空腔可压缩流致噪声问题研究进展

王显圣; 杨党国; 刘俊; 周方奇; 施傲

doi:10.11729/syltlx20170132

空腔可压缩流致噪声问题研究进展

doi: 10.11729/syltlx20170132

王显圣^{1, 2, ,},
杨党国^{1, 2},
刘俊^{1, 2},
周方奇²,
施傲²

1.
中国空气动力研究与发展中心空气动力学国家重点实验室, 四川绵阳 621000
2.
中国空气动力研究与发展中心高速空气动力研究所, 四川绵阳 621000

基金项目:

国家自然科学基金资助项目 11602287

国家自然科学基金资助项目 11402286

详细信息

作者简介:
王显圣(1985-), 男, 吉林榆树人, 助理研究员。研究方向:空气动力学。通信地址:四川省绵阳市二环路南段6号(621000)。E-mail:xishw@hotmail.com

通讯作者:
王显圣, E-mail:xishw@hotmail.com

中图分类号: V211.5
计量
- 文章访问数: 380
- HTML全文浏览量: 265
- PDF下载量: 41
- 被引次数: 0
出版历程
- 收稿日期: 2017-10-10
- 修回日期: 2018-05-07
- 刊出日期: 2018-06-25

Progress of research on noise induced by compressible flow over cavities

Wang Xiansheng^{1, 2
, ,},
Yang Dangguo^{1, 2},
Liu Jun^{1, 2},
Zhou Fangqi²,
Shi Ao²

1.
State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang, Sichuan 621000, China
2.
High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang, Sichuan 621000, China

摘要

摘要: 空腔是一种常见的飞行器结构，高速来流条件下，空腔流致噪声成为重要噪声源，制约飞行器性能的提高。针对空腔可压缩流致噪声问题的研究进展进行综述，分析空腔流激振荡及其诱导噪声的产生机制、参数影响规律与噪声控制技术发展趋势。基于空腔非定常流动及其诱导噪声特性，总结空腔可压缩流致噪声产生、传播规律以及相关研究方法，从来流参数、空腔形态、结构振动等关键参数出发，阐述空腔可压缩流致噪声的参数影响规律，总结空腔噪声控制技术的研究现状以及存在不足。最后，对空腔可压缩流致噪声问题研究面临的挑战和发展趋势进行展望。
- 空腔 /
- 可压缩流场 /
- 气动声学 /
- 噪声控制 /
- 流激振荡
Abstract: The cavity is commonly employed in designing an aircraft. Nevertheless, the cavity flow, especially under high-speed conditions, is usually an important noise source, restricting the performance of the aircraft. The research progress on the cavity noise is summarized, including characteristics of the cavity oscillation, generation of the aeroacoustic noise, parameters which influence the cavity flow, and control of the cavity noise. The generation and propagation of the noise induced by the compressible flow over cavities are analyzed based on the characteristics of the unsteady cavity flow. Parameters that determine the cavity flow and noise are classified according to flow conditions, cavity geometry and structural vibrations. Furthermore, effects of these parameters on the cavity noise are considered, and the passive and active control techniques are summarized. Finally, challenges and future directions of researches on the cavity noise are outlined.
- cavity /
- compressible flow /
- aeroacoustics /
- noise control /
- flow-induced oscillation

HTML全文

图 1 空腔辐射声场实验与数值结果比较^[19]

Figure 1. Comparison between the experimental and numerical results of cavity noise^[19]

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图 2 空腔流场结构示意图^[10]

Figure 2. Schematic of cavity flow strucutres^[10]

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图 3 空腔剪切层尺度演化规律^[23]，其中θ表示剪切层动量厚度，L为空腔长度

Figure 3. Scale of the shear layer in a cavity flow^[23]

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图 4 空腔Tornado涡对流谱显示结果^[25]

Figure 4. Surface flow pattern of the tornado vortex pair^[25]

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图 5 超声速空腔流场波系结构阴影图(a), (b)以及扰动波(c)形成原因^[28-29]

Figure 5. Shadowgraph visualizatoin of the wave pattern in a supersonic cavity flow^[28-29]

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图 6 超声速空腔流场波系结构图^[48]

Figure 6. The wave pattern in a supersonic cavity flow^[48]

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图 7 空腔噪声谱随来流雷诺数变化曲线^[40]

Figure 7. The spectrum of cavity nosie varied with the Reynolds number^[40]

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图 8 空腔噪声谱归一化曲线^[50]

Figure 8. The nondimentionalization of the cavity noise spectrum^[50]

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图 9 空腔振动/噪声相互作用试验模型示意图^[77]

Figure 9. The test model for studing the interaction between cavity noise and structual vibration^[77]

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图 10 弹性空腔风洞试验实物图^[79]

Figure 10. The elasitic cavity in wind-tunnel experiments^[79]

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图 11 空腔流动/噪声控制措施分类^[80]

Figure 11. Classification of the cavity flow/noise control^[80]

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图 12 空腔前缘展向圆柱布置示意图^[88]

Figure 12. The spanwise cylinder at the leading edge of the cavity^[88]

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图 13 空腔前缘法向射流控制模型^[29]

Figure 13. The microjets at the leading edge of the cavity^[29]

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图 14 空腔噪声抑制效果与射流总静压比关系曲线^[29]，其中p_j为射流总压，p_∞为射流静压

Figure 14. Reduction of the cavity noise with different jet pressures^[29]

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