钝尾缘翼型对5MW风力机性能影响的研究

目前国内外对钝尾缘翼型的研究主要集中于翼型的改进方式与二维气动性能的模拟,对钝尾缘翼型应用于风力机时对其性能影响的研究较少,然而钝尾缘翼型应用于风力机时由于旋转效应的存在叶素翼型之间会发生相互影响。为了更好的研究钝尾缘翼型,了解钝尾缘翼型对风力机性能的影响,对NREL 5MW风力机叶片内侧翼型进行对称钝尾缘修型,分析二维翼型气动性能,发现一定范围内,翼型的升力系数、升阻比均随尾缘厚度的增加而增大。对原风力机进翼型替换,模拟并对比两类风力机的性能,研究表明改型后风力机的输出扭矩高于原机,而且随风速增大改型风力机的优势变得越来越突出;然而在相同工况下,改型后风力机的轴向力也大于原机。     

钝尾缘风力机翼型气动性能计算分析

钝尾缘风力机翼型有较好的结构和气动性能,是目前多被用于大型风力机叶片靠近轮毂区域的选定翼型.但钝尾缘翼型也有缺点,易产生大的脱流涡,这会降低叶片的气动性能.为了更好地研究钝尾缘翼型的性能,以了解其气动性能的降低能否与其结构性能的优化相匹配.采用计算流体动力学(Computational fluid dynamics,CFD)方法,对薄尾缘翼型S809和改进的钝尾缘翼型S809-100的性能进行模拟和对比,结果表明相对于薄尾缘翼型,钝尾缘翼型可以增大断面的最大升力系数和升力曲线斜率,并可以降低翼型污染对翼型升力影响的敏感度.     

水平轴风力机叶片翼型的气动特性数值模拟

为了直观形象地探讨水平轴风力机叶片翼型的气动特性,利用计算流体力学软件FLUENT对水平轴风力机叶片常用翼型FFA-W3-211,FFA-W3-301和NACA63-215进行了数值模拟,并与试验数据进行对比和分析,验证数值模拟的可靠性。有利于了解风力机翼型的气动性能,为风力机叶片翼型选型和叶片翼型设计和研发提供重要依据。     

钝尾缘叶片三维建模方法的研究

钝尾缘风力机翼型目前被多数用于大型风力机叶片叶根与最大弦长处,这是因为气动上,钝尾缘翼型能够提高升力系数斜率、降低翼型不敏感性;而结构上,钝尾缘翼型与相同厚度翼型相比增加了截面面积和转动惯量[1],论文依据钝尾缘特点,提出设计钝尾缘翼型方案,并以58米长度叶片为例,设计钝尾缘翼型形状,以及此区域主模型的分模方式,完成三维模型建立,为后续有限元建模及模具加工制造提供基础。     

可逆地铁风机用翼型优化设计与验证

作为叶片设计的基本组成单元,可逆翼型的选取对整机性能的影响起着重要的作用。以性能较好的R18可逆翼型作为初始翼型,通过翼型优化方法得到一款优化翼型。利用Numeca软件对R18翼型构建的叶片进行气动性能计算并与标准风机试验台的数据进行比对,验证该数值方法的可靠性。在此基础上采用两种翼型构建两种叶片模型并用Numeca软件计算气动性能,以此对翼型优化的设计效果作出评价。研究结果表明：在设计攻角范围内,优化翼型的升阻力特性均高于R18翼型;且在设计工况范围内,优化翼型设计出的风机全压提升5.43%,效率提升0.905%。表明该翼型优化设计方法确能提高设计出的可逆地铁风机气动性能。     

风力机翼型气动噪声优化设计研究

为获得高升阻比、低噪声水平的风力机翼型,将气动噪声引入到风力机专用翼型的设计中.为评价翼型气动噪声水平,对翼型自身噪声进行讨论和研究,应用NASA基于大量试验而得到的翼型自身噪声模型进行建模.采用型函数扰动法对翼型廓线进行表示,以翼型自身噪声水平作为优化目标,将气动特性作为性能约束,建立翼型的优化设计模型.设计过程中,采用XFOIL获取翼型边界层参数,及对翼型的气动性能进行评价.将流场求解程序和直接优化方法相结合,采用复合形法进行搜索寻优,用Matlab编制优化程序.以NACA4415作为原始翼型进行优化设计,得到一种具有高气动性能、低噪声水平的风力机专用翼型.     

风力机叶片气动载荷的优化研究

为了研究垂直轴风力机的叶片气动性能,利用流固耦合法模拟了垂直轴风力机在实际工况下的气动载荷分析,模拟结果表明,由于翼型后部较薄,受到的变形应力最大。为了避免因叶片变形而引起风力机整体气动性能下降,提出了通过加大翼型后部厚度的方案来提高叶片的强度,并通过数值模拟对改进后的翼型做了气动性能分析,得出了适当的增加翼型后部厚度,并不会对翼型气动性能造成太大的影响,验证了此方案的有效性。这些研究结论为今后垂直轴风力机的设计制造提供了一定的参考依据。     

翼型与弦长对直线翼垂直轴风力机起动性能影响的数值模拟

为了探究翼型与弦长对直线翼垂直轴风力机起动性能的影响，选择了NACA0018、NACA0026、S809以及S1046四种翼型，40mm、60mm和80mm三种叶片弦长进行研究，其中S809翼型采用正装和反装两种方式。对不同条件下风力机的静态力矩性能以及转速性能进行数值模拟研究。静态力矩性能研究表明，随着叶片弦长的增大，风力机平均静态力矩增大。通过对比不同翼型的结果发现：NACA0026翼型平均静态力矩系数最大且达到稳定时间最短，S809翼型起动性能最差且反装时平均静态力矩系数最小，SI046翼型稳定转速最高。转速性能研究表明，叶片弦长的增大会增大叶片的质量，进而增大转动惯量，使得风力机的起动性能降低。本研究将对直线翼垂直轴风力机的设计提供有益的参考。     

双层翼叶片几何参数对水平轴风力机气动性能影响研究

为了提高风力机的气动性能,基于NREL Phase Ⅵ水平轴风力机叶片,设计出的一种双层翼叶片。通过计算流体力学的方法,在不同来流风速下,对比分析了双层翼叶片与按比例缩放各叶高处弦长的NREL Phase Ⅵ水平轴风力机叶片的扭矩与弯矩,研究了叶片实度的影响,发现实度增加并不是双层翼叶片的气动性能优于原始NREL Phase Ⅵ风力机叶片的主要原因。对不同弦长比、垂直距离及水平距离的大小叶片所组成的双层翼结构进行数值模拟研究,利用流线图着重分析了大小叶片水平距离对风力机气动性能的影响,总结了气动性能随双层翼叶片几何参数的变化规律,发现在15 m/s至25 m/s的风速下,选择较大弦长比、较大垂直距离或者较小水平距离的双层翼叶片可得到较高的扭矩值,但弯矩值也会随之增加。     

翼型厚度对风力机翼型气动特性的影响

在Re=3×106下,基于k-w SST两方程湍流模型对两种不同厚度的NREL风力机专用翼型进行了数值模拟,重点研究了-5°～15°攻角下不同厚度对翼型气动特性的影响规律。非定常计算结果表明:不同厚度对翼型气动性能影响显著,在某一小攻角范围,较小厚度值可获得较大升阻比,在大攻角翼型发生失速时,较大厚度值可提高翼型的升阻比,拓宽高升阻比的攻角范围,有效改善翼型的分离流动特性。     

Aerodynamic shape optimization of wind turbine rotor blades considering aeroelastic deformation effect

An aerodynamic shape optimization framework of two modules is developed for improving the aerodynamic performance of wind turbine rotor blades. The first module conducts CFD-based aeroelastic analysis for the complete blade configuration to evaluate the turbine performance and to extract the sectional flow conditions at selected blade sections. The second module performs 2-D shape optimization of blade sections to maximize the lift-to-drag ratio under given sectional flow conditions. When the optimization is completed for all selected blade sections, the performance and sectional flow characteristics of the new blade reconfigured from the optimized sections are evaluated again by the CFD-based aeroelastic analysis. The above procedure is repeated until the solution converges satisfactorily. Applications were made for the NREL phase VI and the NREL 5MW reference wind turbines. The results showed that the optimization framework can be effectively utilized in enhancing the aerodynamic performance of wind turbine blades.

     

复合新翼型风力机叶片的气动设计及建模

基于Wilson法,用美国可再生能源实验室开发的S系列新翼型S833、S834、S835和三者的组合翼型来设计叶片,不同翼型连接处采用MATLAB程序语言的样条差值和曲线拟合法进行过渡修正,以满足气动连续性要求。在叶片设计基础上,分别计算了单翼型和复合翼型叶片的气动性能;利用有限元分析软件ANSYS建立了风轮的三维实体模型。结果表明:复合翼型叶片在较宽尖速比范围内比其它几种单翼型叶片的功率系数大,利用ANSYS软件建立的风轮实体三维模型,为风轮的结构动态及载荷等问题的进一步分析提供了技术基础。     

CFD investigation on the flatback airfoil effect of 10 MW wind turbine blade

The flatback airfoil effect on the inboard region of a large wind turbine blade was investigated by numerical analysis. Complicated flow phenomena in wind turbine blade with flatback and non-flatback airfoil were captured by Reynolds-averaged Navier–Stokes flow simulation with shear stress transport turbulence model. Although both airfoil blades were designed using blade element momentum theory to produce identical shaft power, results of three-dimensional computational fluid dynamics (CFD) flow analysis indicated that at a specific location of the root area, the flatback airfoil improved the inboard force by approximately 6 % compared with the non-flatback airfoil. We were also able to confirm that by using the flatback airfoil, the overall shaft power throughout the blade increased by 1 %, thereby restraining the bending moment exerted by the thrust force on the hub by 0.5 %. Moreover, numerical analysis results indicated that the flatback airfoil blade reduced the size of the secondary vortex around the blade root area and its progress in the secondary direction in comparison with the non-flatback airfoil blade. The shape of the flatback airfoil on the trailing edge weakened the adverse pressure gradient migrating from the lower to the upper surface. Regardless of the flatback airfoils, the tip vortex core of the outboard region formed on the suction surface leading edge and strongly rolled up by the pressure surface boundary layers due to the large pressure difference between the suction and pressure surfaces in the blade tip region. This remarkable strong tip vortex developed downstream and raked up the boundary layer of the blade trailing edge with low energy.     

Computational study on wind turbine airfoils based on active control for deformable flaps

This study numerically investigates the aerodynamic performance of Deformable trailing edge flaps (DTEFs) to reduce the fatigue and ultimate loads of wind turbine blades. A parametric design is adopted to ensure the flexible deformation of the DTEFs. Based on experimental data, a simulation of a baseline airfoil is performed with two methods: A fully coupled viscous/inviscid method employed by the XFOIL program and a Reynolds-averaged Navier–Stokes solver with a Transition SST (T-SST) turbulence model. The static and dynamic performances of DTEFs are then investigated under different flow conditions by using T-SST and maximizing its numerous advantages. Results indicate that under steady conditions, the effects of flap deflection on the integral forces and flow field structures of airfoils vary from attached flow conditions to separated conditions. The gaps between unsteady aerodynamic responses and static values are greater in attached flow and light stall conditions than in deep stall conditions. The ability of DTEFs to control the fatigue loads on wind turbine blades is verified. Specifically, DTEFs effectively alleviate the force fluctuations on blades under gust-induced swinging when wind speed measurements are considered.     

CFD Investigation on the aerodynamic characteristics of a small-sized wind turbine of NREL PHASE VI operating with a stall-regulated method

The objective of this investigation is to clearly understand the aerodynamic characteristics of a small-sized wind turbine of NREL Phase VI, operating with a stall-regulated method using CFD code. Based on this, it is possible to provide turbine designers with the aerodynamic design data to increase efficiency and improve performance in the design phase of future small-sized wind turbine blades. Moreover, a comparison was made between experimental datasets, in order to verify the reliability and validity of the analysis results. The first height in the normal direction from the surface of a rotor blade is about 0.2 mm, and the average value of y⁺ is about 7 at 7 m/s. The domain is chosen to consist of only two hexahedral mesh regions, namely the interior region, including the wind turbine blade, and the external region excluding the rectangle. The total cell number of the numerical grid is about N_g = 3.0 × 10⁶. Five different inflow velocities, in the range V_in = 7.0−25.1 m/s, are used for the rotor blade calculations. The calculated power coefficient is about 0.35 at a TSR of 5.41, corresponding to 7 m/s, and showed considerably good agreement with the experimental measurements, to within 0.08%. It was observed that the 3-D stall begins to generate near the blade root at a wind speed of 7 m/s. Therefore, root design approaches considering the appropriate selection of the angle of attack and the thickness are very important in order to generate the stall on the blade root. Through a clear understanding of aerodynamic characteristics of a small-sized NREL Phase VI wind turbine, it is expected that this useful aerodynamic data will be made available to designers as guidance in designing stall-regulated wind turbine blades in the development phase of small-sized wind turbine systems in the future.