﻿ 低噪声风力机翼型设计方法及实验分析
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1. 湖北工业大学 机械工程学院, 武汉 430068;
2. 重庆大学 机械工程学院, 重庆 400030;
3. 丹麦技术大学 机械工程学院, 灵比 DK-2800

Wind turbine airfoil design method with low noise and experimental analysis
WANG Quan1 , CHEN Jin2, CHENG Jiangtao2,3, WANG Jun1, SUN Jinfeng1, YOU Ying1
1. School of Mechanical Engineering, Hubei University of Technology, Wuhan 430068, China;
2. College of Mechanical Engineering, Chongqing University, Chongqing 400030, China;
3. Department of Mechanical Engineering, Technical University of Demark, Lyngby DK-2800, Denmark
Abstract:In order to study the noise characteristic of wind turbine airfoils, the airfoil optimal design mathematic model was built based on airfoil functional integrated theory and noise calculated model. The new optimized objective function of maximizing lift/drag to noise was developed on the design angle of attack. Then, the comparison of sound pressure level between CQU-DTU-B18 and NACA-64-618 airfoil was analyzed under the same condition of wind tunnel experiment and wind speed. It is indicated that the changed trend of the predicted noise results are in agreement with that of the tested data, though there is a certain difference between the theory results and experiment data. Compared with NACA-64-618 airfoil, the CQU-DTU-B18 airfoil exhibits lower noise, which validates the feasibility of this design method. It is a guide to design wind turbine airfoil with lower noise and to reduce airfoil noise.
Key words: wind turbine airfoil     noise     wind tunnel test     sound pressure level     frequency

1 翼型噪声计算模型

1.1 湍流边界层尾缘噪声(TBL-TE)

1.2 失速噪声(SEP)

2 翼型型线设计理论

3 低噪声风力机翼型设计模型

3.1 目标函数

3.2 设计变量和约束

3.3 优化结果

 图 1 CQU-DTU-B18翼型廓线Fig. 1 CQU-DTU-B18 airfoil profile
4 实验验证

 图 2 升力系数RFOIL计算与实验结果的对比Fig. 2 Comparison of the experimental results and the RFOIL predicted lift coefficient
 图 3 升阻比RFOIL计算与实验结果的对比Fig. 3 Comparison of experimental results and the RFOIL predicted lift/drag ratio

 图 4 翼型噪声测试示意图Fig. 4 Schematic of airfoil noise test section

 图 5 CQU-DTU-B18与NACA-64-618翼型声压级对比图Fig. 5 Comparison of sound pressure level for CQU-DTU-B18 and NACA-64-618 airfoil

 dB 翼型 CL=0.50 CL=0.94 CQU-DTU-B18 56.153 57.604 NACA-64-618 58.320 61.407

5 结 论

1) 基于翼型泛函集成理论及翼型噪声计算模型,建立了低噪声翼型优化设计数学模型,提出以翼型最大升阻比与噪声比值为目标函数,采用RFOIL耦合BPM噪声计算模型预测翼型噪声值.优化设计得到一种低噪声的新翼型.该方法较好地解决了翼型气动性能与噪声之间的矛盾,为设计低噪声风力机翼型拓宽了思路.

2) 为了验证该翼型具有较低的噪声特性,对CQU-DTU-B18翼型及NACA-64-618翼型在相同的噪声风洞实验中进行了噪声测试.实验结果表明:相比NACA-64-618翼型,在相同的升力系数及风速条件下,CQU-DTU-B18翼型具有更低的噪声大小;虽然基于BPM噪声计算模型预测结果与实验数据有一定的偏差,但是升压级随频率的变化趋势是一致的,从而验证了该设计方法的可行性,同时对于翼型噪声预测具有很好的指导作用.

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#### 文章信息

WANG Quan, CHEN Jin, CHENG Jiangtao, WANG Jun, SUN Jinfeng, YOU Ying

Wind turbine airfoil design method with low noise and experimental analysis

Journal of Beijing University of Aeronautics and Astronsutics, 2015, 41(1): 23-28.
http://dx.doi.org/10.13700/j.bh.1001-5965.2014.0072