基于K-FWH声比拟方法的串列双圆柱气动噪声研究

陈武; 周毅

doi:10.13700/j.bh.1001-5965.2020.0365

基于K-FWH声比拟方法的串列双圆柱气动噪声研究

doi: 10.13700/j.bh.1001-5965.2020.0365

陈武,
周毅^,

南京理工大学能源与动力工程学院, 南京 210094

基金项目:

国家重点研发计划 2019YFE0104800

详细信息

通讯作者:
周毅, E-mail: yizhou@njust.edu.cn

中图分类号: V21
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- 被引次数: 0
出版历程
- 收稿日期: 2020-07-28
- 录用日期: 2020-10-18
- 网络出版日期: 2021-10-20

Investigation on aeroacoustic of tandem double cylinders by K-FWH acoustic analogy method

CHEN Wu,
ZHOU Yi^,

School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China

Funds:

National Key R & D Program of China 2019YFE0104800

More Information

Corresponding author: ZHOU Yi, E-mail: yizhou@njust.edu.cn

摘要

摘要:
为了研究串列双圆柱的气动噪声与大尺度涡脱落之间的关系，采用大涡模拟并结合K-FWH方程的方法进行研究。采用标准算例的实验结果对数值模拟方法进行了验证，证实了壁面自适应局部涡黏（WALE）大涡模拟模型结合基于K-FWH方程的声比拟方法能够较好地预测不同频率下的噪声谱密度。数值模拟结果表明：上下游圆柱的涡脱落频率相同，大尺度涡呈现反相位脱落。上游圆柱表面平均阻力系数大于下游圆柱，而下游圆柱表面的压力脉动更为剧烈。双圆柱绕流的气动噪声来源主要为偶极子噪声（包括柱体表面瞬时压强及其时间导数），其中瞬时压强的时间导数是主要的声压组成部分。在此基础上，对某一观测点的瞬时声压及其分解项之间的物理关联进行了研究。观测点的瞬时声压主要由下游圆柱产生的声压主导。由于上游涡脱落对下游圆柱的涡脱落的影响，导致下游升力系数频谱及观测点总噪声频谱呈现次级峰的现象。此外，通过希尔伯特变换发现观测点的声压脉动值不受上下游旋涡脱落的相位差影响。研究结果能为后续降低双圆柱气动噪声的研究做出贡献，给工程降噪问题提供参考。
- 串列双圆柱 /
- 气动噪声 /
- 大涡模拟 /
- K-FWH方程 /
- 涡脱落
Abstract:
To study the intrinsic relation between the aerodynamic noise of tandem double cylinders and the large-scale vortex shedding behavior, we carry out large eddy simulations combined with the K-FWH equation. Firstly, the high-fidelity of the numerical treatment is verified by a comparison with the corresponding experimental results, and it has been proved that the combination of Wall Adaptive Local Eddy (WALE) viscosity model and K-FWH equation can accurately predict the distribution of noise spectrum density under different frequencies. The numerical results show that the vortex shedding frequencies of the upstream and downstream cylinders are the exactly same and the large-scale vortex shedding prove to be antiphase shedding. The mean surface drag coefficient of the upstream cylinder is larger than that of the downstream cylinder, but the pressure fluctuations on the downstream cylindrical surface are much more significant. The main contribution of the aerodynamic noise generated by flow around tandem cylinders is the dipole noise term (i.e. effects of the instantaneous pressure on the cylinder surface and the time derivative of the pressure), in which the time derivative of instantaneous pressure is the dominant component of sound pressure. The physical correlation between the instantaneous sound pressure and the lift and drag forces at a selected observation point is also explored. It is shown that the instantaneous sound pressure is mainly dominated by the sound pressure generated by the downstream cylinder. Owing to the influence of the upstream vortex shedding on the downstream cylinder vortex shedding, the downstream lift coefficient spectrum and the total noise spectrum exhibit discernable secondary peaks. Furthermore, by the Hilbert transform, it is found that the acoustic pressure strength at the observation point is not affected by the phase difference of the upstream and downstream vortex shedding. This research contributes to the understanding of the reduction of the aerodynamic noise of tandem double cylinders and sheds light on the engineering noise reduction.
- tandem double cylinders /
- aerodynamic noise /
- large eddy simulation /
- K-FWH equation /
- vortex shedding

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图 1 X-Y平面上的计算网格

Figure 1. Computational grids of X-Y plane

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图 2 上下游圆柱表面时均压力系数C_p分布

Figure 2. Distribution of time-averaged pressure coefficient C_p on the surface of upstream and downstream cylinders

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图 3 上下游圆柱表面时均脉动压力系数C_p′分布

Figure 3. Distribution of root mean square C_p′ of pressure coefficient disturbance on the surface of upstream and downstream cylinders

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图 4 观测点处的声压级噪声功率谱密度

Figure 4. Power spectral density of sound pressure level at observation point

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图 5 远场声压级指向分布图(r/D=33.74)

Figure 5. Directivity of Sound Pressure Level at r/D=33.74

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图 6 Q值为1 000的瞬时等值面图

Figure 6. Instantaneous isosurfaces with Q=1 000 and corresponding streamwise velocity

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图 7 流场平均压力分布

Figure 7. Pressure distribution of flow field

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图 8 上下游圆柱阻力系数及升力系数随时间变化

Figure 8. Time history of drag coefficients and lift coefficients on the surface of upstream and downstream cylinders

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图 9 上下游圆柱阻力系数及升力系数频谱

Figure 9. Frequency spectra of drag coefficients and lift coefficients on the surface of upstream and downstream cylinders

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图 10 上下游圆柱升力系数相位差的时间演化

Figure 10. Time history of lift coefficient phase difference between upstream and downstream cylinders

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图 11 上下游圆柱升力系数相位差的概率密度分布

Figure 11. Probability distribution of lift coefficient phase difference between upstream and downstream cylinders

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图 12 上下游圆柱声压及分解项随时间变化

Figure 12. Time history of acoustic pressure and its decompositions on the surface of upstream and downstream cylinders

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图 13 上下游圆柱声压分解项的声压级噪声功率谱密度

Figure 13. Sound pressure level noise power spectrum of sound pressure decomposition on the surface of upstream and downstream cylinders

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图 14 上下游圆柱声压相位差的时间演化

Figure 14. Time history of acoustic pressure phase difference between upstream and downstream cylinders

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图 15 上下游圆柱声压相位差的概率密度分布

Figure 15. Probability distribution of acoustic pressure phase difference between upstream and downstream cylinders

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图 16 基于上下游圆柱声压相位差的选定观测点声压脉动值条件平均分布

Figure 16. Conditional average of acoustic pressure pulsation at selected observation points based on acoustic pressure phase difference between upstream and downstream cylinders

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表 1 上下游圆柱气动特性统计结果

Table 1. Statistic results of aerodynamic properties for upstream and downstream cylinders

算例编号	网格节点	上游平均阻力系数	下游平均阻力系数	涡脱落频率/Hz
1	1.09×10⁶	0.552 9	0.427 4	190.7
2	2.38×10⁶	0.579 7	0.452 5	181.6
3	6.65×10⁶	0.455 5	0.438 2	187.6
Min^[25]	N/A	0.334	0.294	153
Max^[25]	N/A	0.800	0.518	226

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表 2 相关项之间的相关系数

Table 2. Correlation coefficients between related terms

声压
	0.119 3	0.993 9	N/A	N/A	-0.149 4
	N/A	N/A	0.164 8	0.988 1	0.936 5

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