上海交通大学学报

上海交通大学学报 >

2022 , Vol. 56 >Issue 12: 1619 - 1629

DOI: https://doi.org/10.16183/j.cnki.jsjtu.2022.110

新型电力系统与综合能源

尾缘襟翼偏转角对不同翼型的垂直轴风力机气动影响研究

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  • 1.上海交通大学 船舶海洋与建筑工程学院, 上海 200240
    2.湘潭大学 土木工程学院, 湖南 湘潭 411105
戴孟祎(1997-),女,湖南省长沙市人,硕士生,从事垂直轴风力机相关研究.

收稿日期: 2022-04-15

  网络出版日期: 2022-08-08

基金资助

国家自然科学基金项目(42076210);国家自然科学基金项目(51879160);国家自然科学基金项目(52088102);上海市科委重大研究计划(2019-01-07-00-02-E00066);湖南省自然科学基金项目(2021JJ50027);湖南省教育厅科学研究项目(21A0103);政府间国际科技创新合作重点专项(2018YFE0125100)

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Aerodynamic Effect of Deflection Angle of Trailing Edge Flap on Vertical Axis Wind Turbine with Different Airfoils

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  • 1. School of Naval Architecture, Ocean and Civil Engineering, Shanghai Jiao Tong University, Shanghai 200240, China
    2. College of Civil Engineering, Xiangtan University, Xiangtan 411105, Hunan, China

Received date: 2022-04-15

  Online published: 2022-08-08

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摘要

风能转化率偏低是阻碍垂直轴风力机市场化发展的重要原因.尾缘襟翼的设计能够改变叶片表面的流场结构,从而提高垂直轴风力机的气动性能.目前关于不同翼型垂直轴风力机的气动性能随尾缘襟翼的变化规律尚不明确.基于计算流体动力学方法,采用转捩剪切应力输运湍流模型,对3种不同分离式尾缘襟翼的翼型(NACA0018、NACA0021和NACA0024)叶片的H型垂直轴风力机气动性能进行数值研究.验证算例与已有的实验结果对比,结果吻合较好,证实本方法的可靠性.进一步考虑3种基础翼型与5组襟翼偏转角(-16°、-8°、0°、8°、16°)参数,探究垂直轴风力机的气动性能差异,分析其内在机理.研究结果表明:逆风区正向襟翼偏转角可以有效提高叶片的弯矩系数,顺风区负向襟翼偏转角对叶片的弯矩系数产生有利影响.在负向襟翼偏转角下,风能利用率受偏转影响的程度与翼型厚度呈正相关;在正向襟翼偏转角下,风能利用率受偏转影响的程度与翼型厚度呈负相关.研究成果可以为垂直轴风力机尾缘襟翼的应用提供有效参考.

关键词： 垂直轴风力机; 计算流体动力学; 尾缘襟翼; 翼型; 气动性能

本文引用格式

戴孟祎, 张志豪, 涂佳黄, 韩兆龙, 周岱, 朱宏博 . 尾缘襟翼偏转角对不同翼型的垂直轴风力机气动影响研究[J]. 上海交通大学学报, 2022 , 56(12) : 1619 -1629 . DOI: 10.16183/j.cnki.jsjtu.2022.110

Abstract

Low power efficiency is a critical factor that restricts marketization development of the vertical axis wind turbine (VAWT). The proposal of the trailing edge flap can change flow structure on blade surface, so as to improve the aerodynamic performance of VAWT. At present, the variation law of aerodynamic performance of different airfoil VAWT with trailing edge flaps is not clear. Based on the computational fluid dynamics (CFD) method and the shear stress transport (SST) model, a numerical simulation of 3 H-type VAWTs with different airfoils (NACA0018, NACA0021, and NACA0024) with separated trailing edge flap is conducted. It is found that the results of the validation case are in good agreement with experimental results, which verifies the reliability of this method. Afterwards, 3 basic airfoils and 5 groups of flap deflection angle (-16°, -8°, 0°, 8°, and 16°) parameters are selected to explore the difference in the aerodynamic performance of VAWTs. The results indicate that the positive flap deflection angle in the upwind region can effectively improve blade moment coefficient, and the negative flap deflection angle in the downwind region has a beneficial effect. For the negative flap, the degree of wind energy utilization affected by deflection is positively correlated with airfoil thickness, while for the positive flap, the opposite is true. The research results of this paper can provide an effective reference for application of trailing edge flaps of vertical axis wind turbines.

Key words： vertical axis wind turbines (VAWT); computational fluid dynamics (CFD); trailing edge flap; airfoil; aerodynamic performance

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