|Publication number||CN102588206 A|
|Application number||CN 201210075764|
|Publication date||18 Jul 2012|
|Filing date||17 Oct 2006|
|Priority date||17 Oct 2005|
|Also published as||CA2625997A1, CA2625997C, CN101300419A, CN101300419B, CN102588206B, CN102606388A, CN102606388B, DE602006011640D1, EP1945942A1, EP1945942B1, EP2163760A1, EP2172648A1, US8177517, US8469672, US8864473, US20090232656, US20120257982, US20130272891, WO2007045244A1|
|Publication number||201210075764.8, CN 102588206 A, CN 102588206A, CN 201210075764, CN-A-102588206, CN102588206 A, CN102588206A, CN201210075764, CN201210075764.8|
|Export Citation||BiBTeX, EndNote, RefMan|
|Classifications (9), Legal Events (3)|
|External Links: SIPO, Espacenet|
用于风カ涡轮机转子的叶片 Grades for wind turbine rotor blades
[0001 ] 本申请是原案申请日为2006年10月17日、申请号为200680038594. 9 (PCT/ DK2006/000582)、发明名称为《用于风カ涡轮机转子的叶片》的发明专利申请的分案申请。  This application is original bill filed October 17, 2006, application No. 200680038594. 9 (PCT / DK2006 / 000582), titled "grades for a wind turbine rotor blade," the patent application points application filed.
技术领域 Technical Field
 本发明涉及ー种用于具有基本水平转子轴的风カ涡轮机转子的叶片，所述转子包括毂，安装时叶片从所述毂基本上径向伸出，所述叶片具有在所述叶片的前缘和后缘之间延伸的翼弦面，所述叶片包括最靠近毂的根部区域、距毂最远的翼面区域和在根部区域和翼面区域之间的过渡区域，并且所述叶片包括基本上沿着整个翼面区域的单一翼面。  The present invention relates ー species for a wind turbine rotor blade grades having a substantially horizontal rotor shaft, said rotor comprising a hub, when installing blade extending substantially radially from said hub, said blade having at the chord surface extending between the leading and trailing edges of the blade, the blade comprises a root area closest to the hub, furthest away from the hub airfoil region and the transition region between the root region and the airfoil region, and the said blade includes a substantially along the entire wing surface area of a single wing.
 理想地，翼面式叶片成形为类似于一般的飞机机翼的形状，随着与毂的距离的减少，这种叶片的翼弦面宽度以及它的ー阶导数不断増加。  Ideally, the airfoil vane shaped like a general shape of an airplane wing, with decreasing distance from the hub, and this chord of the blade surface width and its ー continue to increase in the first derivative. 这就导致所述叶片理想地在毂附近变得相当宽。 This results in the vicinity of the blade hub desirably becomes quite wide. 这又导致在将叶片安装到毂上时会出现问题，此外，由于叶片表面积较大， 这会导致安装叶片时的显著载荷，例如风暴载荷。 This in turn results when the blade is mounted on the hub will have problems, in addition, since the large blade surface area, which will lead to a significant load when mounting the blade, such as storm loads.
 因此，在过去数年里，叶片的结构已经朝着ー种形状改进，在这种形状中，叶片包含最靠近毂的根部区域，距毂最远的翼面区域，和在根部区域和翼面区域之间的过渡区域。  Thus, in the past few years, the structure of the blade has been moving ー shapes improvements in this shape, the blade root area closest to the hub contains, furthest away from the hub wing surface area, and in the root region and the transition zone between the airfoil region. 所述翼面区域具有理想的或者近乎理想的叶片形状，而根部区域具有基本上圆形的截面， 其能够减少风暴载荷并使得更容易和更安全地把叶片安装到毂上。 The airfoil area has an ideal or almost ideal blade shape, whereas the root region has a substantially circular cross-section, which is capable of reducing the storm loads and easier and safer to install blades to the hub. 优选所述根部区域直径是沿着所述整个根部区域恒定的。 Preferably the diameter of the root region along the entire root area is constant. 由于所述圆形截面，所述根部区域并没有提高风カ涡轮机的发电量，而事实上，由于风阻降低了一些发电量。 Because of the circular cross-section, the root area and did not increase generating capacity of wind turbines grades, and in fact, due to the drag reducing the number of power generation. 顾名思义，所述过渡区域具有从根部区域的圆形形状逐渐变化到翼面区域的翼型的形状。 As the name suggests, the transition region from a circular shape having a gradual change in the root region to the airfoil shape of the airfoil region. 一般地，过渡区域的宽度随着与毂的距离的增加而基本上线性增加。 Generally, the width of the transition region with increasing distance from the hub increases substantially linearly.
 众所周知，在飞机行业，带有两个机翼的飞机即通常所说的双翼飞机，通常比只有一个机翼的飞机更容易升空。  It is well known in the aircraft industry, the aircraft with two wings known as the biplane, usually more than just one wing of the aircraft easier to launch. 这允许在不增加机翼宽度的情况下增大飞机机翼的总升力。 This allows the wing without increasing the width of the situation to increase the total lift aircraft wing.
 结合风力涡轮机的叶片，也就是通过制造带有两个或更多转子的风カ涡轮机也可获知这个原理。  The combination of a wind turbine blade, which is manufactured by having two or more grades of wind turbine rotors can also be informed of this principle. CA 2395612描述了带有两个同轴转子的风カ涡轮机，其中一个转子比另ー个转子旋转更快。 CA 2395612 describes with two coaxial rotor wind turbine ka, where a rotor rotating rotors than the other ー faster. GB 758628描述了带有两个在相反方向上旋转的同轴转子的风カ涡轮机。 GB 758628 describes a wind turbine with coaxial rotor grades two in the opposite direction of rotation.
 W098/31934掲示了类似于双翼机设计的叶片。  W098 / 31934 kei shows similar biplane designed blades. 所述叶片由通过横拉条相互连接的两个平行的翼梁构造而成。 The blade made by two parallel horizontal brace interconnected spar constructed. 在每个翼梁上安装两个流线型的元件，所述元件分别包括共同构成翼面的前缘和后缘。 Streamlined installation of two elements in each spar together constitute the elements each include a leading edge and a trailing edge of the airfoil.
 US5161952掲示了一种用于风カ涡轮机转子的双平面结构。  US5161952 kei shows a dual-plane structure for a wind turbine rotor grades. 所述风カ涡轮机设计成使得两个直叶片彼此以一定距离与所述转子的毂连接。 Ka said wind turbine blade is designed so that two straight to a certain distance from the rotor hub connected to each other. 所述两个叶片的末端互相联接。 Join the two ends of each of the blades.
 本发明的目的是提供ー种新的改进的叶片结构。  The object of the present invention is to provide a new and improved kind ー blade structure.
 根据本发明，通过所述叶片和具有翼型的根部部分中的至少ー个根部部分实现这个目的，所述叶片包括基本上沿整个根部区域的至少第一根部部分和第二根部部分，所述部分布置成具有横向于翼弦面的相互间距。  According to the present invention, the blade having airfoil and root, at least a portion of the root portion ー achieve this object, the blade comprising substantially along the entire root area of the root portion of at least a first and a second root portion the portions are arranged transversely to the chord face each other with a pitch. 以这样的方式，所述带有翼型的根部部分有助于提高风カ涡轮机的发电量。 Root portion in such a manner, with the airfoil helps to improve power generation of wind turbine grades.
 根据本发明叶片的优选实施例，叶片的所述翼弦面在叶片的纵向上是扭曲的，其中所述扭曲可能在叶片的纵向上达到80度。  According to a preferred embodiment of the invention the blades, the chord surface of the blade in the longitudinal direction of the blade is twisted, wherein the twist may reach 80 degrees in the longitudinal direction of the blade. 一般地，所述扭曲在60和70度之间。 Typically, the twist between 60 and 70 degrees. 通常情况下，所述扭曲的ー阶导数随着与毂的距离的递减而増大，这就意味着，翼弦面Kl在根部区域2的扭曲优选相对较高。 Under normal circumstances, ー order derivatives of the distortions and decline with distance from the hub and Zeng large, which means that chord in the root area 2 Kl face twisted preferably relatively high.
 根据本发明的优选实施例，至少ー个带有翼型的根部部分的翼弦面基本上平行于最靠近轮毂的区域内的叶片本身的翼弦面。  According to a preferred embodiment of the present invention, at least ー with a root portion of the airfoil chord plane substantially parallel to the blade area closest to the hub itself chord face. 更适宜地，叶片的翼弦面在叶片的纵向上是扭曲的，以补偿叶片随着与毂的距离的增加而增加的局部速度，这表明叶片根据距离毂的半径不同地“看到”风向。 More suitably, the chord surface of the blade in the longitudinal direction of the blade is twisted to compensate for blade with increasing distance from the hub of the local rate increases, indicating that the blade according to the distance of the hub radius different "see" the wind . 这表明在该实施例中，翼弦面在根部区域的纵向上的路径是翼弦面在翼面区域和/或过渡区域的纵向上的路径的延续。 This suggests that in this embodiment, the path in the longitudinal plane chord root region is a continuation chord path in the longitudinal plane airfoil region and / or the transition region.
 根据本发明的具体实施例，第一和第二根部部分都具有翼型。  According to a particular embodiment of the present invention, the first and second root portion having an airfoil. 这样，两个根部部分都有助于提高风カ涡轮机的发电量，也可以这样设计使两部分的总贡献量与理想叶片的宽阔部分的贡献量相当。 This will help to improve both the root portion of wind turbine power generation grades can also be designed so that the contribution of the widened portion of the total contribution amount and the ideal of the two parts of the blade quite.
 根据优选实施例，至少ー个带有翼型的根部部分的翼弦面具有基本上恒定的宽度，过渡区域的翼弦面随着与毂的距离的增加而变宽，翼面区域的翼弦面随着与毂的距离的増加而变窄。  According to a preferred embodiment, at least one with a root portion ー chord airfoil surface having a substantially constant width, chord surface of the transition region with increasing distance from the hub widened, airfoil region chord face with the enlargement of the hub distance plus narrowed. 这样，本发明的叶片就具有与常规叶片相当的形状，这样现有的叶片的模具可以被相对简易地修改以便能够制造新型叶片。 Thus, the present invention is the blade having a shape corresponding to conventional blades, so that existing mold blade can be relatively easily modified to enable the manufacture of new blades.
 根据具体实施例，过渡区域包括至少第一过渡部分和第二过渡部分，在横向于翼弦面看去时，所述部分布置成具有一定的相互距离，其中过渡部分中的至少ー个过渡部分具有翼型。  According to a particular embodiment, the transition region comprises at least a first transition portion and a second transition portion, in a plane transverse to the chord when viewed, the portion is arranged to have a certain distance from each other, wherein at least a portion of the transition ーa transition portion has an airfoil. 更适宜地，在过渡区域和翼面区域之间的过渡处，至少ー个带有翼型的过渡部分的翼弦面平行于叶片本身的翼弦面，并且优选两个过渡部分都具有翼型。 More suitably, at the transition between the transition region and the airfoil region, at least ー a chord transition portion with the airfoil surface parallel to the surface of the blade chord itself, and two transition portions preferably have airfoil .
 通常情况下，根部区域和过渡区域的总长度在叶片总长度的5%和35%之间，并且经常是在叶片总长度5%和25%之间，甚至是叶片总长度的5%和15%之间。  Typically, the total length of the root region and the transition region between 5% and 35% of the total length of the blade, and often is the total length of the blade between 5% and 25%, or even the total length of the blade 5 % and 15% between.
 根据本发明的优选实施例，第一和第二根部部分在过渡区域最靠近毂的部分处连接。  According to a preferred embodiment of the present invention, the first and second portions of the root portion of the transition area closest to the hub connection. 这样，过渡区域可以具有与常规叶片相当的形状，而只有根部区域具有双叶型。 Thus, the transition region may have a shape corresponding to a conventional blade, while only the root area has a double leaf type.
 根据叶片的另ー个实施例，第一和第二根部部分合并成为第一和第二过渡部分， 而第一和第二过渡部分与距毂最远的过渡区域的部分相连。  According to another blade ー embodiment, the first and second root portions merge into the first and second transition portion, and the first and second transition portion connected to the transition region furthest away from the hub portion. 这样，过渡区域也具有双重结构并且具有潜在的更大升力。 Thus, the transition area also has a dual structure and potentially greater lift.
 根据优选实施例，在最靠近毂的根部区域的部分，第一和第二根部部分相连形成共同的安装区域。  According to a preferred embodiment, the portion of the root area closest to the hub, the first and second root portions connected to form a common mounting area. 更适宜地，这个安装区域具有基本圆形的横截面。 More suitably, the mounting area has a substantially circular cross section. 这样，根据本发明的叶片可以具有与常规叶片相应的安装法兰，以便这些新式叶片装入到现有的毂中。 Thus, the blade according to the present invention may have a mounting flange corresponding to conventional blades so that these new blades mounted to an existing hub.
 根据优选实施例，叶片由用壳体构成，所述壳体由玻璃纤维或者碳纤维加强的聚合物材料制成。  According to a preferred embodiment of the polymeric material, the blades constituted by a casing, said casing reinforced by glass fibers or carbon fibers. 更适宜地，叶片设计成为单ー的整体壳体。 More suitably, the blade designed as a single integral housing ー of.
 可供选择的，至少ー个带有翼型的根部部分可以有被分开安装的部分。  The alternative, at least ー airfoil having a root portion may have to be installed separately parts. 这个实施例的优越性在于，所述部分可以无需更换叶片而被用于现有的风カ涡轮机，例如通过将这些部分安装到已安装叶片的根部部分。 The advantage of that embodiment, the blade portion can be used without changing the existing wind turbines ka, e.g., by mounting these parts to the installed blade root portion. 也很显然，不是所有根部部分都需要固定到毂上。 Clearly also, not all need root portion fixed to the hub. 附图说明 Brief Description
 下面參考附图详细地说明本发明，其中  The present invention is described below with reference to which the detail drawings
 图I显示了理想翼面式叶片的俯视图；  Figure I shows the ideal blade airfoil plan view;
 图2显示了常规翼面式叶片的透视图；和  FIG. 2 shows a perspective view of a conventional airfoil blades; and
 图3-9显示根据本发明的叶片的不同实施例。  Figure 3-9 shows the blade of the present invention according to different embodiments.
具体实施方式 DETAILED DESCRIPTION
 图I显示了理想翼面式叶片20的实施例。  Figure I shows an embodiment of the ideal of the airfoil blade 20. 所述叶片具有适合固定到风カ涡轮机的毂上的根部部件21。 Said blade having a root hub member 21 wind turbines on the grades for fixed to. 所述理想的叶片20设计成叶片20的宽度随着与毂之间距离L的增加而減少。 The ideal blade 20 is designed with the width of the blade between the hub 20 and the distance L is reduced to increase. 此外，叶片20的宽度的ー阶导数也随着与毂20的距离的增加而减少，这意味着，理想状态下，叶片20在根部区域21是很宽的。 In addition, the width of the guide vanes ー order of 20 also increases with the distance from the hub 20 is reduced, which means that, ideally, the blade 20 in the root region 21 is very wide. 这就引起如何将叶片20固定到毂上的问题。 This leads to how the blade 20 is fixed to the question hub. 此外，安装吋，由于所述叶片20的表面面积很大，叶片20以很大的风暴载荷冲击所述毂。 In addition, installation inch, due to the large surface area of the blade 20, the blade 20 to impact a large storm loads the hub.
 因此，在过去数年里，叶片的结构已经朝着ー种形状改进，其中，叶片的外部部分对应理想的叶片20，而根部区域的表面面积与理想的叶片相比被显著缩小。  Thus, in the past few years, the structure of the blade has been moving ー shapes improvements which corresponds to the outer portion of the blade ideal blade 20, but was significantly reduced compared to the ideal blade surface area to the root zone. 这个实施例在图I中以虚线示出，其透视图显示在图2中。 The embodiment shown in Figure I, shown in dashed lines, its perspective is shown in Figure 2.
 从图2可以看出，所述常规叶片I包括最靠近所述毂的根部区域2、距所述毂最远的翼面区域4和在根部区域2和翼面区域4之间的过渡区域3。  As can be seen from Figure 2, the conventional blade comprises a root area I closest to the hub 2, furthest away from the hub 4 and the airfoil region in the root region and the airfoil region between 2 4 transition region 3. 叶片I包括当叶片安装到毂上时朝向叶片I的旋转方向的前缘5，和面向前缘5的相反方向的后缘6。 I include blade when the blade is mounted to the direction of rotation of the blades I when the leading edge of the hub 5, the leading edge and the trailing edge facing the opposite direction 5 of 6. 所述翼面区域4具有理想的或者近乎理想的叶片形状，而根部区域2具有基本上圆形的截面，其能够减少风暴载荷并且使得更容易和更安全地将叶片I安装到毂上。 The airfoil area 4 has an ideal or almost ideal blade shape, whereas the root area 2 has a substantially circular cross-section, which is capable of reducing the storm loads and makes it easier and safer I blade mounted on the hub. 更适宜地，根部区域2的直径沿着整个根部区域2是恒定的。 More suitably, the diameter of the root along the entire root area 2 is constant region 2. 所述过渡区域3具有一个逐渐从根部区域2的圆形形状转换到翼面区域4的翼型的形状。 The transition region 3 has a gradual transition from the circular shape of the root region airfoil 2 to the airfoil shape of region 4. 过渡区域3的宽度随着与所述毂的距离L的増加基本上线性增加。 With the width of the transition region 3 and the hub of the distance L to increase in a substantially linear increase.
 所述翼面区域4具有翼型，该翼型带有在叶片I的前缘5和后缘6之间延伸的翼弦面K。  The airfoil region 4 has an airfoil, the airfoil surface of the blade with the I chord extending between the leading edge and the trailing edge 6 5 K. 所述翼弦面的宽度随着与所述毂的距离L的增加而減少。 The width of the wing chord plane with increasing distance to the hub of L is reduced. 应该注意，所述翼弦面没有必要在其整个区域上直线延伸，因为叶片可能扭曲和/或弯曲，由此为翼弦面提供对应扭曲和/或弯曲的路线，这是最常出现的情形，以便补偿取决于距离毂的半径的所述叶片的局部速度。 It should be noted, the chord face straight no need to extend over the entire region, because the leaves may distort and / or curved, thereby providing a corresponding distortion and / or curved line as chord surface, which is the most frequently occurring situation The local velocity of the blade, in order to compensate depending on the distance of the radius of the hub.
 由于圆形截面，根部区域2并没有促进风カ涡轮机的发电量，事实上却由于风阻而降低少许发电量。  Since the circular cross-section, the root area 2 does not promote the generation of wind turbines grades, in fact since the wind resistance is reduced a little electricity. 因此，本发明的想法是把所述根部区域2和可选的过渡区域3分成为两个或更多部分，这样这些部分中的至少ー个部分具有为叶片I的这一部分提供升力的叶型，从而有助于提高风カ涡轮机的发电量。 Thus, the idea of the invention is the root region 2 and optional transition region 3 divided into two or more parts, so that these portions of the at least one portion having ー provide lift to this part of the blade airfoil I helping to improve wind turbine power generation grades.
 图3A显示了根据本发明的叶片的第一个实施例，其中朝向前缘5观察所述叶片， 而图3B显示沿着线BB的截面，图3C显示沿着图3A的线CC的截面，其中截面CC位于根部区域2和过渡区域3之间的过渡部分。  Figure 3A shows a blade according to a first embodiment of the present invention, wherein the blade leading edge 5 toward the observation, and FIG 3B shows a sectional view along line BB, Figure 3C shows along the line CC in FIG. 3A cross section, wherein the cross-section CC 3 located in the transition portion and the transition region between the root region 2. 根据该实施例，根部区域2被分成第一根部部分7 和第二根部部分8，而过渡区域3被分成第一过渡部分9和第二的过渡部分10。 According to this embodiment, the root area 2 is divided into a first root portion 7 and the second root portion 8, and the transition area 3 is divided into transition portion 9 and the second transition portion 10 first. 所述两个过渡部分9和10在过渡区域3和翼面区域4之间的过渡部分连接起来。 The two transition portions 9 and 10 in the transition section 3 and 4 between the wing surface area transition area connected. 结果，在所述各个部分之间就形成了缝隙17。 As a result, between the various parts of the slit 17 is formed. 另外，这些部分可以通过安装在所述部分之间的缝隙17内的加强装置相互连接。 In addition, these parts can be installed in the stiffening means 17 is the portion of the gap between each other. 这些加强装置可以例如被设置成如钢制的格子结构，还可以提供有例如所谓的降阻叶型，其中该叶型的横截面具有対称的下降形状。 These stiffening means may for example be arranged as a steel lattice structure, it may also be provided with a barrier such as a so-called drop leaf type, in which the leaf-shaped cross-sectional shape having Dui said the decline. 这样，减小了加强装置的风阻，并且可以降低噪音的进入。 Thus, the stiffening means reduces the drag, and can reduce the noise entering.
 图3B显示该叶片的安装区域。  Figure 3B shows the mounting area of the blade. 在这个区域的叶片部分的叶型形成使得所述叶型位于带有圆形根部部分（用虚线12示出）的相应的常规叶片之内。 In the airfoil blade portion of the region is formed such that the airfoil is located within a corresponding conventional blade with circular root part (shown by dotted lines 12) in the. 第一根部部分7在包括翼弦面Kl的安装区域内具有翼型，而第二个根部部分8具有能够减少该部分风阻的叶型，其对风カ涡轮机的发电量不必起到促进作用。 The first root portion 7 having a chord in the plane including the mounting region Kl airfoil, while the second root portion 8 having a portion capable of reducing the drag of the airfoil, which grades wind turbine power generation does not have to play a catalytic role. 第一根部部分7合并成也具有包括翼弦面K3的翼型的第一过渡部分9。 Merged into the first root section 7 also includes a chord having a first transition surface of the airfoil section 9 K3. 第二根部部分8合并成为第二过渡部分10，并且从安装区域的已降低风阻的叶型逐渐转变成为在第二过渡部分10包括翼弦面K4的实际翼型。 The second root portion 8 merged to become the second transition section 10, and the mounting area has been reduced drag airfoil gradually transformed into the second transition portion 10 K4 include actual airfoil chord face. 该叶片的翼弦面K通常沿着叶片的纵向扭曲以补偿叶片的局部速度。 The chord of the blade along the blade surface K generally longitudinal twist to compensate for the local velocity of the blade. 因此，翼弦面K1、K3和K4 的路线是叶片在翼面区域4的翼弦面K的路线的延续。 Therefore, the chord plane K1, K3 and K4 route is blade airfoil chord surface area of 4 K line continuation.
 叶片的翼弦面K可以沿叶片纵向扭曲到75-80度，但是通常情况下是在60和70 度之间。  chord of the blade surface K twisted longitudinally along the blade to 75-80 degrees, but usually is between 60 and 70 degrees. 通常，该扭曲的一阶导数会随着与毂的距离的递减而增加，这表明在根部区域2的翼弦面Kl的扭曲更适宜相对较高。 Typically, the first derivative of the distortion will be with the decreasing distance from the hub increases, suggesting that twisted chord in root surface area of more suitable Kl 2 is relatively high.
 第一根部部分7和第二根部部分8在安装区域具有许多安装孔11。  The first root portion 7 and the second root portion 8 in the mounting region 11 having a plurality of mounting holes. 这些孔11的位置与带有圆形根部部分12的常规叶片上的位置相同。 These holes 11 have the same location with a conventional blade on a circular root portion 12 is the same. 这样根据本发明的新叶片可以安装在常规的毂上，并以简易的方式在更换期间替换现有的叶片。 Under the new blade so that the present invention can be installed on a conventional hub, and easy way to replace the existing blade during replacement.
 图4和5分别显示了本发明的第二和第三实施例，它们是图3所示实施例的变型。  Figures 4 and 5 show the second and third embodiments of the present invention which is a modification of the embodiment shown in FIG. 3. 因此，这里只论述差异之处。 So, here only discuss the differences between. 如图4显示的第二实施例，第二根部部分81在安装区域内同样具有包括翼弦面K2的翼型。 Figure 4 shows a second embodiment, the second root portion 81 within the mounting region also has a chord plane K2 include airfoil. 此外，如图4B清楚示出的，所述根部部分81的叶型延伸到根部部件12的常规圆形叶型以外。 In addition, best shown in FIG. 4B, the root portion of the airfoil 81 extends into the root of the airfoil section 12 of the conventional circular outside. 该附图也显示了两个部分的翼弦面可以相互呈一定角度。 The figure also shows the faces of the two parts of the chord may be mutually angled.
 根据附图5显示的第三个实施例，第一和第二根部部分72，82以及第一和第二过渡部分92，IO2都有対称的叶型。  According to the third embodiment shown in FIG. 5, the first and second root portions 72 and 82 and the first and second transition portion 92, IO2 have Dui said airfoil. 示出所述叶型具有与叶片旋转方向平行的翼弦面，然而所述叶型可更适宜与旋转方向成一定的角度，该角度的选取决定于使升力增大到最大值。 The airfoil is shown having the rotating direction of the blade parallel to the chord plane, but may be more suitably the airfoil certain direction with the rotation angle of the angle depends on the selection of lift increases to a maximum.
 如附图5B所示，第一根部部分I2和第二根部部分82都延伸到常规根部部分12的圆形叶型以外。  As shown in Figure 5B, the first and the second root portion I2 root portion 82 are extended to a conventional circular root portion of the airfoil 12 beyond. 最后，应当指出附图4和5以及附图3显示的实施例的根部部分的每ー个都并入相应的过渡部分（92，93，IO2, IO3)，所述部分在过渡区域3和翼面区域4之间的过渡处连接形成公共的叶型。 Finally, it should be noted that the root portion of each ー embodiment of Figures 4 and 5, and Figure 3 shows the two portions are incorporated in the corresponding transition (92,93, IO2, IO3), the portion of the transition region 3 and the wing 4 at the transition area between the surface of the airfoil to form a common connection.
 附图6显示了叶片的第四实施例，其中第一根部部分73和第二根部部分83在安装区域22连接在一起。  Figure 6 shows a fourth embodiment of the blade, wherein the first root portion 73 and a root portion 83 at a second mounting region 22 are connected together. 如附图6B所示，安装区域22是圆形的并包含安装孔11，该叶片通过所述孔被螺栓固定到毂上。 As shown, the mounting area figures 6B 22 is circular and includes a mounting hole 11, the blade is fixed to the bolt through the hole on the hub. 该叶片适用于常规的毂，这样也可以在更新期间替换已安装在风カ涡轮机上的现有叶片。 The blade is suitable for conventional hub, which can be replaced during the update has been installed in the wind turbine blade grades existing machines.
 附图7显示了叶片的第五实施例，其中第一根部部分74和第二根部部分84在安装区域22相连，但是这两个部分并没有在距毂的一定距离处连接，而是作为具有不同长度的两个分离叶片部件出现。  Figure 7 shows a fifth embodiment of the blade, wherein the first root portion 74 and the second root portion 84 is connected to the mounting region 22, but does not connect the two parts at a certain distance from the hub, and as two separate blade parts with different lengths occur. 显然如附图7所示，不同的根部部分不必具有同样的厚度。 7 as clearly shown in the drawings, the different root portion need not have the same thickness.
 附图8显示了叶片的第六实施例，其中第一、第二、和第三根部部分75，85，13分别合并成为第一、第二和第三过渡部分95，IO5,14。  Figure 8 shows a sixth embodiment of the blade, wherein the first, second, and third root portion 75,85,13 are merged to become the first, second and third transition section 95, IO5,14 . 在这里显示出第一和第二根部部分75，85以及第一和第二过渡部分95，IO5具有減少这些部分的风阻的形状，同时第三根部部分13和第三过渡部分14具有现有的翼型。 Here shows the first and second root portions 75, 85 and first and second transition portion 95, IO5 reduce drag these portions having a shape, while the third root portion 13 and the third transition portion 14 having a conventional airfoil. 然而，这些叶型可都具有増加相应区域的升力的叶型，从 However, these airfoil lift may have to increase in the corresponding region of the leaf type, from
7而也增加风カ涡轮机的发电量。 Grades 7 and also increased wind turbine power generation. 当然，所述三个根部部分75，85，13可如附图6和7所示那样在安装区域连接。 Of course, the three root portion 75,85,13 and 6 can be as illustrated in Fig. 7 in connection mounting area.
 附图9显示了与附图6的实施例相对应的实施例，但是其中叶片额外具有第一分开安装的叶片部件15和第二分开安装的叶片部件16。  Figure 9 shows the embodiment 6 of the accompanying drawings corresponding to embodiments, but wherein additional blades having a first blade member separate mounting member 15 and a second separately mounted blade 16. 所述分开安装的叶片部件15，16通过许多保持装置18被分别地安装在第一和第二根部部分73，83上。 The separately mounted blade parts 15, 16 by a number of holding means 18 are respectively mounted on the first and second root portions 73, 83. 所述叶片部件15和16 沿着根部区域2延伸，也可以选择沿着叶片的过渡区域3延伸。 The blade members 15 and 16 extend along the root area 2, you can choose 3 extends along the transitional area of the blade. 叶片本身不一定要有两个根部部分和/或过渡部分，但是可以有这样的形状，即其中没有缝隙17，没有根部部分和/ 或过渡部分，在这种情况下，叶片的根部区域和过渡区域相当于常规的叶片。 Two blade itself does not have to root portion and / or the transition section, but may have a shape, i.e., where there is no gap 17, no portion and / or the roots of the transition portion, in this case, the blade root and the transition region region corresponds to a conventional blade. 这个实施例的优越性在于分开安装的叶片部件15，16能够被安装，而不需更换在已安装的风カ涡轮机上的叶片。 The advantages of an embodiment of a blade member 15, 16 installed separately can be installed without the need to replace the blades in the installed wind turbines on ka. 所述保持装置可形成具有例如用于降低风阻和噪声进入的降阻叶型。 The holding means may be formed having, for example for reducing wind resistance and noise reduction in resistance into the blades.
 本发明已经对优选方案进行了描述。  The preferred embodiments of the present invention has been described. 由此也可以想到没有偏离本发明的范围的许多改进。 We can also think of many improvements without departing from the scope of the present invention. 对本领域的技术人员显而易见的改进和变化被认为落入本发明的范围之内。 Those skilled in the art of the obvious modifications and variations are considered to fall within the scope of the present invention. 例如， 附图9显示的实施例可只有单个分开安装的叶片部件。 For example, Figure 9 shows an embodiment may be in single separately mounted blade member. 也可以想到这样的实施例：其中各个部分具有単独的叶片角调节。 You can also think of such examples: in which each part of the blade has a separate radiolabeling angle adjustment.
 附图标记列表 I叶片 2根部区域 3过渡区域 4翼面区域 5前缘 6后缘 7第一根部部分 8第二根部部分 9第一过渡部分 10第二过渡部分 11安装孔 12圆形根部部分 13第三根部部分 14第四根部部分 15第一分开安装的叶片部件 16第二分开安装的叶片部件 17缝隙 18保持装置 20叶片 21根部部分 22安装区域 Kx翼弦面 L纵向  List of reference numerals  I blade  2 root region  3 transition region  4 wing surface area  5 leading edge  6 trailing edge of the  7 first root  The first transition portion 9  The second root portion 8  10 second transition portion  11 mounting holes  12 circular root portion  13 third root portion  The fourth root portion 14  The components of the first blade section 15 separately mounted blade  16 second installed separately  17 slot  18 holding device  20 blade  21 root portion [ 0064] 22 mounting area  Kx chord surface  L Portrait
|Cooperative Classification||F03D1/0658, Y02E10/721, F05B2260/97, F05B2240/301, F03D1/0641, F01D5/12|
|European Classification||F03D1/06C2, F03D1/06B6B|
|18 Jul 2012||C06||Publication|
|19 Sep 2012||C10||Entry into substantive examination|
|22 Oct 2014||C14||Grant of patent or utility model|