CN101603514A - Bionic coupling blade of aerogenerator - Google Patents
Bionic coupling blade of aerogenerator Download PDFInfo
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- CN101603514A CN101603514A CNA2009100672154A CN200910067215A CN101603514A CN 101603514 A CN101603514 A CN 101603514A CN A2009100672154 A CNA2009100672154 A CN A2009100672154A CN 200910067215 A CN200910067215 A CN 200910067215A CN 101603514 A CN101603514 A CN 101603514A
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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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Abstract
The present invention relates to a kind of bionic coupling blade of aerogenerator, belong to the wind power plant field.The present invention is a kind of bionic coupling blade of aerogenerator structure, and promptly aerofoil profile (configuration) is coupled with blade structure.By to typical birds (Asio otus etc.) wing wing plumage study on arrangement, based on the biological function coupling principle,, form bionical coupled structure surface to leading edge in the blade exhibition with the sequential arrangement of aerofoil profile, make it have the characteristic of high-lift lower resistance.The exhibition of blade can limit with crest, trough and three values of wavelength to the leading edge form, and its trough is made as the basic chord length C of aerofoil profile to the distance of trailing edge, crest to the distance of trailing edge be the basic chord length C of aerofoil profile (1.025～1.20) doubly; Trough to trough (crest is to crest) apart from wavelength l be the basic chord length C of aerofoil profile (0.25～1) doubly.The objective of the invention is to reduce the eddy current that the blade blade face is produced, improve the blade working efficiency, effectively reduce the blade construct noise.
Description
Technical field:
The present invention relates to a kind of wind power generator oar blade structure, belong to the wind power plant field.
Background technique:
Improve the utilization ratio of wind energy conversion system wind energy, be the target that people constantly pursue always.
CN03134065.2 and CN 200952450Y have proposed to open fumarole on blade surface, and jet direction is the tangent direction of impeller rotation, i.e. so-called " push type working principle ", it has reduced the starting wind velocity of wind energy conversion system, thereby has enlarged the operating range of wind energy conversion system.But also have some problems when implementing this technology, for example under the feather situation, any slight change of propeller pitch angle all can influence on the blade with respect to the jet direction of plane of rotation, and this obviously can influence performance performance of wind energy conversion system.
CN 1415854A adopts the mode that wing fence is set on the blade windward side, make wing fence consistent with the blade cross-sectional direction, vertical with the blade face, utilize wing fence the barrier effect of air-flow to be reduced the radial air flow of blade, more be converted into Driving force so that airflow kinetic energy loss reduces, in fact but reduced the Security of blade structure and the stability of its function on blade but wing fence is set to blade.
Yet, with regard to blade, air-flow acts on the blade face down with the wind, the active force of air-flow is decomposed into the pressure of forward and the thrust of side direction, and this lateral thrust shows as the Driving force that blade rotates, because traditional blade blade face is smooth, make air-flow on the blade face form Radial Flow from middle mind-set blade tip, such air-flow can make the blade decrease in efficiency, also makes must keep certain distance between per two typhoon power generators, descends with the working efficiency of avoiding bringing because of vortes interference.Therefore the present invention has proposed new wind wheel blade organization plan in order to overcome the deficiency of above-mentioned aerofoil profile fan blade on the basis of existing aviation wing.
Summary of the invention
The object of the invention is to provide a kind of bionic coupling blade of aerogenerator, to reduce the eddy current that the blade blade face is produced, improves the working efficiency of blade and has effectively reduced the construct noise of blade.
Traditional idea and classical theory think that smooth body surface helps to reduce the resistance of fluid, but actual conditions are not exclusively like this, and in the process to drag reduction understanding, bionic research has played promoting effect.The animal and plant of occurring in nature has experienced the evolution in 1 years, and its structure and function have reached the perfect degree that is close to.Its form, structure and constouctional material have the system of maximum adaptation and harmony by mutual optimization, coupling formation to living environment, and form the function of many excellences, as wear-resisting, antifatigue, drag reduction noise reduction etc.For example, some canonical biometrics have excellent drag reduction decrease of noise functions by the coupling mechanism realization, and being commonly called as of cat owl Shi Owl class is mousing expert famous in the birds.It is almost voiceless sound generation in flight course, makes the very sensitive muroid of the sense of hearing hard to guard against to it, thereby is described as nature " concealed aircraft " at night.Pass through and arrange to constitute " pectination " leading edge with these characteristics distinctive wing pterylosis of De Shi Owl class that adapts, fluid is flowed along the direction of wing plumage, restriction flows to the exhibition in whirlpool and has brought into play effect to the drag reduction noise reduction high-lift of the ， Dui Owl class that flows, and also can weaken the sound that air turbulence produces simultaneously.The Asio otus live body is pounced on the food test and is shown, wing has " pectination " leading edge ratio not have the average noise reduction of " pectination " leading edge to reach 7dB, its achievement also provides good reference for bionical coupled surface drag reduction theory and technology in the research flowing medium, to the drag reduction synergy of research fan blade, bring into play usefulness to greatest extent basic data is provided.
The present invention uses modern bionics technology based on surface and the dynamics between the medium, vibration and tribology and the thermodynamic study of moving element, sums up by a large amount of optimization experiment and proposes following bionic coupling blade of aerogenerator structure of the present invention:
The present invention realizes goal of the invention like this, and accompanying drawings is as follows:
A kind of bionic coupling blade of aerogenerator, by the sequential arrangement of aerofoil profile, form the bionical coupled structure surface of ginseng in the blade exhibition to leading edge according to Owl class and pinion leading edge, the blade exhibition limits with crest, trough and three values of wavelength to the bionical coupled structure surface of leading edge, its trough is made as the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.025～1.20 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.25～1 times of the basic chord length C of aerofoil profile to trough and crest to crest apart from wavelength l.
The present invention compared with prior art, bionical coupling leading edge form has reduced the area of leading edge windward side effectively, reduces the pressure drag of leading edge; Simultaneously the exhibition of blade to, form bionical coupled structure surface regularly, bionical coupled structure surface mainly shows as bionical coupled structure surface to the control behavior in wall boundary layer the wall low velocity fluid has been carried out effective cutting, the exhibition that has suppressed low velocity fluid is to motion, weakened the unstability of the low speed band that forms when turbulent flow is burst, thereby further weakened the turbulent flow intensity of bursting, reduced energy loss.It has not only improved the ratio of lift coefficient to drag coefficient of blade, and has effectively reduced the construct noise of blade.
Description of drawings
Fig. 1 (a) is the bionic coupling blade structural drawing;
Fig. 1 (b) is the aerofoil profile arrangement mode;
Fig. 1 (c) is a blade structure side view;
Fig. 1 (d) is the A-A sectional drawing of Fig. 1 (c);
Fig. 1 (e) is the B-B sectional drawing of Fig. 1 (c).
Fig. 2 (a) is the smooth blade structural drawing of leading edge;
Fig. 2 (b) is the aerofoil profile arrangement mode.
1 is the aerofoil profile that is positioned at trough among the figure, the 2nd, be positioned at the aerofoil profile of crest.
Embodiment
The blade embodiment who provides below in conjunction with accompanying drawing is described in further detail blade of the present invention.
Prey on noiseless flight by the research Jie Shi Owl class of Dian type Sheng Wu Owl class drag reduction noise reduction coupling function in the fluid medium and depend primarily on the exclusive sequential arrangement of its high lift hardware plumage, form a class seemingly in the bionical coupled structure surface of Owl class and pinion leading edge in the blade exhibition to leading edge, it has high-lift lower resistance characteristic.Blade exhibition can limit with crest, trough and three values of wavelength to the leading edge form, and its trough is made as the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is the basic chord length C of aerofoil profile (1.025～1.20) times to the distance of trailing edge; Trough to trough (crest is to crest) apart from wavelength l be the basic chord length C of aerofoil profile (0.25～1) doubly.
This bionical coupling form is consistent with the blade cross-sectional direction in blade windward side leading edge, and is vertical with the blade face.The objective of the invention is to reduce the eddy current that the blade blade face is produced, improve the working efficiency of blade and effectively reduced the construct noise of blade.
With reference to Fig. 1,2, with NACA 0018 (the NACA:(U.S.) NACA) aerofoil profile is example, in reynolds number Re=2.5 * 10
5(Re=VC/v, V wherein: speed of incoming flow, C: chord length, v: fluid motion viscosity) the blade exhibition is to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.025 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.25 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 3.7% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 6.1%.
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.025 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 1.0 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 5.3% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 8.9%.
Embodiment 3
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.2 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.25 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 10.1% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 13.7%.
Embodiment 4
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.2 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 1.0 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 18.4% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 20.7%.
Embodiment 5
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.025 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.33 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 3.5% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 18.3%.
Embodiment 6
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.1 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.33 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 8.2% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 20%.
Embodiment 7
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.05 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.33 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 14.2% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 18%.
Embodiment 8
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.075 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.33 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 19.8% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 19.6%.
Embodiment 9
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.05 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.25 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 9% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 22%.
Embodiment 10
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.05 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.5 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 7.2% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 28.5%.
Embodiment 11
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.05 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.75 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 9.7% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 13.2%.
Embodiment 12
With reference to Fig. 1,2, be example with NACA 0018, in Re=2.5 * 10
5, blade is opened up to the bionical coupled structure surface of leading edge, and its trough is decided to be the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.05 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 1.0 times of the basic chord length C of aerofoil profile to trough (crest is to crest) apart from wavelength l; (Fig. 1) that bionical coupling leading edge arranged increased by 6% than the lift of leading edge smooth (Fig. 2), and resistance has reduced 8.132%.
Certainly, above-mentioned explanation is not to be limitation of the present invention, and the present invention also is not limited to above-mentioned giving an example; those skilled in the art; in essential scope of the present invention, the variation of making, remodeling, interpolation or replacement also should belong to protection scope of the present invention.
Claims (1)
1, a kind of bionic coupling blade of aerogenerator, it is characterized in that, by the sequential arrangement of aerofoil profile, form the bionical coupled structure surface of ginseng in the blade exhibition to leading edge according to Owl class and pinion leading edge, the blade exhibition limits with crest, trough and three values of wavelength to the bionical coupled structure surface of leading edge, its trough is made as the basic chord length C of aerofoil profile to the distance of trailing edge, and crest is 1.025～1.20 times of the basic chord length C of aerofoil profile to the distance of trailing edge; Trough is 0.25～1 times of the basic chord length C of aerofoil profile to trough and crest to crest apart from wavelength l.
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| Application Number | Priority Date | Filing Date | Title |
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| CNA2009100672154A CN101603514A (en) | 2009-07-03 | 2009-07-03 | Bionic coupling blade of aerogenerator |
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| CNA2009100672154A CN101603514A (en) | 2009-07-03 | 2009-07-03 | Bionic coupling blade of aerogenerator |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110043510A (en) * | 2018-05-18 | 2019-07-23 | 广东美的制冷设备有限公司 | The blade of wind wheel |
| CN110397060A (en) * | 2019-07-12 | 2019-11-01 | 河北工业大学 | A kind of biomimetic features antiscour pile foundation |
| CN112848378A (en) * | 2020-12-26 | 2021-05-28 | 吉林大学 | Fiber reinforced composite blade material with bionic structure and preparation method thereof |
| CN112943525A (en) * | 2021-03-29 | 2021-06-11 | 西安交通大学 | Bionic blade structure of coupling wind turbine |
| CN113323796A (en) * | 2021-06-29 | 2021-08-31 | 中国科学院工程热物理研究所 | Bionic leading edge wind power blade and optimal design method |
| CN113669194A (en) * | 2021-08-09 | 2021-11-19 | 中国科学院工程热物理研究所 | Flow separation control method based on bionic concave-convex front edge structure |
| CN113825901A (en) * | 2019-05-16 | 2021-12-21 | 伦敦布鲁内尔大学 | Method for forming additional part of airfoil |
| CN116873187A (en) * | 2023-09-07 | 2023-10-13 | 中国航空工业集团公司沈阳空气动力研究所 | Low-Reynolds-number low-noise bionic coupling wing based on owl wing characteristics |
-
2009
- 2009-07-03 CN CNA2009100672154A patent/CN101603514A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110043510A (en) * | 2018-05-18 | 2019-07-23 | 广东美的制冷设备有限公司 | The blade of wind wheel |
| CN110043510B (en) * | 2018-05-18 | 2024-03-05 | 广东美的制冷设备有限公司 | Blade of wind wheel |
| CN113825901A (en) * | 2019-05-16 | 2021-12-21 | 伦敦布鲁内尔大学 | Method for forming additional part of airfoil |
| CN110397060A (en) * | 2019-07-12 | 2019-11-01 | 河北工业大学 | A kind of biomimetic features antiscour pile foundation |
| CN112848378A (en) * | 2020-12-26 | 2021-05-28 | 吉林大学 | Fiber reinforced composite blade material with bionic structure and preparation method thereof |
| CN112848378B (en) * | 2020-12-26 | 2022-03-29 | 吉林大学 | Fiber reinforced composite blade material with bionic structure and preparation method thereof |
| CN112943525A (en) * | 2021-03-29 | 2021-06-11 | 西安交通大学 | Bionic blade structure of coupling wind turbine |
| CN113323796A (en) * | 2021-06-29 | 2021-08-31 | 中国科学院工程热物理研究所 | Bionic leading edge wind power blade and optimal design method |
| CN113669194A (en) * | 2021-08-09 | 2021-11-19 | 中国科学院工程热物理研究所 | Flow separation control method based on bionic concave-convex front edge structure |
| CN113669194B (en) * | 2021-08-09 | 2023-05-05 | 中国科学院工程热物理研究所 | Flow separation control method based on bionic concave-convex front edge structure |
| CN116873187A (en) * | 2023-09-07 | 2023-10-13 | 中国航空工业集团公司沈阳空气动力研究所 | Low-Reynolds-number low-noise bionic coupling wing based on owl wing characteristics |
| CN116873187B (en) * | 2023-09-07 | 2023-11-14 | 中国航空工业集团公司沈阳空气动力研究所 | Low-Reynolds-number low-noise bionic coupling wing based on owl wing characteristics |
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