水下流激孔腔噪声前馈有源控制实验研究

水流流经腔体时引起的自激振荡会形成流激噪声,该文通过仿真和实验研究了水下流激孔腔噪声的主动声场控制。应用有源前馈控制方法,对比了参考信号的选取以及控制器中增加的泄露因子对控制结果的影响,并在水循环管路中对流激孔腔噪声前馈控制效果进行了实验验证。研究结果表明,前馈有源噪声控制方法可有效抑制水下流激孔腔噪声,在误差点和辅助观测点都取得了良好的降噪效果,最大降噪量大于8 dB,并且使用腔内信号作为参考的控制效果优于上游信号作为参考。     

波浪前缘降低后掠叶片前缘噪声数值模拟研究

采用大涡模拟(LES)结合Ffowcs Williams-Hawkings(FW-H)方程研究了波浪前缘对后掠叶片前缘宽频噪声的降噪效果。通过放置于叶片上游的圆柱产生各向异性的湍流,湍流与后掠叶片相互干涉产生宽频噪声。气流流速设置为40m/s,基于叶片弦长和基于圆柱直径的雷诺数约为400000和26000。在该研究中,研究对象为直前缘后掠叶片和波浪前缘后掠叶片。结果表明:当来流为各向异性的湍流时,波浪前缘可以降低叶片干涉噪声,并且在各个远场方位角下均能降低噪声总声压级而不改变其指向性,添加波浪前缘叶片降噪量约为2.3~3.4 dB。通过分析计算流场发现,波浪前缘可以改变后掠叶片前缘周围气流的流动方式,降低叶片前缘周围的压力脉动和叶片的不稳定载荷。     

低速开式空腔自激反馈流场结构与流致噪声的风洞试验研究

本文主要针对低速开式空腔流动自激振荡产生噪声问题,在0.55 m×0.4 m航空声学风洞开展了不同低马赫数(0.1/0.15/0.2/0.25)条件下长深比为2的空腔腔内流场结构和噪声特性风洞试验研究。通过利用高频粒子图像测速技术捕捉腔内流场结构,分析了腔内声波传递路径;完成空腔远场噪声和壁面压力测试,分析了噪声自激振荡模态和简正波模态,并对空腔壁面脉动压力和远场噪声进行压/声相关性研究。结果表明:空腔内部除主涡外,在腔口前缘处剪切涡与腔口后缘处碰撞涡明显存在;在875 Hz,1288 Hz,1875 Hz,2050 Hz四个频率附近出现了由声腔共振所致的单频噪声;壁面压力与远场噪声密切相关,在壁面压力主频位置有明显单频噪声出现。      

超声速三维空腔流气动噪声被动控制

抑制超声速武器舱空腔流噪声是航空领域中一项重要课题。大量研究表明在空腔前缘采用主/被动控制技术可以在一定程度上抑制腔内噪声水平。利用大涡模拟(large eddy simulation, LES)技术计算分析了Mach 1.4开式矩形方腔及波形、弧形两种前后壁几何修形后空腔的流动及噪声, 探索超声速来流条件下几何修形被动控制技术对开式方腔流噪声的抑制能力。计算结果表明波形和弧形空腔对腔内噪声均具有一定的抑制作用, 且波形空腔噪声控制效果更优。分析认为空腔几何修形能够改变空腔上方剪切层及腔内大尺度涡结构的发展演化, 进而实现对腔内噪声的控制。此外, 还应用LES方法计算分析了增厚的来流边界层条件下超声速方腔流, 发现来流边界层增厚可显著降低腔内噪声水平。      

基于仿生学结构的翼型降噪实验研究

本文运用平面传声器阵列研究了翼型常规尾缘、锯齿形尾缘及波浪形前缘的气动噪声,并在全消声室环境下实验研究了仿生学前缘、尾缘的降噪效果。设计的传声器阵列是同一平面上的单支螺旋线结构,用于二维平面声源定位。实验结果表明:在低湍流度、自由来流情况下,尾缘噪声超过前缘噪声,是翼型噪声的最主要来源,锯齿形尾缘能够有效地降低翼型的尾缘噪声;在较大的宽频范围内,锯齿形尾缘均起到很好的降噪效果,尾缘最大降噪量可以达到10 dB。而波浪形前缘的波长越短,对翼型尾缘的降噪量越明显;波浪形前缘对尾缘噪声的降噪效果在低频时较为明显,而在高频情况下,可以忽略不计。对于湍流-翼型干涉噪声的研究表明:湍流-翼型干涉噪声主要发生于翼型前缘,其声压级远大于尾缘;且锯齿尾缘几乎对湍流-翼型前缘干涉噪声的降噪没有贡献;波浪形前缘可以显著地降低湍流-翼型干涉噪声的声压级,达到良好的降噪效果。     

开孔结构流致噪声的数值模拟和机理分析

飞机机体表面的开孔设计会形成空腔结构,产生空腔流致噪声。空腔噪声的控制需要彻底认识其流动和噪声机理。以飞机的功能性开孔为例,通过半经验公式分析了其空腔噪声频率随速度的变化规律,预测了出现流声共振的工况。空腔发生流声共振时,特定频率的纯音噪声会被放大。为此,采用脱体涡模拟方法开展了开孔结构流声共振的三维非定常数值计算,分析了其流场和声场特性。其中,数值方法的准确性通过圆形空腔标模计算进行验证。结果表明,在一定速度下剪切层内的扰动将诱发空腔深度方向声模态,出现流声共振现象。此时,剪切层表现为强烈的周期性上下拍动,空腔底部和后缘区域的局部压力脉动幅值较大,声波主要由空腔后缘向上游方向辐射,上游噪声大于下游。     

金属烧结丝网在内场消声中的应用

利用试验手段研究暂冲式风洞稳定段内安装不同规格烧结金属丝网对风洞上游控制阀后气流噪声和湍流度抑制作用。试验结果表明:多层金属烧结丝网可在全频段内大幅度降低上游气流的噪声,最大可达21 dB;消声量与金属烧结丝网无量纲的压力损失系数成正比,压力降与金属烧结丝网层数呈现出非线性叠加的结果。另外发现烧结金属烧结丝网对气流速度脉动亦具有突出的抑制效果。例如,试验段马赫数Ma=1:5时,120目26层+160目26层组合烧结金属丝网出口气流速压脉动幅值减小为入口来流的18%,湍流度由11.7%降至3%。因此金属烧结丝网适合于暂冲式风洞的内场降噪。     

尾管中强脉动排气噪声辐射的特征线解

本文应用特征线法，对尾管中的强脉动流的传播问题进行了理论计算．尾管的强脉动排气，在流压超过临界值的情况下，在开口端处的流动将会阻塞，此时应取马赫数等于１代替流压等于大气压作为该处的边界条件．对于强脉动气流，流动的诸参数的起伏量可大于它们各自的时均值，本文将开口端向外的排气气流比作简源，令简源强度与排气气体的体积速度成正比，同时计及湍流噪声的贡献，这样得到的结果与实验可相比较．最后还计算了管长为一定时的噪声辐射与气室压力的关系，气压为一定时的噪声辐射和质量流通量与尾管长度的关系，以及不同气压下噪声辐射与尾管长度的关系，为指导气动声源和往复式发动机尾管的设计提供了计算方法．     

高超声速三角翼上横流不稳定性的实验研究

本文研究了三角翼迎风面边界层中的非定常横流不稳定性.实验在马赫6低噪声风洞中进行,模型为平板构型,攻角为5°和10°.通过温敏漆技术,观察到在远离头部的区域,边界层转捩阵面光滑且平行于前缘,通过Kulite高频脉动压力传感器得到的功率谱密度曲线中有明显的f≈10 kHz的扰动波信号峰值.利用基于纳米示踪的平面激光散射技术,在平行前缘方向对此区域进行流场可视化,观察到规则的向下游卷起的涡结构,形态与数值模拟中的横流涡形态一致,且涡结构的位置不是固定的,因此该10 kHz的信号为非定常横流波信号.只有在边界层为层流时,才能够观察到明显的10 kHz左右的非定常横流波信号峰值,边界层转捩中或转捩后,脉动压力的功率谱密度曲线为低频成分占主导的宽频分布.提高单位雷诺数,同一压力测点位置得到的横流波幅值先增长至饱和而后衰减.增大攻角时,横流行波幅值增长更加迅速,在较低的雷诺数下就可以增长至饱和.另外,还利用Kulite传感器阵列测量了横流波的相速度和传播角度,文中所测状态下,相速度分布在0.24—0.32倍来流速度之间,传播角度与来流方向夹角在40°—60°之间.并且,增大攻角时,横流波的相速度变大,传播角减小.     

湍流激励下柔性层贴敷加筋板自噪声的特征机理

为了研究湍流激励下柔性层贴敷加筋板自噪声的特征机理,基于湍流边界层壁面脉动压力功率谱模型、周期加筋板弯曲运动方程和固体波动方程以及力平衡与位移连续边界条件,建立了湍流边界层壁面脉动压力激励下柔性层贴敷单向周期加筋板的振动及内噪声物理模型。研究发现:橡胶外贴时对湍流激励下壳板的减振降噪主要依靠橡胶的厚度模态振动。无筋时,橡胶层外贴板较无橡胶贴敷板,主要降低湍流脉动压力的水动力学成分所致结构自噪声,距壳板0.05m时,声压降幅小于3 dB,橡胶外贴加筋板相对于加筋板,对湍流激励结构自噪声的降低基本涵盖整个波数域,距壳板0.7 m处,声压降幅仍然在20 dB左右。肋骨横截面高度或宽度每增大1倍,壳板肋骨处加速度自功率谱级降低3 dB,非肋骨处加速度及板内侧声压自功率谱则基本不变,肋骨间距改变对壳板加速度响应及板内侧声压自功率谱级皆无显著影响。      

Suppression of Helmholtz resonance using inside acoustic liner

When a Helmholtz resonator is exposed to grazing flow, an unstable shear layer at the opening can cause the occurrence of acoustic resonance under appropriate conditions. In this paper, in order to suppress the flow-induced resonance, the effects of inside acoustic liners placed on the side wall or the bottom of a Helmholtz resonator are investigated. Based on the one-dimensional sound propagation theory, the time domain impedance model of a Helmholtz resonator with inside acoustic liner is derived, and then combined with a discrete vortex model the resonant behavior of the resonator under grazing flow is simulated. Besides, an experiment is conducted to validate the present model, showing significant reduction of the peak sound pressure level achieved by the use of the side-wall liners. And the simulation results match reasonably well with the experimental data. The present results reveal that the inside acoustic liner can not only absorb the resonant sound pressure, but also suppress the fluctuation motion of the shear layer over the opening of the resonator. In all, the impact of the acoustic liners is to dampen the instability of the flow-acoustic coupled system. This demonstrates that it is a convenient and effective method for suppressing Helmholtz resonance by using inside acoustic liner.     

矩形腔体流场模拟及噪声研究

用大涡模拟方法对低速湍流引起的矩形腔体内流动进行了模拟,并应用FW-H声学类比方程分析了由流动诱发的气动噪声.数值模拟观察到了涡结构的脱体及腔体内部的自激振荡过程,通过分析得出了由流动诱发噪声的声压-频率曲线.研究发现在流速30 m/s时,流动噪声声压级在60 dB以下,348.48 Hz及其高次谐波是噪声的主要来源,流场与声场表现出耦合关系,辐射声场具有明显的方向性.腔体噪声的风洞实验研究得到了与数值模拟吻合的结果.     

Nature of inlet turbulence and strut flow disturbances and their effect on turbomachinery rotor noise

Results of an investigation in which turbomachinery rotor sound spectra were correlated with aerodynamic measurements of the inlet turbulence, strut wake, and vortex flow strengths are reported. Aerodynamic measurements included mean velocity profiles, turbulence intensity, and axial length scales. Inlet turbulence data indicate that the major effect of flow contraction appears to be the elongation of turbulent eddies. Eddies of this size dominate the blade passing frequency (BPF) tones. Decreasing eddy size by use of a grid revealed vortex flow strength to be the second major sound source. A doubling of vortex flow strength produced a 6 dB increase in the SPL of the first BPF. The sound pressure level showed less than a 2 dB change with doubling of strut wake turbulence intensity or velocity defect. A discussion of the relative importance of various sources of noise due to flow non-uniformities at the inlet is given.     

A suppressor for indoor shooting sites

Shootings at test shooting sites indoors can cause a risk of hearing loss for the workers at the site. The noise can also disturb other persons working in nearby rooms in the same building. A simple suppressor was constructed from a ventilation sound absorber. Sound level meters were installed near the shooter, to his side and in front of him, and in two nearby rooms. The suppressor solution attenuated the peak noise level to the side by 14–18 dB. Near the ear of the shooter, the amplification was 1–4 dB due to reflections. Therefore, a suppressor should have an adjustment mat between the muzzle of the weapon and the suppressor that would isolate sound from the muzzle backwards. In front of the shooter, the peak levels were attenuated by 0–3 dB due to the suppressor system. The suppressor system attenuated noise best to the side. The opening between the muzzle and the suppressor system caused the attenuation at the back of the weapon to be modest. In front, the bullet flight noise remained, and as a result there was no significant noise reduction in this direction. More noise control work is still needed, and one possibility for improvement would be a better enclosure of the imminent shooting area.     

Numerical analysis and passive control of a car side window buffeting noise based on Scale-Adaptive Simulation

Flow over an open side window in a car exhibits similar characteristics as the flow over an open cavity. Computational Fluid Dynamics (CFD) simulation over a cavity was done as a benchmark. The unsteady flow simulation was carried out using Scale Adaptive Simulation (SAS) turbulence model. The benchmark results, frequency and sound pressure levels of feedback and resonance modes, all well matched with the experimental data. Then, with the right rear window, for example, the mechanism of the side window buffeting was investigated. The simulation results show that side window buffeting noise is generated by large scale vortices and in low frequency. Furthermore, buffeting noise characteristics under several patterns of side windows opening were also numerically investigated. As a result, rear window buffeting noise is more severe than that of front window when one window open, and combination pattern of side windows open can reduce buffeting noise. To decrease the interior noise and improve car ride comfort, four suppression measures through adding a side window weather deflector at the A-pillars, constructing a cavity at the B-pillars, combination of the front and rear windows and installing a row of square cylinder deflector at the B-pillars were also studied, respectively. In conclusion, certain noise reduction can be achieved through four passive control methods.     

The use of an air bubble curtain to reduce the received sound levels for harbor porpoises (Phocoena phocoena)

In December 2005 construction work was started to replace a harbor wall in Kerteminde harbor, Denmark. A total of 175 wooden piles were piled into the ground at the waters edge over a period of 3 months. During the same period three harbor porpoises were housed in a marine mammal facility on the opposite side of the harbor. All animals showed strong avoidance reactions after the start of the piling activities. As a measure to reduce the sound exposure for the animals an air bubble curtain was constructed and operated in a direct path between the piling site and the opening of the animals' semi-natural pool. The sound attenuation effect achieved with this system was determined by quantitative comparison of pile driving impulses simultaneously measured in front of and behind the active air bubble curtain. Mean levels of sound attenuation over a sequence of 95 consecutive pile strikes were 14 dB (standard deviation (s.d.) 3.4 dB) for peak to peak values and 13 dB (s.d. 2.5 dB) for SEL values. As soon as the air bubble curtain was installed and operated, no further avoidance reactions of the animals to the piling activities were apparent.     

ACTIVE CONTROL OF PRESSURE FLUCTUATIONS DUE TO FLOW OVER HELMHOLTZ RESONATORS

Grazing flows over Helmholtz resonators may result in self-sustained flow oscillations at the Helmholtz acoustic resonance frequency of the cavity system. The associated pressure fluctuations may be undesirable. Many solutions have been proposed to solve this problem including, for example, leading edge spoilers, trailing edge deflectors, and leading edge flow diffusers. Most of these control devices are “passive”, i.e., they do not involve dynamic control systems. Active control methods, which do require dynamic controls, have been implemented with success for different cases of flow instabilities. Previous investigations of the control of flow-excited cavity resonance have used mainly one or more loudspeakers located within the cavity wall. In the present study, oscillated spoilers hinged near the leading edge of the cavity orifice were used. Experiments were performed using a cavity installed within the test section wall of a wind tunnel. A microphone located within the cavity was used as the feedback sensor. A loop shaping feedback control design methodology was used in order to ensure robust controller performance over varying flow conditions. Cavity pressure level attenuation of up to 20dB was achieved around the critical velocity (i.e., the velocity for which the fundamental excitation frequency matches the Helmholtz resonance frequency of the cavity), relative to the level in the presence of the spoiler held stationary. The required actuation effort was small. The spoiler peak displacement was typically only 4% of the mean spoiler angle (approximately 1′). The control scheme was found to provide robust performance for transient operating conditions. Oscillated leading edge spoilers offer potential advantages over loudspeakers for cavity resonance control, including a reduced encumbrance (especially for low-frequency applications), and a reduced actuation effort.