增升装置缝翼噪声机理与控制研究进展

魏人可; 刘宇

doi:10.11729/syltlx20230017

增升装置缝翼噪声机理与控制研究进展

doi: 10.11729/syltlx20230017

魏人可^{1, 2,},
刘宇^1, ,

1.
南方科技大学力学与航空航天工程系，深圳　518055
2.
中国空气动力研究与发展中心气动噪声控制重点实验室，绵阳　621000

基金项目: 国家自然科学基金项目（92052105，12272163）；气动噪声控制重点实验室开放课题（ANCL20200102）

详细信息

作者简介:
魏人可：（1993—），男，陕西西安人，博士研究生。研究方向：气动声学、气动力学。通信地址：广东省深圳市南山区学苑大道1088号南方科技大学工学院北楼1018A实验室（518055）。E-mail：11930881@mail.sustech.edu.cn

通讯作者:
E-mail：liuy@sustech.edu.cn

中图分类号: V211；TB533⁺.2
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- 文章访问数: 299
- HTML全文浏览量: 93
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- 被引次数: 0
出版历程
- 收稿日期: 2023-02-24
- 修回日期: 2023-04-09
- 录用日期: 2023-05-22
- 网络出版日期: 2023-06-21

Review of slat noise mechanism and control in high-lift devices

WEI Renke^{1, 2
,},
LIU Yu^{1
, ,}

1.
Department of Mechanics and Aerospace Engineering, Southern University of Science and Technology, Shenzhen 518055, China
2.
Key Laboratory of Aerodynamic Noise Control, China Aerodynamics Research and Development Center, Mianyang 621000, China

摘要

摘要: 在飞机着陆过程中，增升装置中的缝翼是机体气动噪声的重要噪声源。近几十年来，国内外研究者针对缝翼噪声开展了大量风洞试验研究，对其噪声特性和机理已有深入认识，并在流动控制和降噪技术方面进行了诸多尝试。本文综述分析了二维翼型缝翼噪声风洞试验研究方面的主要进展，介绍了3种缝翼噪声成分（低频宽频噪声、高频离散纯音噪声和低频离散纯音噪声）的产生机理。缝翼噪声控制主要有3类思路：第一类是以凹腔填充为代表的整流方法，通过消除或限制回流的产生控制噪声，效果最为显著；第二类是在缝翼尖端干扰剪切层内相干结构的形成；第三类则是从工程可行性出发，通过优化缝道和缝翼结构参数或采用前缘下垂等新构型来控制噪声。未来研究需进一步借助先进测试手段和试验方案，深入认识缝翼凹腔剪切层流动的流声耦合及其与缝翼尾缘相互作用等复杂现象，以获得更为高效的噪声控制技术。
- 增升装置 /
- 缝翼噪声 /
- 噪声机理 /
- 噪声控制
Abstract: During aircraft landing, the slat of high-lift devices is an important source of airframe aerodynamic noise. In recent decades, a large number of wind tunnel tests on slat noise have been carried out domestically and abroad. A deep understanding has been achieved on the characteristics and mechanisms of slat noise, and many attempts have been made in flow control and noise reduction technologies. Slat noise mainly includes low-frequency broadband noise, low-frequency discrete tonal noise, and high-frequency tonal noise. In this paper, the main research progress of wind tunnel testing on two-dimensional airfoil slat noise is reviewed and analyzed, and the generation mechanisms of the three slat noise components are introduced in detail. There are three main categories of control methods for slat noise. The first is the fairing method represented by the slat cove filler, which removes or limits the generation of recirculation flow and hence significantly reduces noise. The second is applied at the slat cusp to interfere with the formation of coherent structures in the shear layer. From the perspective of engineering feasibility, the third category is to optimize the slat slot and structural parameters or to adopt new configurations with leading edge droop as an example. In summary, in order to achieve efficient noise control technologies, it is necessary to deeply understand the complex phenomena in the shear layer flow of the slat cove, such as the fluid-acoustic coupling and its interference with the slat trailing edge, through advanced testing methods and experimental schemes.
- high-lift device /
- slat noise /
- noise mechanism /
- noise control

HTML全文

图 1 飞机降噪的标准化平均历史进程^[5]

Figure 1. Normalized average historical progress in aircraft noise reduction^[5]

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图 2 增升装置的主要部件示意图

Figure 2. Schematic diagram of main components of high-lift device

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图 3 缝翼噪声远场噪声频谱特征

Figure 3. Far-field spectral characteristics of slat noise

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图 4 缝翼凹腔流动特征

Figure 4. Flow phenomena in the zone of the slat cove

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图 5 缝翼凹腔展向涡量^[23]

Figure 5. Spanwise vorticity results in slat cove^[23]

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图 6 Kevlar测试段和壁装式麦克风阵列

Figure 6. Kevlar test section and wall-mounted microphone array

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图 7 远场噪声马赫数标度律^[9]

Figure 7. Far-field noise Mach number scaling^[9]

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图 8 缝翼凹腔反馈波动瞬时涡量POD重构结果^[49]

Figure 8. POD reconstruction results of instantaneous vorticity in slat cove^[49]

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图 9 方腔模型声反馈示意图^[59]

Figure 9. Schematic diagram of acoustic feedback in square cavity model^[59]

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图 10 缝翼凹腔模型声反馈示意图

Figure 10. Schematic diagram of acoustic feedback of slat cavity model

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图 11 缝翼凹腔剪切层摆动过程瞬时速度分量^[29]

Figure 11. Instantaneous velocity of shear layer oscillation process^[29]

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图 12 不同缝翼尾缘厚度的远场噪声1/3倍频程^[15]

Figure 12. 1/3 octave band SPL per foot for different slat trailing edge thicknesses^[15]

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图 13 缝翼尾缘吸力面边界层与噪声压力波之间的瞬时涡量^[72]

Figure 13. Instantaneous vorticity diagram between upper surface boundary layer and noise pressure wave^[72]

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图 14 缝翼整流方法示意图^[74]

Figure 14. Schematic diagram of slat rectification methods^[74]

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图 15 2种凹腔填充方式及其远场噪声频谱对比^[73]

Figure 15. Schematic diagram of cove filling modes and far-field noise spectrum^[73]

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图 16 半填充与全填充的表面压力信号高阶谱结果对比^[40]

Figure 16. Comparison of high order spectral results of semi-filled and fully filled surface pressure signals ^[40]

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图 17 有/无凹腔填充的速度幅值比较^[74]

Figure 17. Velocity magnitude with and without cove filler^[74]

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图 18 有/无凹腔填充的时均展向涡量比较^[74]

Figure 18. Time-averaged spanwise vorticity with and without cove filler^[74]

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图 19 缝翼密封装置^[75]

Figure 19. Slat sealing device^[75]

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图 20 缝翼凹腔波纹壁面结构示意^[81]

Figure 20. Sketch of slat cove wavy wall^[81]

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图 21 缝翼近场测点S1及主翼前缘测点M1与远场噪声的相干性^[83]

Figure 21. Coherence between the near-field sensors at the slat location S1 and main-element location M1 with the far-field microphone^[83]

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图 22 多孔缝翼尖端降噪效果^[84]

Figure 22. Noise reduction effect of porous slat cusp^[84]

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图 23 缝翼尖端附近的转捩条和涡流发生器^[15]

Figure 23. Transition strip and vortex generator near slat cusp^[15]

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图 24 等离子激励器布置方式^[86]

Figure 24. Layout of plasma actuator^[86]

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图 25 缝翼尾缘弯曲结构^[103]

Figure 25. Slat with bending trailing edge^[103]

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图 26 前缘下垂构型示意^[108]

Figure 26. Schematic diagram of leading edge droop^[108]

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