大型风力机翼型的气动载荷计算与分析

发布时间：2018-06-04 14:05

本文选题：风力机 + 翼型　；参考：《南京航空航天大学》2014年硕士论文

【摘要】：针对对S809翼型的静态和动态性能、以及PHASE VI叶片在三维旋转流场的气动性能，本文采用CFD方法开展数值模拟研究和分析。主要研究内容包括：对S809二维翼型静态性能问题，在计算过程中，使用了4种湍流模型对S809翼型进行了全湍流模拟，发现SST k-ω湍流模型的模拟效果与实验结果最为接近。但是大迎角状态下，S-A模型和k-ε模型预测的气流分离点较实验值靠后，导致升力显著高于实验值。之后又比较了SSTk-ω湍流模型模拟的翼型几个状态下的表面压力分布和流场结构，研究了翼型静态失速下的气动性能。对S809二维翼型动态性能问题，，计算得到了翼型动态失速下的升阻力迟滞曲线，并分析了翼型在典型状态下的表面压力分布与流场结构，研究S809翼型的动态失速特性。模拟结果表明，该模拟结果和之前静态性能的模拟的结论是一致的，并得到了翼型升阻力系数的迟滞曲线。不过由曲线可以看出，翼型进入失速的临界攻角较大，这和之前实验的结果略有出入，这可能是全湍流模拟的弊端，在之前进行翼型静态性能模拟的时候就已经发现了。对NREL PHASE VI三维叶片进行了旋转流场的数值模拟，得到了一些叶片的基本性能。和实验结果比较发现，Fluent的模拟结果从定性上能够准确模拟出PHASE VI风力机叶片随着风速增大进入失速和深失速的整个状态，在叶片失速前和深失速后的模拟结果和实验吻合良好，但对于临界攻角的预测上比实验结果靠后，从而导致了失速段的模拟和实验值有一定的偏差，这和之前对二维翼型的模拟结论相一致。
[Abstract]:Aiming at the static and dynamic performance of S809 airfoil and the aerodynamic performance of PHASE VI blade in three-dimensional rotating flow field, the CFD method is used to carry out numerical simulation and analysis in this paper. The main research contents include: For the static performance of S809 two-dimensional airfoil, four turbulence models are used to simulate the full turbulence of S809 airfoil. It is found that the simulation effect of SST k- 蠅 turbulence model is the closest to the experimental results. But the gas separation points predicted by the S-A model and the k- 蔚 model at high angle of attack are lower than the experimental values, and the lift force is significantly higher than the experimental value. Then the surface pressure distribution and flow field structure of airfoil simulated by SSTk- 蠅 turbulence model are compared, and the aerodynamic performance of airfoil under static stall is studied. For the dynamic performance of S809 two dimensional airfoil, the rising drag hysteresis curve is obtained under the dynamic stall of the airfoil. The surface pressure distribution and flow field structure of the airfoil under typical conditions are analyzed, and the dynamic stall characteristics of S809 airfoil are studied. The simulation results show that the simulation results are consistent with those of the previous static performance simulation, and the hysteresis curves of the lift resistance coefficient of the airfoil are obtained. However, it can be seen from the curve that the critical angle of attack of airfoil entering stall is large, which is slightly different from the results of previous experiments. This may be the disadvantage of full turbulence simulation, which has been discovered in the previous static performance simulation of airfoil. The rotating flow field of NREL PHASE VI three dimensional blade is numerically simulated and the basic performance of some blades is obtained. Comparing with the experimental results, it is found that the simulation results of fluent can accurately simulate the whole state of PHASE VI wind turbine blade entering stall and deep stall with the increase of wind speed. The simulation results before and after the blade stall are in good agreement with the experiment. However, the prediction of critical angle of attack is later than that of the experimental results, which leads to a certain deviation between the simulated and experimental values of the stall section, which is consistent with the previous simulation results for two-dimensional airfoils.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2014
【分类号】：TM315

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