| 齿形襟翼对风力机翼型气动噪声影响的数值研究 |
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| 引用本文： | 郑楠,叶学民,李春曦. 齿形襟翼对风力机翼型气动噪声影响的数值研究[J]. 太阳能学报, 2023, 44(1): 297-305. DOI: 10.19912/j.0254-0096.tynxb.2021-0922 |
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| 作者姓名： | 郑楠 叶学民 李春曦 |
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| 作者单位： | 1.华北电力大学动力工程系,保定 071003;2.华北电力大学 河北省低碳高效发电技术重点实验室,保定 071003;3.华北电力大学 保定市低碳高效发电技术重点实验室,保定 071003 |
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| 基金项目： | 国家自然科学基金（11602085） |
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| 摘 要： | 为分析齿形襟翼（SGF）尾缘对风力机翼型气动性能及噪声特性的影响，利用SST k-ω湍流模型对装设Gurney襟翼（GF）和SGF的NACA0018翼型进行数值模拟，研究齿高和齿宽对气动性能和静压分布的影响，并采用大涡模拟（LES）对气动性能最优的SGF进行噪声预估和涡结构分析。结果表明：SGF可有效提高翼型升力系数并延迟失速；SGF-0.8-6.7模型可使最大升阻比提高8.61%，失速攻角延迟3°，其在拓宽高升力区间、延迟失速等方面具有最优性能；SGF翼型上下翼面噪声无明显差异，平均声压级随攻角增大而提高；SGF-0.8-6.7模型的尾迹噪声随攻角增大呈现先增后减的变化趋势，随距离增加而降低；翼型辐射噪声呈典型偶极子状，GF噪声小攻角下降低，而大攻角下则增大，SGF在不同攻角下均降噪显著，最大降噪量达10.2 dB;SGF尾涡稳定有序，能耗及损失降低，由此使气动性能和噪声得以明显改善。
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| 关 键 词： | 齿形襟翼 气动噪声 风力机翼型 尾涡噪声 涡结构 |
| 收稿时间： | 2021-08-09 |
NUMERICAL INVESTIGATION ON AERODYNAMIC NOISE OF WIND TURBINE AIRFOILS WITH SERRATED GURNEY FLAP |
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| Zheng Nan,Ye Xuemin,Li Chunxi. NUMERICAL INVESTIGATION ON AERODYNAMIC NOISE OF WIND TURBINE AIRFOILS WITH SERRATED GURNEY FLAP[J]. Acta Energiae Solaris Sinica, 2023, 44(1): 297-305. DOI: 10.19912/j.0254-0096.tynxb.2021-0922 |
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| Authors: | Zheng Nan Ye Xuemin Li Chunxi |
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| Affiliation: | 1. Department of Power Engineering, North China Electric Power University, Baoding 071003, China;2. Hebei Key Laboratory of Low Carbon and High Efficiency Power Generation Technology, North China Electric Power University, Baoding 071003, China;3. Baoding Key Laboratory of Low Carbon and High Efficiency Power Generation Technology, North China Electric Power University, Baoding 071003, China |
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| Abstract: | To explore the influence of the trailing edge of serrated Gurney flap （SGF） on the aerodynamic performance and noise of wind turbine airfoils, the SST k-ω turbulence model is adopted to numerically study the NACA0018 airfoil with Gurney flap （GF） and SGF. The effects of serration height and width on aerodynamic performance and static pressure distribution are examined. The noise and vortex structure of SGF with optimal aerodynamic performance are investigated by LES. The results show that SGF can effectively improve the lift coefficient and delay stall of the airfoil, and SGF-0.8-6.7 model can increase the maximum lift-to-drag ratio by 8.61% and the stall angle of attack （AOA） by 3°, which presents a preferred performance in widening the high lift range and deferring the stall. There is no significant difference between the upper and lower airfoil noise of SGF, and the average sound pressure level rises with increasing AOA. The wake noise of SGF-0.8-6.7 model increases and then decreases with increasing AOA, decreases with lengthening distance. The radiation noise presents a typical dipole shape, the noise of GF reduces under small AOAs but raises under large AOAs, while that of SGF is lower than baseline under all AOAs, with the maximum reduction of 10.2 dB. The wake vortices of SGFs are more stable and orderly, the energy consumption and loss are reduced, resulting in significant improvements in the aerodynamic performance and noise. |
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| Keywords: | serrated Gurney flap aerodynamic noise wind turbine airfoil wake vortex noise vortex structure |
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