipation axial flow fan |
| CN115076157A (en) * | 2022-08-19 | 2022-09-20 | 中国航发沈阳发动机研究所 | Final-stage stator blade of fan compressor of aircraft engine |
| CN115076157B (en) * | 2022-08-19 | 2022-11-22 | 中国航发沈阳发动机研究所 | Last-stage stator blade of fan compressor of aircraft engine |
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