Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.

Patents

  1. Advanced Patent Search
Publication numberCN102011710 B
Publication typeGrant
Application numberCN 201010554905
Publication date18 Jul 2012
Filing date23 Nov 2010
Priority date23 Nov 2010
Also published asCN102011710A
Publication number201010554905.5, CN 102011710 B, CN 102011710B, CN 201010554905, CN-B-102011710, CN102011710 B, CN102011710B, CN201010554905, CN201010554905.5
Inventors王同光, 许波峰
Applicant南京航空航天大学
Export CitationBiBTeX, EndNote, RefMan
External Links: SIPO, Espacenet
Wind machine blade
CN 102011710 B
Abstract
The invention relates to a wind machine blade, belonging to the field of wind power generation. The wind machine blade comprises a blade front part and a blade back part; the blade front part is the part from the blade tip part to the blade section (12) with the biggest chord length; the blade back part is the part form the blade section (12) with the biggest chord length to the blade root part; the wind machine blade is characterized in that the blade back part comprises a structure component (9) for mounting blade root and bearing loads of the blade and a pneumatic component (10) for capturing wind energy in turn from inner to outer; a cavity is formed between the structure component (9) and the pneumatic component (10); the shape of the pneumatic component (10) is transitioned from the blade section with the biggest chord length to a pneumatic wing section (2) at the blade root; the specific transition form is obtained by lofting each section wing section at front part of the blade and the pneumatic wing section (2) at the blade root. The wind machine blade of the present invention can use the wind energy in a wind wheel fully, improve the use ratio of the wind energy, and increase the generating capacity of the wind machine.
Claims(3)  translated from Chinese
1. 一种风力机叶片,由叶片前部和叶片后部构成,叶片前部即为叶尖部分到叶片最大弦长截面(12),叶片后部即为叶片最大弦长截面(12)到叶根部分;上述叶片后部由内往外依次包括用于叶根安装并承受叶片载荷的结构部件(9)和用于捕获风能的气动部件(10) 组成;上述结构部件(9)与气动部件(10)之间为空腔;其特征在于:上述气动部件(10)的外形由叶片最大弦长处开始过渡至叶根气动翼型(2)处,具体过渡形式通过叶片前部各截面翼型与叶根气动翼型(2)放样得到;上述气动部件(10)的叶根气动翼型(2)弦长大于结构部件的叶根结构弦长,同时小于叶片最大弦长;上述叶根气动翼型(2)的外形由以下方式决定:叶根气动翼型外形由与结构型外形相切的5个相切圆弧组成,该5个圆弧依次定义为前缘上圆弧(3)、前缘圆弧(4)、前缘下圆弧(5)、后缘下圆弧(7)、后缘上圆弧(6);其中前缘上圆弧(3)与结构型(1)外圆内切,前缘下圆弧(5)与结构型(1)外圆内切, 前缘圆弧(4)与前缘上圆弧(3)和前缘下圆弧(5)都内切,后缘上圆弧(6)的圆心在过结构型(1)圆心且与中性线成60的直线上,与结构型(1)外圆内切,后缘下圆弧(7)圆弧的圆心在过结构型(1)圆心且与中性线成-45的直线上,与结构型(1)外圆外切;上述中性线指过结构型圆心,且垂直于前缘上圆弧(3)和前缘下圆弧(5)的圆心连线;上述后缘下圆弧(7)和后缘上圆弧(6)衔接处形成尾缘厚度(8),尾缘厚度(8)为结构型(1)直径的0. 5%〜1% ;上述叶根气动翼型(2)的相对厚度小于100%。 A wind turbine blade, the front portion of the rear blades and the blade configuration, that is, part of the front portion of the blade tip to the blade chord length of the largest cross-section (12), the rear of the blade maximum chord length of the blade is the cross-section (12) to blade-root portion; the rear of the blade from the inside out and in turn comprising means for 叶根安 withstand structural loading of the blade member (9) for capturing wind energy and pneumatic components (10) consisting of; said structural member (9) and a pneumatic member (10) between the cavity; wherein: shape above pneumatic components (10) to start the transition from blade to blade root chord maximum aerodynamic airfoil (2) of the specific forms of transition through the front of each cross section of the blade airfoil aerodynamic airfoil and blade root (2) The stake obtained; said pneumatic member (10) of the blade root aerodynamic airfoil (2) grow up on the structural component chord blade root chord structure, while less than the maximum chord length of the blade; said blade root pneumatic airfoil (2) is determined by the shape of the following ways: the root airfoil aerodynamic and structural shape by the shape of tangent arcs tangent to 5, followed by the five arc on the leading edge is defined as an arc (3) , the leading edge arc (4), at the leading edge arc (5), at the trailing edge arc (7), the arc on the trailing edge (6); wherein the leading edge of the arc (3) consistent with structure type (1 ) within the cylindrical cut at the leading edge arc (5) and structural (1) cylindrical cut, the leading edge of the arc (4) and on the leading edge of the arc (3) and the leading edge of the next arc (5) They were cut inside the arc on the trailing edge (6) of the center in the past structure type (1) into the center and on a straight line and the neutral line of 60 , and structure type (1) cut in the outer, lower rear edge of the arc ( 7) through the center of the arc in the structure type (1) into the center and on a straight line and the neutral line of -45 , and structure type (1) the outer circumscribed; refers above the neutral line through the structural center, and vertical on the leading edge of the arc (3) and the leading edge of the next arc (5) of the center wire; under the rear edge of the arc (7) and a trailing edge arc (6) converge at the trailing edge thickness is formed (8) , the thickness of the trailing edge (8) of the structure type (1) 0.5% ~ 1% of the diameter; said aerodynamic airfoil blade root (2) the relative thickness of less than 100%.
2.根据权利要求1所述的一种风力机叶片,其特征在于:上述结构部件(9)和叶片前部为一整体;上述气动部件(10)在叶片最大弦长处与结构部件(9)及叶片前部固定连接。 2. A wind turbine blade according to claim 1, wherein: said structural member (9) and the front portion of the blade as a whole; said pneumatic member (10) in the blade maximum chord structural member (9) and fixedly connected to the front of the blade.
3.根据权利要求1所述的一种风力机叶片,其特征在于:上述结构部件(9)的叶根结构型(1)是半径与叶根法兰半径一致的圆形。 3. A wind turbine blade according to claim 1, wherein: said structural member (9) of the blade root structure of type (1) is consistent with the radius of the root circle radius of the flange.
Description  translated from Chinese

一种风力机叶片 A wind turbine blade

技术领域 Technical Field

[0001] 本发明涉及一种风力机叶片,属风力发电领域。 [0001] The present invention relates to a wind turbine blade, it is wind power. 背景技术 Background

[0002] 可再生能源是解决能源危机的最佳途径,而风力发电又是可再生能源行业中发展最迅速、技术最成熟、前景最广阔的行业。 [0002] Renewable energy is the best way to solve the energy crisis, and the wind is the renewable energy industry, the fastest growing, most mature technology, the prospects of the industry's most extensive. 我国幅员辽阔,风能资源十分丰富,随着科学技术的不断进步,风力发电的经济性不断改善,加之我国已把可再生能源作为我国能源战略的重要组成部分,风力发电拥有巨大的潜在市场。 China has a vast wind resources are very rich, with the continuous progress of science and technology, wind power economy continues to improve, coupled with our 已把 renewable energy as an important part of our energy strategy, wind power has a huge potential market.

[0003] 风力机叶片气动效率的高低决定了一款风力机在市场上的优劣,所以风力机叶片气动外形的设计是风力机设计的关键。 [0003] The wind turbine blade determines the level of aerodynamic efficiency of a wind turbine on the market of the merits, so wind turbine blade aerodynamic design is the key wind turbine design. 现在市场主流的大型风力机叶片根部基本都是圆柱体,叶片根部至径向1/5左右处都是近似圆柱体,这样在风轮内部的风能都没有被利用,而且圆柱体对整个尾流流场也会产生影响。 Now the market mainstream large-scale wind turbine blade root basically cylindrical, radial blade root to about 1/5 of the cylinder are approximate, so the wind in the wind wheel inside are not being used, but also the entire cylinder wake the flow field will have an impact. 目前行业内都没有重视该问题,认为叶片根部线速度比较小,而且力臂也比较小,出不出力不会有太大影响。 Currently no attention to the problem within the industry that the blade root line speed is relatively small, and the arm is relatively small, the output will not have much impact not. 因此许多人对叶片的优化都局限于叶片的中部和尖部,不去考虑叶片的根部。 So many people are confined to the optimization of the blade tip and the middle of the blade, do not consider the root of the blade. 利用风力机叶片气动外形优化经典理论即Glauert理论优化的结果在叶根有比较大弦长,但是处于结构和与轮毂连接上的考虑,实际叶片叶根采用圆柱体结构,弦长远小于优化结果。 Use of wind turbine blades aerodynamic shape optimization theory of the classical theory that is Glauert optimal results in a relatively large blade root chord, but in structure and connected to the hub consideration, the actual blade base use cylindrical structure, the long string of less than optimal results.

[0004] 有不少专利是通过流动控制手段来提高叶片气动性能,如加襟翼、前缘带旋转圆柱体、射流控制等。 [0004] There are a lot of patents is through the flow control means to improve the aerodynamic performance of the blades, such as adding flaps, leading edge with a rotating cylinder, the jet control. 对于现在已有的风力机叶片来讲,叶根的气动外形还有可优化可改造的余地,而且能够对提高风轮气动性能有很大作用,但目前国内还未见专门针对叶根设计的提高叶片气动性能的相关技术报道。 For now existing in terms of wind turbine blades, blade root aerodynamic shape also can be engineered to optimize room, but also to improve the aerodynamic performance of wind turbines have a significant role, but the country has not been designed specifically for blade root Related technology is reported to improve the aerodynamic performance of the blade.

发明内容 DISCLOSURE

[0005] 本发明的目的是提供一种可以充分利用风轮内部的风能,提高风能利用效率,增加风力机发电量风力机叶片。 [0005] The object of the present invention is to provide a way to take advantage of the wind wheel inside the wind, wind energy utilization to improve efficiency, increase wind turbine generating capacity of wind turbine blades.

[0006] 一种风力机叶片,由叶片前部和叶片后部构成,叶片前部即为叶尖部分到叶片最大弦长截面,叶片后部即为叶片最大弦长截面到叶根部分;其特征在于:上述叶片后部由内往外依次包括用于叶根安装并承受叶片载荷的结构部件和用于捕获风能的气动部件组成;上述结构部件与气动部件之间为空腔;上述气动部件的外形由叶片最大弦长处开始过渡至叶根气动翼型处,具体过渡形式通过叶片前部各截面翼型与叶根气动翼型放样得到。 [0006] A wind turbine blades, the front portion of the rear of the blade and the blade configuration, that is part of the front tip of the blade to the blade chord length of the largest cross-section, the rear blade chord length is the largest cross-section blade to blade-root portion; it characterized in that: said rear blade comprises a sequence from the inside out and subjected to structural members mounted 叶根安 blade loading for capturing wind energy and pneumatic components; between the structural member and member of the pneumatic chamber; said pneumatic member Shape beginning of the transition from the blade to the maximum chord aerodynamic airfoil at the root, the specific form of transition through the cross section of the front of the blade airfoil obtained aerodynamic airfoil blade root loft.

[0007] 上述叶片前部的外形根据风力机叶片气动外形优化经典理论即Glauert理论得到,能够最大化地捕捉风能。 [0007] the shape of the front portion of the blade wind turbine blade according to the classical theory of aerodynamic shape optimization that is Glauert theory is, to maximize wind capture. 叶片后部的结构部件设计准则是以叶片结构设计为主,气动部件设计准则是以叶片气动设计为主。 Structural component design criteria based on structural design of the rear blade main blade, pneumatic component design criteria are based on the aerodynamic design of the main blade. 这样的设计既能发挥叶根的风能捕捉能力,又能兼顾叶根强大的承载能力。 This design can not only play the root of the wind capture capability, while maintaining the Yegen Jiang large carrying capacity.

[0008] 一种风力机叶片,其特征在于:上述气动部件的叶根气动翼型弦长大于结构部件的叶根结构弦长,同时小于叶片最大弦长;叶根气动翼型的外形由以下方式决定:叶根气动翼型外形由与结构型外形相切的5个相切圆弧组成,该5个圆弧依次定义为前缘上圆弧、前缘圆弧、前缘下圆弧、后缘下圆弧、后缘上圆弧;其中前缘上圆弧与结构型外圆内切, 前缘下圆弧与结构型外圆内切,前缘圆弧与前缘上圆弧和前缘下圆弧都内切,后缘上圆弧的圆心在过结构型圆心且与中性线成60的直线上,与结构型外圆内切,后缘下圆弧的圆心在过结构型圆心且与中性线成-45的直线上,与结构型外圆外切;上述中性线指过结构型圆心,且垂直于前缘上圆弧和前缘下圆弧的圆心连线;上述后缘下圆弧和后缘上圆弧衔接处形成尾缘厚度,尾缘厚度为结构型直径的0. 5%〜1% ;上述叶根气动翼型的相对厚度小于100% ο [0008] A wind turbine blade, wherein: said pneumatic components of the blade root airfoil aerodynamic chord grew up in structural components of the leaf to the root of the chord length, while less than the maximum chord length of the blade; blade root aerodynamic airfoil shape by the following decided: the root airfoil aerodynamic shape and structural shape by the tangent of five tangent arcs, which in turn is defined under 5 arc on the leading edge of the arc, the leading edge of the arc, the leading edge of the arc, under the trailing edge arc, arc on the trailing edge; wherein the inner arc on the leading edge and the outer cutting structural, cut inside the arc and structured under the leading edge of the outer, on the leading edge of the leading edge arc and arc at the leading edge of the arc are cut inside the rear edge of the center of the circle in a straight line through the center of the circle and the structural and the neutral line of 60 , the cut cylindrical inner structure type, under the trailing edge of the center of the arc in the past structure Type center and on a straight line and the neutral line to -45 , and with structural cylindrical outer cutting; refers above the neutral line through the structural center and perpendicular to the leading edge of the arc and the leading edge even under the center of the arc line; arc converge at the arc and the trailing edge at the rear edge of the trailing edge thickness is formed, the trailing edge thickness is 0.5% ~ 1% structural diameter; the relative thickness of the blade root aerodynamic airfoil is less than 100% ο

[0009] 叶根气动翼型的形状与一般的厚翼型类似,上下表面形状的不对称性产生弯度, 提高气动性能。 [0009] The shape of the blade root aerodynamic airfoil similar to a thick airfoil general asymmetry produces curvature of the upper and lower surface of the shape, improve aerodynamic performance. 5个弧形表面的相切连接保证了表面形状曲率半径的连续性,后缘上下圆弧的圆心位置可以有变化,上述位置作为参考值,要保证翼型具有弯度。 Tangentially five curved surface to ensure the continuity of the surface shape of the radius of curvature, the center position of the trailing edge of the vertical arc may have changed, the position as a reference value, to ensure airfoil having a camber. 相对厚度根据实际风场情况而定,年平均风速较大的风场叶根气动翼型相对厚度大,反之则相对厚度小。 The relative thickness of the actual wind farm on the circumstances, the annual average wind speed greater aerodynamic airfoil blade root wind farm is relatively large thickness, otherwise relatively small thickness. 尾缘厚度是由实际生产的工艺决定的,叶片上下面尾缘粘接时必然会产生厚度,而且厚尾缘的翼型比尖尾缘的翼型性能会好。 Trailing edge thickness is determined by the actual production process, would have a thickness below the trailing edge of the blade when bonding, and thick airfoil trailing edge of the airfoil performance will be better than the tip of the trailing edge. 一般的叶片叶根都为圆形,叶片后部大部分为圆柱,风轮旋转时,叶片后部既不能捕捉风能,而且在叶片尾流区产出涡街,破坏流场。 General vane roots are round, most of the blade rear cylinder when the wind wheel rotation, neither rear blades capture wind energy, and the output of the blade wake vortex region, undermining the flow field. 采用叶根气动翼型的气动部件既能捕捉风能,提供风能利用系数,又能改善流场。 Airfoil blade root using pneumatic pneumatic components both capture wind energy, wind energy utilization coefficient provided, but also to improve the flow field.

[0010] 上述结构部件和叶片前部可以为一整体;然后气动部件在叶片最大弦长处与结构部件及叶片前部固定连接。 [0010] the front of the structural member and the blade can be as a whole; then the maximum chord blade pneumatic components and structural parts and fixedly connected to the front portion of the blade. 这样的结构简单,且很容易实现。 Such a structure is simple and easy to implement. 结构部件与叶片前部的整体性,保证了叶片传力的连续,满足结构设计准则。 Structural integrity of the components and the front portion of the blade, ensuring continuous, meet the structural design criteria blade transmission power. 气动部件在外形确定单独制造后粘贴至结构部件上及叶片前部与后部交接处(即最大弦长处)。 Pneumatic components in shape after the individual manufacturing stuck to determine the structural member and the front and rear blade junction (ie, the maximum chord length).

[0011] 上述结构部件的叶根结构翼型可以是半径与叶根法兰半径一致的圆形。 [0011] airfoil blade root structure of the structural member may be consistent with the radius of the root radius of the circular flanges. 该结合便于安装。 The combination of ease of installation.

[0012] 本发明应用范围较广。 [0012] The present invention is a wide range of applications. 可以在叶片设计时叶片前部与后部综合考虑进行设计,也可以在现有圆柱叶根型叶片的基础上,单独设计叶片后部的气动部件,然后将气动部件粘贴至现有叶片上,即本发明可以对现有的叶片进行改造,来提高叶片的气动性能。 The front and rear of the blade can be taken into account when designing the blade design can also be based on the existing cylindrical blade root type blade on the rear of the blades individually designed pneumatic components, pneumatic components and then pasted onto the existing blade, Namely, the present invention can be carried out transformation of existing blades, to improve the aerodynamic performance of the blade.

附图说明 Brief Description

[0013] 图1为本发明实施例叶根翼型示意图。 [0013] FIG. 1 is a schematic view of an airfoil blade root invention implemented.

[0014] 图2为本发明实施例正视图。 [0014] FIG. 2 is a front view of the embodiment of the invention.

[0015] 图3为本发明实施例前视图。 [0015] FIG. 3 is a front view of the implementation of invention.

[0016] 图4为利用本发明的实施例叶片与一般叶片的风能利用系数比较。 [0016] Example 4 for the use of blade and blade embodiment of the present invention generally wind energy utilization coefficient comparison chart.

[0017] 图5为利用本发明的实施例叶片与一般叶片的推力系数比较。 [0017] FIG. 5 is a thrust coefficient embodiment utilizing the present invention with the blades of the blade generally comparison.

具体实施方式 DETAILED DESCRIPTION

[0018] 图1〜图5为本发明一个实施例叶片的形状和性能。 [0018] FIG. 1 ~ FIG. 5 embodiment of the present invention the shape and properties of the blade in one embodiment. 该叶片长度为41米,额定功率1500kW,叶片最大弦长位置距叶根7. 5米,叶根法兰直径为1. 89米。 The blade length of 41 m, rated power 1500kW, the maximum chord length of the blade position 7.5 m away from the blade root, the blade root flange diameter of 1.89 meters.

[0019] 参照图1,为该实施例的叶根翼型,叶根翼型由结构型1和叶根气动翼型2组成。 [0019] Referring to FIG. 1, for the root airfoil embodiment, airfoil blade roots by structural type 1 and 2 airfoil blade root pneumatic components. 结构型1是半径为R的圆,R由叶根连接法兰的半径确定,结构型1与法兰通过螺栓连接。 Structure type 1 is a circle of radius R, the radius R from the blade root to determine the connection flange, and a flange type structure by bolting. 叶根气动翼型2由结构型1的部分外形、5个相切圆弧和尾缘厚度8组成,5个相切圆弧分别为前缘上圆弧3、前缘圆弧4、前缘下圆弧5、后缘上圆弧6和后缘下圆弧7。 Aerodynamic airfoil blade root portion 2 by the structural shape 1, 5 tangential arc and trailing edge thickness of 8 composed of five are on the leading edge of the arc tangent arc 3, the leading edge of the arc 4, the leading edge Under the arc 5, 6 arc on the trailing edge and the trailing edge lower arc 7. 前缘上圆弧3的圆弧圆心在结构型1圆心正下方2/5R处,圆弧半径为7/5R,与结构型1外圆内切。 Arc on the leading edge of the circle center 3 structure type 1 in the center just below 2 / 5R at a radius of curvature of 7 / 5R, within a cylindrical cut and structure type. 前缘下圆弧5的圆弧圆心在结构型1圆心正上方1/2R处,圆弧半径为3/2R,与结构型1外圆内切。 At the leading edge of the arc center of the arc 5 in the structure type 1 center just above the 1 / 2R at a radius of curvature of 3 / 2R, cut and structure within a cylindrical type. 前缘圆弧4与前缘上圆弧3和前缘下圆弧5都内切,半径为1/2R。 The leading edge of the arc on the leading edge of the arc 4 and 3 and 5 are the leading edge of the next arc cut inside radius of 1 / 2R. 后缘上圆弧6的圆心在过结构型1圆心且与中性线成60的直线上,半径为4R,与结构型1外圆内切。 6 on the trailing edge of the center arc in a straight line through the center of the circle and the structure of type 1 and the neutral line of 60 , the radius 4R, and structured within a cylindrical cut. 后缘下圆弧7的圆心在过结构型1圆心且与中性线成-45的直线上,半径为2R,与结构型1 外圆外切。 7 under the trailing edge of the center arc in a straight line through the center of the circle and the structure type 1 and the neutral line to -45 , the radius 2R, and a cylindrical outer cutting structure type. 尾缘厚度8面竖直,厚度为结构型1直径的0. 5%〜1%。 Trailing edge thickness of 8 vertical surface, the thickness of the structure type 0.5% ~ 1% 1 diameter. 该实施例叶根翼型气动型弦长为2. 83米,相对厚度为66. 7%。 Examples airfoil blade root chord type is 2.83 meters this embodiment, the relative thickness of 66.7 percent.

[0020] 参照图2,为该实施例叶片的正视图。 [0020] Referring to Figure 2, a front view of the blade for the embodiment in FIG. 叶根与叶片最大弦长截面中间的部分分为结构部件9和气动部件10。 Part of the blade root and blade maximum chord length of the middle of the cross-section is divided into structural components and pneumatic components 9 10. 结构部件9在前0. 5米(叶根至截面11处)是圆柱段,用来埋入螺栓,截面11往后的截面形状通过圆形与叶片最大弦长截面12 (叶片最大弦长处)往后各截面翼型放样得到。 Structural components 9 forward 0.5 meters (root to the cross section 11) is a cylindrical section for embedding bolts, the subsequent cross-sectional shape of the cross-section 11 through the circular cross section of the blade maximum chord length of 12 (maximum blade chord) Each airfoil cross-section loft get back. 气动部件10是通过叶根气动型与叶片最大弦长截面12往后各截面翼型放样得到。 Pneumatic member 10 through the root pneumatic blade maximum chord length and cross section of each sectional airfoil 12 loft get back. 叶根结构型部分是叶片主要承载部分,叶根结构型部分与叶中和叶尖为一体, 作为一个整体制造得到。 Blade-root portion is the main structural bearing part of the blade, the blade root and leaves structural part and tip as a whole, as a whole, manufacturing get. 叶根气动型部分是根据已经设计好的外形单独制造,然后将其粘贴到结构部件上及叶片最大弦长截面12处。 Pneumatic blade-root portion are manufactured separately has been designed according to the shape, and then paste it to the structural member and the blade maximum chord-section 12.

[0021] 参照图3,为该实施例叶片的前视图(从叶根往叶尖看),叶片最大弦长截面(12)在距叶根7. 5米处。 [0021] Referring to FIG. 3, for the implementation of the front view of the blade (from the root to the tip of view), the maximum chord length of the blade sections (12) at a distance of 7.5 meters at the blade root. 气动型与结构型中间形成一个空腔。 Pneumatic and structured to form a cavity in the middle.

[0022] 参照图4,为利用本发明设计的实施例叶片与未利用本发明设计的一般叶片风能利用系数的比较。 [0022] Referring to FIG. 4, for the use of embodiments of the present invention is designed with a blade not compare the power coefficient of the general design of the blades of the present invention is utilized. 可见,利用本发明设计的叶片的风能利用系数大大提高。 Visible, with the present invention designed blade wind energy utilization coefficient is greatly increased. 特别是在较大叶尖速比(较低风速)时,风能利用系数有较明显的增加,这正对应于全年的高风频,因此年发电量也能明显增加。 Especially in larger tip speed ratio (low wind speed), the power coefficient has been significantly increased, this being the year corresponding to the high wind frequency, thus annual power output can be increased significantly.

[0023] 参照图5,为利用本发明设计的实施例叶片与未利用本发明设计的一般叶片推力系数的比较,叶片与上述叶片相同。 [0023] Referring to FIG. 5, for the use of embodiments of the present invention, the blade design of the present invention and comparative unutilized generally designed blade thrust coefficient, the same blade with the blade. 风力利用系数提高后,推力系数却没有增加,而在较大叶尖速比(较低风速)时推力系数稍有减小。 After the wind utilization factor increased thrust coefficient was not increased, while slightly reducing the thrust coefficient larger tip speed ratio (low wind speed) is.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
CN2869370Y20 Jan 200614 Feb 2007陈向阳Wind wheel blade for small-sized wind mill generator
CN101300419A17 Oct 20065 Nov 2008Lm玻璃纤维制品有限公司Blade for a wind turbine rotor
CN101737249A25 Dec 200916 Jun 2010阳江市新力工业有限公司Wind power blade
EP2187045A119 Nov 200719 May 2010Mitsubishi Heavy Industries, Ltd.Windmill blade and wind power generator using same
WO2009/121927A1 Title not available
Classifications
International ClassificationF03D11/00
Cooperative ClassificationY02E10/722
Legal Events
DateCodeEventDescription
13 Apr 2011C06Publication
1 Jun 2011C10Entry into substantive examination
18 Jul 2012C14Grant of patent or utility model
27 Feb 2013ASSSuccession or assignment of patent right
Owner name: JIANGSU LIVON AUTOMOBILE COMPONENTS TECHNOLOGY CO.
Free format text: FORMER OWNER: NANJING UNIVERSITY OF AERONAUTICS AND ASTRONAUTICS
Effective date: 20130121
27 Feb 2013C41Transfer of patent application or patent right or utility model
27 Feb 2013CORChange of bibliographic data
Free format text: CORRECT: ADDRESS; FROM: 210016 NANJING, JIANGSU PROVINCE TO: 211178 NANJING, JIANGSU PROVINCE