On the Existence of Subharmonic Screech in Choked Circular Jets from a Sharp-Edged Orifice

Experiments are performed in choked circular hot and cold nitrogen jets issuing from a 2.44 cm diameter sharp-edged orifice at a fully expanded jet Mach number of 1.85 in an effort to investigate the character of screech phenomenon. The stagnation temperature of the cold and the hot jets are 299 K and 319 K respectively. The axial distribution of the centerline Mach number was obtained with a pitot tube, while the screech data (frequency and amplitude) at different axial and radial stations were measured with the aid of microphones. The fundamental screech frequency of the hot jet is slightly increased relative to that of the cold jet. It is concluded that temperature effects on the screech amplitude are manifested with regard to the fundamental and the subharmonic even at relatively small temperature range considered.

Three-Dimensional Visualization of Shock Cell Structure and Screech Tone Emission in Underexpanded Circular Jet

The three-dimensional visualization of flow and screech-tone emission from an underexpanded circular jet is first investigated experimentally using high-speed cross-schlieren imaging and microphone measurements in the cross-sectional planes along the jet axis. This experimental technique allows the visualization of the shock-cell structure, directivity of sound intensity, and frequency spectrum in the cross-sectional planes of the screeching jet. The high-speed cross-schlieren observation of the screeching jet shows the occurrence of an asymmetrical shock-cell structure that is generated by the flapping mode in the screeching jet. This contributes to the generation of a screech tone propagating upstream along the jet axis and non-uniform sound intensities around the jet in circumferential direction. These observations by high-speed cross-schlieren imaging were validated by the microphone measurements.

矩形射流激波啸叫机理实验研究

为了解超声速欠膨胀射流激波啸叫噪声的产生机理,基于宽高比10∶1的矩形收缩喷管射流模拟实验装置,采用远场噪声测试及近场流动纹影测量相结合的方法,研究了超声速射流激波格栅结构的非定常运动规律,及其与大尺度旋涡相互作用产生啸叫噪声的过程。实验结果表明不同方位激波啸叫噪声的产生机制存在差异,射流上游和侧边方向的激波啸叫主要是由大尺度旋涡与激波格栅尖梢相互作用而形成的弧形脉冲声波,而下游方向的激波啸叫噪声主要由马赫波辐射引起。实验探究了超声速射流激波格栅结构的非定常运动激发激波啸叫弧形脉冲波的过程,并采用高斯调制的弧形脉冲序列对激波啸叫噪声进行模拟。结果表明,激波啸叫弧形脉冲声波的离散性质以及多声源机制会导致高阶激波啸叫噪声的产生。

Jet Screech Reduction with Perforated Flat Reflector

In the present experimental study, investigations have been carded out to evaluate the performance of the new control technique of jet screech with different perforated flat reflectors. Mainly two types of porous flat reflectors had been used in the experiment. One reflector （reflector-V） designed for placing the reflector surface vertical to the jet axis, when, another type of reflector （reflector-H） designed for placing the reflecting surface horizontal to the jet axis. In both cases the reflectors had been placed at the nozzle （base tube with uniform cross-sectional area） exit. The diameter of the reflector-V was 15D when the diameter of the reflector-H was 10D. The porous area of the reflector-V was 6D and 4.5D for reflector-H where D indicated the diameter of the nozzle exit. The placement of the reflector at the exit of the nozzle reduces the sound pressure at the nozzle exit. Thus the muted sound can not excite the unstable disturbance at the nozzle exit and the loop of the feedback mechanism disappeared, finally, the generation of jet screech be cancelled. The suction space located at the back side of the porous surface of the reflector-V improves the efficiency of the screech control technique. However, in the case of reflector-H, the receptivity process of feedback loop had been controlled by reducing the disturbances at the effective shock fronts as well as at the nozzle exit. The performance of the proposed method was verified with a flat reflector concept and good performance in jet screech suppression has been confirmed in the case of porous reflector.

When Squirrels Screech

松鼠(squirrel)在遇到潜在威胁时会发出尖锐刺耳的声音,研究人员最近发现,它们实际上是在使用超声波"耳语"(whisper)相互警告,而人类是听不到松鼠发出的这种声音的。这是科学家首次发现动物利用超声波作为警告的呼叫。

喷管非轴对称性对超声速欠膨胀射流激波啸叫影响实验研究

喷口外形是影响超声速射流激波啸叫模态特性的重要因素之一。对矩形射流以外的非轴对称喷管的超声速射流激波啸叫研究较为缺乏。为研究非轴对称收缩喷管对超声速射流激波啸叫的影响,针对圆形射流、正方形射流和正三角形射流的激波啸叫特性开展了实验研究。研究发现相比圆形喷管和正方形喷管,三角形喷管具有很大的抑制激波啸叫噪声的降噪潜力。采用方位角重构的方法对不同喷管外形的超声速射流激波啸叫开展了模态特性分析,结果表明,圆形射流、正方形射流和三角形射流激波啸叫A模态和B模态的基频模态特性基本一致,而A模态的倍频模态特性存在一定差异。在完全膨胀马赫数大于1.32时,三角形射流出现了特有的激波啸叫模态,其基频和倍频均为轴对称模态。

超声速喷流啸声的控制方法

通过实验比较了几种超声速喷流啸声的控制方法,包括附加三角凸台和开V形槽的收敛喷嘴。实验结果表明,带三角凸台和V槽的喷嘴对啸声幅值有明显的抑制,尤其是凸台喷嘴对啸声的模态也产生了明显的影响,但是啸声成分仍然存在,并且在上游方向依然占主导地位。在此基础上提出了一种新的控制方法——凸台加V槽的组合喷嘴,实验结果表明,组合喷嘴完全抑制了啸声,而且对于其它超音速喷流噪声成分的幅值也有一定程度的降低。最后还对各种结构喷嘴的气动推力损失进行了综合评估,结果表明组合喷嘴的推力损失介于V槽喷嘴和三角凸台喷嘴之间,平均推力损失在3%左右。

连续超声速射流对撞诱导激波聚焦的机理研究

为研究连续超声速射流对撞诱导激波聚焦的机理,在喷口间距为70mm,不同入射压力的条件下进行了自由射流对撞、二维凹面腔内的射流对撞及三维凹面腔内的射流对撞诱导激波聚焦实验。通过对比自由射流对撞辐射啸声频谱和凹面腔内射流对撞中凹面腔底部的动态压力频谱,结合纹影照片对连续超声速射流对撞诱导激波聚焦的机理进行了研究。结果表明,沿射流对撞面两侧的椭球形激波阵面的高频拉锯式振荡是连续射流对撞诱导激波聚焦的本质。当两侧的波阵面同时到达凹面腔底部发生碰撞时,激波聚焦得以完成;在一定的入射压力范围内,由于射流对撞面不稳定,两侧椭球形激波阵面不能同时到达两喷口中间的对称面,因此在自由射流对撞的辐射噪声频谱上共存两种模式的啸声。在凹面腔内的射流对撞中,凹面腔底部的压力脉动频谱上也同时存在两个频率十分接近的峰值;随着入射压力的进一步提高,两侧的椭球形激波阵面经过一段时间的协调同步后同时到达喷口中间的对称面,辐射噪声和压力脉动频谱中双频率值共存的现象消失,并统一为单一值。

超音喷流啸音发声机理的实验研究

啸音是超音速喷流噪声的三大成分之一,其特点是向上游传播的离散纯音,被认为是飞机部件声疲劳的重要因素之一。但到目前为止,啸音仍是喷流噪声研究中理解最少、预测能力最低的成分,研究表明这主要是因为啸音受环境的影响很大,如啸音的强度就受到喷流马赫数、喷流温度、喷嘴唇口厚度以及形状等的影响。本文通过实验研究了在超音速喷流情况下喷嘴唇口厚度对啸音幅值、模态等的影响。实验结果表明,随着喷嘴厚度的增加,啸音的幅值增加达到了10 db以上。啸音的频率则随着唇口厚度的增加有所减小。

基于模态分解的轴对称超声速射流啸声产生位置数值分析

不完全膨胀超声速射流的势核中会产生准周期的激波栅格结构,其与剪切层内拟序结构的相互作用会产生激波噪声.啸声是主要向上游方向传播的、具有离散频率的高强度激波噪声,其产生是受一种非线性的声反馈环机制驱动.精确定位啸声的声源位置是定量理解啸声反馈环机制和发展准确的啸声预测模型的一个关键所在.为了分析近场啸声,本文采用高精度数值方法直接求解轴对称可压缩Navier-Stokes方程,数值模拟了完全膨胀射流马赫数为1.10和1.15的圆形声速喷管欠膨胀超声速冷射流,得到了A_(1)和A_(2)两种轴对称模态啸声.通过傅里叶模态分解、本征模态分解和动态模态分解,分析了射流时序压力场和速度场,研究了啸声关联拟序流动结构的空间演化,精确定位了轴对称模态啸声的声源位置.研究表明:啸声关联拟序流动结构存在饱和态区域,啸声声波是在其饱和态区域产生并向外传播;在本文所涉及的射流马赫数范围内,A_(1)和A_(2)两种轴对称模态啸声的有效声源位置分别是在第4和第3个激波栅格结构的尾缘.

硅系延期药燃烧过程的研究

采用高速摄像技术对硅系延期药的动态燃烧过程进行了研究,计算了延期药燃烧的瞬时速度和平均速度。试验结果表明,利用高速摄像技术既可以清晰的看到延期药燃烧波阵面的传播过程,又能计算延期药燃烧速度。研究结果显示,硅系延期药在燃烧过程呈现出明显的非线形振荡燃烧特点。

矩形喷嘴超声速射流啸叫模式切换的分布性研究

为了研究矩形喷嘴超音速自由射流噪声的湍流噪声、啸叫以及激波相关宽频噪声这3类成分的分布特性及其各成分的切换特性,通过准阵列实验方式对宽高比为4的矩形喷嘴射流噪声进行了分析研究,并与理论结果进行了对比验证。通过改变射流下游测点的径向距离和测点与射流轴线的夹角,研究了射流下游噪声信号的模式特性。通过分析得到,射流下游噪声主体是湍流噪声,其基频不受角度变化影响,并且噪声模式切换的随机性较高。研究发现:随着径向距离的增大,湍流噪声基频在5和2.6kHz之间跳动,高频湍流噪声强度随之减弱,基频逐步稳定;随着射流上游测点角度的增大,啸叫的占优特性增强,在120°时啸叫的占优区间最长,而且在此位置的射流初始阶段出现了激波相关宽频噪声的占优区间,与理论结果进行对比,得出啸叫的第一阶主频和激波相关宽频噪声是向射流上游传播,并呈现一定的范围。此项研究可为工程中避免小尺度的结构疲劳破坏及对相关工作人员的声防护提供一定的参考依据。

A Numerical Study on Jet Structure and Noise Emission of Underexpanded Radial Jet

In this study, an underexpanded radial jet issuing from a small gap between two circular tubes facing each other is investigated numerically. Radial jet is formed, for example, downstream of high-pressure valves in piping system and of poppet valves in engines, and causes many industrial problems such as the noise generation and the fatigue failure of structure. In this study, the jet issuing from a small gap between two tubes with same diameter is numerically simulated. The flow field is assumed to be axisymmetric against the central axis of tubes and to be symmetric against the intermediate plane between the exits of two tubes. The axisymmetric Euler equations are solved using symmetric TVD (Total Variation Diminishing) scheme. The effects of nozzle pressure ratio and of diameter of circular tubes on the structure and the behavior of jets are examined. Typical cell structure of underexpanded jet appears in radial jet and the length of cell becomes smaller in downstream region because the jet spreads radially like a disc. The length and width of first cell are larger with higher nozzle pressure ratio. Many vortices are generated one after another near the jet boundary and move downstream, which cause the oscillation of jet. Outside of jet, two types of density waves are observed. One of them propagates toward the nozzle (toward the upstream region) and the other propagates in opposite direction. Focusing on the pressure change caused by the former waves, which is related to well-known screech, dominant frequency obtained by FFT analysis was found to become lower with higher pressure ratio and smaller diameter of tube.

如何解决车辆通过曲线时车轮产生啸叫声

概述了车辆通过曲线时车轮产生啸叫声的原因,并提出了解决啸叫声的方法。

激波和剪切层相互作用下的超音速射流

欠膨胀超音速射流处于螺旋模式下的中度欠膨胀时 ,其入射剪切层的激波具有很高强度 ,激波和剪切层发生了强烈的相互作用 ,远场辐射的拢动波出现了大间隔、交错的上下行类似螺旋锥面波形图像 ,该扰动波具有很强的向上游传播的指向性 ,导致上游噪声高于垂直喷嘴方向的声压级 .而在相对压比较低的低度欠膨胀情况下 ,或高压比下的高度欠膨胀的情形 ,入射剪切层激波强度相对较弱 ,远场辐射没有大间隔。

矩形喷口欠膨胀超声速射流对撞的实验研究

在不同喷口间距和射流压力下开展了矩形喷口欠膨胀超声速射流对撞实验并与自由射流进行了对比.实验表明:超声速射流对撞的辐射噪声中存在四种不同的啸音模式,且随喷口距离和射流压力的变化在不同模式间切换.在射流压力大于0.5MPa且喷口间距小于50mm时,射流对撞面在两个喷口外形成两道正激波之间,啸音基频维持在3kHz左右.随喷口间距的增大或射流压力的降低,射流对撞面在一侧喷口外的弓形激波与另一侧喷口外的正激波之间.对撞面也有可能出现在两个弓形激波之间,对应的啸音基频约为9kHz,但容易受扰动而回到喷口一侧或是在喷口之间大幅度振荡.当射流压力小于0.36MPa且喷口间距大于70mm后,对撞面在两个喷口之间大幅度振荡,产生基频在1kHz左右并随射流压力的降低和喷口间距的增大而降低的啸音.

流经矩形喷嘴的超音速射流啸叫模式切换的实验研究

通过实验分析比较了对于相同高度不同宽度的四种矩形喷嘴,当压力在0.2 MPa到0.8 MPa之间变动时,欠膨胀超音速自由射流的啸叫特性和对应的流场纹影结构.结果表明:不同宽高比喷嘴的超音速自由射流辐射噪声中的单频离散啸叫存在两种不同的啸叫模式,且随着射流压力的变化会出现模式间的切换.所谓模式切换是指不同模式的轮流占优和消失的现象.啸叫模式间的切换及占优区间的宽度随着喷嘴宽高比的减小而缩短.其中,宽高比为2的射流啸叫模式中的一种模式所占的射流压降区间异常小,此现象未在相关文献中提及;喷嘴宽高比为4的射流啸叫占优区间内,啸叫基频-射流压力曲线在0.49 MPa时出现了间断、跳跃现象.随着压力的降低激波纹影的轴线出现了抖动,不同宽高比下流场结构的稳定性随压力变化的规律各异.射流压力在0.70 MPa到0.45 MPa区间内,随着宽高比减小,第一波节格栅的激波致密度减弱,且出现轴向脉动,第二波节后方的流场变得紊乱;当射流压力低于0.45 MPa时,激波串结构随着宽高比的增大而趋于稳定,在此压力区间内周期性激波格栅结构较射流压力在0.45 MPa以上时有所减弱.结合啸叫频谱及纹影图分析,可初步认为,第二、三波节也会对啸叫频率的声压幅值起到反馈增强作用.

数值模拟轴对称欠膨胀超声速射流啸叫单音

为了验证本文所采用的方法对射流啸叫单音特性的预测能力,针对不同马赫数下射流流场进行了数值模拟。采用SAS-SST模型模拟二维轴对称超声速欠膨胀射流的湍流流场,空间离散采用Roe格式,时间离散采用双时间步长法,远场边界采用无反射边界条件。模拟了激波单元结构形成过程,并对比了实验和计算所得的流场纹影图、不同位置上的压力和密度值;对于射流噪声,研究了啸叫单音的波长、频率和声压级,这些数据都与实验值吻合良好,并且可以准确的捕捉到啸叫单音的模态切换。此外,当考虑有来流条件下时,啸叫噪声幅值降低,有利于削弱了射流对附近机械机构的声疲劳破坏。结果表明,该方法可用于啸叫单音预测和机理研究,为下一步高马赫数射流啸叫单音和减小啸叫单音的研究提供了重要参考。

The Effect of Reflector with Sound-Absorbing Material on Supersonic Jet Noise

This paper describes an experimental work to investigate the effect of a reflector on supersonic jet noise radiated from a convergent-divergent nozzle with a design Mach number 2.0.In the present study,a metal reflector and reflectors made of three different sound-absorbing materials(grass wool and polyurethane foam)were employed,and the reflector size was varied.Acoustic measurement is carried out to obtain the acoustic characteristics such as frequency,amplitude of screech tone and overall sound pressure level(OASPL).A high-quality schlieren optical system is used to visualize the detailed structure of supersonic jet.The results obtained show that the acoustic characteristics of supersonic jet noise are strongly dependent upon the jet pressure ratio and the reflector size.It is also found that the reflector with sound-absorbing material reduces the screech tone amplitude by about 5-13dB and the overall sound pressure levels by about 2-5dB,compared with those of the metal reflector.

The Effect of Spherical Surface on Noise Suppression of a Supersonic Jet

Experiments were carried out to eliminate the screech tone generated from a supersonic jet. Compressed air was passed through a circular convergent nozzle preceded by a straight tube of same diameter. In order to reduce the jet screech a spherical reflector was used and placed at the nozzle exit. The placement of the spherical reflector at the nozzle exit controlled the location of the image source as well as minimized the sound pressure at the nozzle exit. The weak sound pressure did not excite the unstable disturbance at the exit. Thus the loop of the feedback mechanism could not be accomplished and the jet screech was eliminated. The technique of screech reduction with a flat plate was also examined and compared with the present method. A good and effective performance in canceling the screech component by the new method was found by the investigation. Experimental results indicate that the new system suppresses not only the screech tones but also the broadband noise components and reduces the overall noise of the jet flow. The spherical reflector was found very effective in reducing overall sound pressure level in the upstream region of the nozzle compared to a flat plate. The proposed spherical reflector can, accordingly, protect the upstream noise propagation.