多孔前缘抑制圆柱⁃翼型干涉噪声实验

王勇; 郝南松; 赖庆仁; 李文建

doi:10.13224/j.cnki.jasp.20210313

多孔前缘抑制圆柱⁃翼型干涉噪声实验

doi: 10.13224/j.cnki.jasp.20210313

王勇^1,,
郝南松^1,, ,,
赖庆仁²,
李文建¹

1.
中国空气动力研究与发展中心气动噪声控制重点实验室，四川绵阳 621000
2.
中国空气动力研究与发展中心低速空气动力研究所，四川绵阳 621000

基金项目:

国家自然科学基金 11602290

中国空气动力研究与发展中心自主基金 PJD20180200

详细信息

作者简介:
王勇（1982-），男，副研究员，博士，主要从事气动噪声控制研究。E⁃mail：wangyong@cardc.cn

通讯作者:
郝南松（1983-），男，高级工程师，硕士，主要从事气动噪声机理研究。E⁃mail：hns2010@mail.ustc.edu.cn

中图分类号: V211.7
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出版历程
- 收稿日期: 2021-06-21

Experiment of rod⁃airfoil interaction noise reduction using porous leading edges

1.
Key Laboratory of Aerodynamic Noise Control，China Aerodynamics Research and Development Center，Mianyang Sichuan 621000，China
2.
Low Speed Aerodynamics Institute，China Aerodynamics Research and Development Center，Mianyang Sichuan 621000，China

摘要

摘要:
为了抑制圆柱⁃翼型干涉噪声，提出了仿生多孔前缘结构的降噪措施，并在0.55 m×0.4 m声学风洞中进行了实验验证。针对典型构型，对比确定了多孔金属泡沫降低圆柱⁃翼型干涉峰值噪声和中高频噪声的效果。3种不同ppi（pores per inch）值多孔金属泡沫的详细声学测量结果表明，所提出的多孔前缘结构能在翼型迎角为0°和10°时，分别降低最多4.10 dB和4.67 dB的圆柱⁃翼型干涉峰值噪声，且能明显降低峰值频率右侧的中高频噪声；多孔材料的占比越大、ppi值越小，整体降噪效果越好。
- 多孔材料 /
- 前缘 /
- 圆柱⁃翼型干涉噪声 /
- 噪声抑制 /
- 气动噪声
Abstract:
A method for rod⁃airfoil interaction noise reduction with a bio⁃inspired porous leading edge structure was proposed，and then verified experimentally in the 0.55 m×0.4 m acoustic wind tunnel.For typical configurations，the effects of porous metal foams in reducing the peak noise and the mid⁃to⁃high frequency noise of the rod⁃airfoil interaction were determined.The detailed acoustic measurements on three porous metal foams with different ppi （pores per inch） values showed that the proposed porous leading edges can reduce the peak value of the rod⁃airfoil interaction noise by up to 4.10 dB and 4.67 dB at the airfoil angle of attack of 0° and 10°，respectively.It can also significantly reduce the mid⁃to⁃high frequency noise on the right side of the peak frequency.The larger the proportion，the smaller the ppi value of the porous materials and the better the overall noise reduction effect.
- porous material /
- leading edge /
- rod⁃airfoil interaction noise /
- noise reduction /
- aerodynamic noise
注释:

1) 陈越

HTML

图 1 实验设置草图（未按比例，单位:mm）

Figure 1. Sketch of the experimental set⁃up（not in scale,unit:mm）

下载: 全尺寸图片幻灯片

图 2 模型示例图

Figure 2. Illustration of the tested model

下载: 全尺寸图片幻灯片

表 1 迎角 $α$ =0°时，圆柱⁃翼型干涉噪声的峰值SPL

Table 1. Peak SPL of the rod⁃airfoil interaction noise at the airfoil angle of attack of $α$ =0°

前缘构型	$V_{\infty} / (m / s)$
前缘构型	30	40	50	60
Baseline	90.12	96.10	100.63	104.69
X20Y20Z20	86.65	93.56	97.74	101.20
X50Y50Z50	87.58	94.43	98.80	102.29
X80Y80Z80	88.58	94.37	98.59	102.56
X50Y00Z00	90.35	96.18	101.34	104.66
X20Y50Z80	88.02	94.83	99.42	103.04
X80Y50Z20	86.02	92.64	97.55	101.16
注：表中粗体文字表示在风速下的最优结果，下表同。

下载: 导出CSV

表 2 迎角 $α$ =10°时，圆柱⁃翼型干涉噪声的峰值SPL

Table 2. Peak SPL of the rod⁃airfoil interaction noise at the airfoil angle of attack of $α$ =10°

前缘构型	$V_{\infty} / (m / s)$
前缘构型	30	40	50	60
Baseline	89.91	95.97	100.78	103.59
X20Y20Z20	85.24	92.05	96.45	99.55
X50Y50Z50	86.95	93.75	97.57	101.31
X80Y80Z80	88.12	94.30	98.48	101.26
X50Y00Z00	89.54	95.74	100.55	103.27
X20Y50Z80	87.04	93.69	97.66	100.91
X80Y50Z20	86.40	92.78	97.00	100.06

下载: 导出CSV

表 3 迎角 $α$ =0°时，圆柱⁃翼型干涉噪声的OASPL

Table 3. OASPL of the rod⁃airfoil interaction noise at the airfoil angle of attack of $α$ =0°

前缘构型	$V_{\infty} / (m / s)$
前缘构型	30	40	50	60
Baseline	94.74	102.66	107.50	111.95
X20Y20Z20	91.74	99.82	105.11	108.92
X50Y50Z50	92.73	100.83	105.84	109.81
X80Y80Z80	93.39	100.93	106.03	110.08
X50Y00Z00	95.11	102.81	108.20	112.48
X20Y50Z80	93.49	101.46	106.53	110.59
X80Y50Z20	91.00	99.22	104.61	108.52

下载: 导出CSV

表 4 迎角 $α$ =10°时，圆柱⁃翼型干涉噪声的OASPL

Table 4. OASPL of the rod⁃airfoil interaction noise at the airfoil angle of attack of $α$ =10°

前缘构型	$V_{\infty} / (m / s)$
前缘构型	30	40	50	60
Baseline	94.75	102.51	107.56	111.46
X20Y20Z20	90.18	98.26	103.68	106.96
X50Y50Z50	91.71	99.73	104.63	108.45
X80Y80Z80	92.81	100.34	105.52	108.78
X50Y00Z00	94.35	102.17	107.33	110.90
X20Y50Z80	91.89	99.87	105.00	108.46
X80Y50Z20	90.91	98.86	104.12	107.52

下载: 导出CSV

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