风力机大厚度钝尾缘翼型数值模拟研究  

Numerical Study of Wind Turbine Airfoil with Large-thickness Blunt Trailing Edges

作　　者：李新凯[1] 戴丽萍[1] 康顺[1,2] 梁思超[1] 

机构地区：[1]华北电力大学电站设备状态监测与控制教育部重点实验室,北京102206 [2]西安现代控制技术研究所,西安710065

出　　处：《动力工程学报》2015年第11期938-943,共6页Journal of Chinese Society of Power Engineering

基　　金：国家自然科学基金资助项目(51176046);国家863高技术研究发展计划资助课题(2012AA051303)

摘　　要：以具有实验数据的风力机专用翼型DU97-W-300、DU00-W2-401为对象,研究了湍流模型和网格分布对RANS预测气动性能的影响,并在多个攻角下对比了DES与RANS的计算效果.结果表明:在翼型升力曲线的线性段,考虑转捩的T-SST模型计算值与实验值更加吻合,但在升力曲线的失速段,全湍流模型计算结果优于T-SST湍流模型,且全湍流模型中SA优于SST湍流模型;相比RANS方法,DES方法计算得到的翼型升阻力系数更加接近实验值,DES方法能更好地模拟细致的分离涡结构,所以DES方法更加适合模拟易发生分离的大厚度翼型.Taking airfoils DU97-W-300 and DU00-W2-401 with experimental data for wind turbines as the object of study, the effects of turbulence model and grid distribution on aerodynamic performance of the airfoils predicted by RANS algorithm were analyzed, while a comparison of calculation results was made between DES and RANS at multiple angles of attack. Results show that in the linear section of airfoil lift curve, the calculation values of transition SST （T-SST） model agree well with the experimental data, but in the stall segment of airfoil lift curve, the calculation results of full turbulence models are superior to T- SST turbulence model, and among the full turbulence models, SA model is better than SST model. Compared with RANS algorithm, the airfoil lift drag coefficient calculated by DES method is closer to the experimental data, which is able to better simulate the detail structure of separation vortex, and therefore is suitable for simulation of the large-thickness airfoils easy to get separated.

关 键 词：风力机 翼型 数值模拟 DES 湍流模型 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]