中压气源亚/跨音速射流噪声试验台设计

在全消声室配套射流噪声试验台是开展射流噪声机理和测量方法研究的重要基础。该文研究了中压气源亚/跨音速射流噪声试验台设计,包括设计指标分析、系统软硬件组成、调试以及达到的效果等。结果表明,采用两级调压的方式可以较好地满足射流噪声研究所需的流量和压力需求,同时通过合理的流道设计,控制精度和流场品质均达到较高要求。与国际主流结果对比表明,该试验台测得的射流噪声信号具有极低的干扰噪声水平。     

周期性冲击射流噪声特性数值研究

基于大涡模拟与声类比的方法对射流速度做周期性变化的平板冲击射流的噪声特性进行了数值研究。采用正弦、三角、锯齿和矩形4种典型的周期性波形,周期变化频率的范围是5～40 Hz,以不同监测点位置下的等效连续声压级为噪声大小的评价指标,研究了波形变化和周期频率变化对周期性冲击射流噪声特性的影响。结果表明:周期性冲击射流噪声大于稳态冲击射流噪声。矩形射流的冲击噪声最大,噪声分布波动剧烈,噪声频谱呈现高频特性,其他三种波形噪声分布较为均匀,噪声频谱呈现宽频特性。周期性冲击射流噪声随着周期变化频率的增加而增大。周期变化频率的改变对矩形波形频谱特性影响较小,对于其他三种波形的频谱特性影响较大。     

合成双射流激励器振动噪声特性

合成双射流激励器工作噪声远低于合成射流激励器工作噪声, 但其噪声特性仍然限制了其应用于笔记本电脑、空调、冰箱等室内电子设备散热. 为降低合成双射流激励器整体噪声, 采用数值模拟的手段探究合成双射流激励器在不同边界条件下的振动噪声特性, 为合成双射流激励器降噪设计提供指导. 结果表明: 压电振子与壳体的振动共同影响着激励器振动噪声声压级大小; 夹持条件对振动噪声影响很大, 压电振子处于夹支条件时, 激励器的振动噪声声压级比压电振子处于简支时的激励器最大声压级低10 dB.      

不同角度圆锥冲击射流的噪声特性研究

本文针对射流冲击不同角度圆锥体的噪声特性进行了研究。通过声学测量实验获得了总声压级和噪声频谱等声学数据,分析结果表明,锥角对冲击射流噪声特性的影响随着冲击距离的变化而变化。同时,对冲击射流的流场进行了数值模拟,结合流场模拟结果与声场测量结果,对不同冲击距离与圆锥角度下冲击射流的主要噪声源进行了分析。此外,还进行了噪声指向性研究,给出了不同冲击距离、监测点位置及圆锥角度下冲击射流总声压级的分布情况。     

填充系数对脉冲爆轰发动机爆轰噪声影响的实验研究

为探索不同填充系数下气液两相脉冲爆轰发动机爆轰噪声特点,搭建了能够准确调节气液两相脉冲爆轰发动机填充系数的噪声测试实验系统,对800 mm和3000 mm处不同角度下脉冲爆轰发动机爆轰噪声特性进行了研究。结果表明,随着填充系数的增加,冲击噪声幅值与射流噪声幅值随之增大,但射流噪声幅值与冲击噪声幅值的比值降低;在爆燃与爆轰的转折点,冲击噪声幅值与射流噪声幅值显著增加;爆燃阶段下的冲击噪声幅值与射流噪声幅值增加速率小于爆轰阶段;随着距离的增加,填充系数对冲击噪声与射流噪声的增强作用有所减弱,冲击噪声的衰减速度快于射流噪声;随着填充系数的增加,当距离较小时指向性明显,当距离较大时指向性不明显。      

填充系数对脉冲爆轰发动机爆轰噪声影响的实验研究

为探索不同填充系数下气液两相脉冲爆轰发动机爆轰噪声特点,搭建了能够准确调节气液两相脉冲爆轰发动机填充系数的噪声测试实验系统,对800 mm和3000 mm处不同角度下脉冲爆轰发动机爆轰噪声特性进行了研究。结果表明,随着填充系数的增加,冲击噪声幅值与射流噪声幅值随之增大,但射流噪声幅值与冲击噪声幅值的比值降低;在爆燃与爆轰的转折点,冲击噪声幅值与射流噪声幅值显著增加;爆燃阶段下的冲击噪声幅值与射流噪声幅值增加速率小于爆轰阶段;随着距离的增加,填充系数对冲击噪声与射流噪声的增强作用有所减弱,冲击噪声的衰减速度快于射流噪声;随着填充系数的增加,当距离较小时指向性明显,当距离较大时指向性不明显。     

轴对称射流气动声场的数值模拟

构造了Kirchhoff积分和CFD计算相结合的算法,采用高精度差分格式对不同喷口马赫数的轴对称射流进行数值模拟,并以此作为近场声源,运用Kirchhoff积分方法研究远场气动噪声.数值结果表明,远场噪声具有方向性,噪声声压在离开对称轴20°处达到最大值.随着传播距离增大,噪声方向性逐渐减弱.     

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设计建立了同轴圆柱介质阻挡放电线状射流装置,并利用其实现了宽度为50mm的大尺度线状射流,并对射流长度随放电参数的变化进行了研究.研究发现,随气压、流量的增加,射流长度呈先增加后达到饱和;随激励电压的增加,射流长度增加.对氮气射流等离子体进行发射光谱诊断,表明氮气等离子体中主要是氮分子和少量氮原子,并利用光谱拟合得出射流的温度范围为290～350K.     

水下气体喷射噪声特性研究

水下气体喷射形成了复杂气液流场,同时伴有频带宽、声压大的排气噪声产生。为研究水下排气流动状态与声压频谱之间的关系,建立水下排气噪声测试系统对水下排气形成的两相流场和排气噪声频谱进行了试验研究。结果表明随着排气速度的逐渐增大,排气形成的两相流场由气泡流态过渡为射流流态。伴随着流态的转换,气液边界面附近不稳定,形成大量体积较小气泡,这些小气泡在排气形成的湍流场激振作用下产生共振,从而辐射噪声;另一方面,这些气泡体积小,表面张力大,当多个气泡相互作用以及气泡形态发生变化时将释放出更高的能量,这些能量会辐射形成噪声;喷射流场的流态对水下排气噪声中频段声压峰值有较大的影响。当射流场由气泡流态过渡为射流流态后,2 kHz处对应的声压峰值呈非线性增大。     

轴对称受限射流冲击尖端障碍物流声特性

本文研究了障碍物位于流场不同位置时轴对称射流冲击尖劈障碍物流动和声学特性。应用大涡模型(LES)数值模拟了受限射流流动特性和FW-H方程数值积分求解了远声场噪声频谱和声压级特性,并与自由射流模拟结果进行对比分析。模拟结果表明当障碍物位于自由射流流场转折界面处,自由射流涡环配对失败,使得自由射流主要噪声源被破坏,受限射流声源为障碍物产生的偶极子声源;当障碍物位于自由射流流场充分发展区,自由射流主要声源涡环配对完成,声源为自由射流段四极子声源和障碍物产生的偶极子声源,且随着离喷嘴距离增加,障碍物处流体流动速度减小,远声场相同位置声压级值逐渐减小。     

A study on generation of noise by high-speed pulsating jets

This paper describes the noise generation in an exhaust system of a reciprocating engine and focuses on the noise generated by shock/vortex interaction. The pulsating flow through the exhaust pipe consists of the compression and expansion wave, shock wave being generated by the non-linearity of the compression wave at its head. The jet noise is produced when the pulsating flow is discharged from the pipe end into atmosphere. The numerical simulation based on a finite difference method and experiment were made, the result of both of them being compared. First, the flow field in the pipe was obtained to easily discuss the characteristic of the pulsating jet in terms of the pressure history in the pipe. The jet structure was visualized by using schlieren and shadowgraph techniques. Sound pressure measurements at various locations were made in order to survey the directivity of the noise. The comparison between the result of numerical calculation and experiment showed a good agreement. A noise source related to shock/vortex interaction was confirmed by the numerical study clearly.     

Liquid jet directionality and droplet behavior during emulsification of two liquids due to acoustic cavitation

The present study numerically investigates liquid-jet characteristics of acoustic cavitation during emulsification in water/gallium/air and water/silicone oil/air systems. It is found that a high-speed liquid jet is generated when acoustic cavitation occurs near a minute droplet of one liquid in another. The velocity of liquid jet significantly depends on the ultrasonic pressure monotonically increasing as the pressure amplitude increases. Also, the initial distance between cavitation bubble and liquid droplet affects the jet velocity significantly. The results revealed that the velocity takes maximum values when the initial distance between the droplet and cavitation bubble is moderate. Surprisingly, the liquid jet direction was found to depend on the droplet properties. Specifically, the direction of liquid jet is toward the droplet in the case of water/gallium/air system, and vice versa the jet is directed from the droplet in the case of water/silicone oil/air system. The jet directionality can be explained by location of the high-pressure spot generated during the bubble contraction.     

小孔喷注消声器在宇航设备上的应用

宇航设备中的供氧排气系统在排气过程中产生了很高的喷注噪声,小孔喷注消声器是控制喷注噪声的有效措施。以喷注噪声理论为基础,利用小孔喷注消声器设计方法,为宇航设备供氧排气系统喷口设计小孔喷注消声器。设计中通过限制孔间距要求,降低孔径,实现了小孔喷注消声器的高降噪效果。加工消声器并测试,降噪效果理想。喷注噪声的计算和实测结果对比显示,两者吻合良好,误差在2 dB(A)左右,但驻压比为4时,计算结果与实测结果相差较大,分析原因是喷口后附加喇叭口结构对喷注噪声中的冲击噪声产生了影响,而经典计算公式并未考虑此种情况。小孔喷注消声器在宇航设备供氧排气系统中应用的可行性和小孔喷注消声器设计方法的可靠性得到了验证。     

Measurement of the water jet velocity at the outlet of nozzles with different profiles

Water jets accelerated by differently configured convergent nozzles of diameters ranging from 4.5 to 5.0 mm are studied. The excess pressure at the nozzle inlet varies from 5 × 10³ to 3.5 × 10⁶ Pa. Velocity measurements are carried out with a spring dynamometer and a free-running Pelton microturbine. The jet strength at the outlet of the nozzle is found to increase by a factor of 4.0–4.5 compared with the water flow strength at the inlet, which depends on the excess pressure and volume flow at the inlet. Reasons for such an effect and a possible source of the additional energy are considered. The 2D Bernoulli equation used instead of the 1D equation routinely applied in nozzle analysis leads to a negative value of the excess pressure at the nozzle exit section and in the jet. Gas evolution and cavitation enhance this effect because of a decrease in the jet density. As a result, the jet is accelerated not only by the inlet pressure but also due to the fact that the potential energy of the flowing medium decreases because of a decrease in its absolute pressure down to the technical vacuum level. The contraction of the jet by the atmospheric air and the establishment of the equilibrium (in air) pressure in the water jet eventually raise its kinetic energy through the internal energy of the air.     

Jet noise control using the dielectric barrier discharge plasma actuators

We study experimentally how plasma actuators operating on the basis of surface barrier high-frequency discharge affect jet noise characteristics. The results of investigations of air jets (100?C200 m/s) have demonstrated that the studied plasma actuators have control authority over the noise characteristics of these jets. An actuator??s effect on the jet in the applied configuration is related to acoustic discharge excitation and to a large extent is similar to the well-known Vlasov-Ginevsky effect. It has been shown that jet excitation in the case of St ?? 0.5 using the barrier-discharge plasma actuator leads to broadband amplification of jet sound radiation. The jet excitation in the case of St > 2 leads to broadband noise reduction if the action is sufficiently intensive.     

新型高频消音器对Whoosh噪声的优化

为了诊断匹配涡轮增压器的汽油车型急加速过程中产生的Whoosh噪声,并分析噪声产生的原理,确定噪声的频率特性以及噪声产生的工况,本文通过对Whoosh噪声在进气系统中贡献量的分析,按照"源-路径-响应"原则,设计出频率相应的高频穿孔消音器并将其插入到进气系统中,从噪声传递路径上进行优化与控制。通过整车道路客观数据分析和主观驾评,确定该方案切实可行,可推广至多款增压车型上应用。     

Influence of air pressure on the performance of plasma synthetic jet actuator

Plasma synthetic jet actuator(PSJA) has a wide application prospect in the high-speed flow control field for its high jet velocity.In this paper,the influence of the air pressure on the performance of a two-electrode PSJA is investigated by the schlieren method in a large range from 7 k Pa to 100 k Pa.The energy consumed by the PSJA is roughly the same for all the pressure levels.Traces of the precursor shock wave velocity and the jet front velocity vary a lot for different pressures.The precursor shock wave velocity first decreases gradually and then remains at 345 m/s as the air pressure increases.The peak jet front velocity always appears at the first appearance of a jet,and it decreases gradually with the increase of the air pressure.A maximum precursor shock wave velocity of 520 m/s and a maximum jet front velocity of 440 m/s are observed at the pressure of 7 k Pa.The averaged jet velocity in one period ranges from 44 m/s to 54 m/s for all air pressures,and it drops with the rising of the air pressure.High velocities of the precursor shock wave and the jet front indicate that this type of PSJA can still be used to influence the high-speed flow field at 7 k Pa.     

Acoustic properties of heated twin jets

A thorough experimental study of the noise characteristics of twin jets is presented in this paper. Twin round jets are investigated at typical jet engine conditions: that is, with heated high velocity flow. By varying the nozzle to nozzle spacing, it is possible to discriminate between the effects of turbulent mixing and acoustic shielding. As a result of this investigation, it was established that the turbulent mixing effects (both interaction noise generation and mixing suppression) occur for closely spaced nozzles. While acoustic shielding occurs at all nozzle spacings, it plays the dominant role at wide nozzle spacings. The levels of this acoustic shielding afforded by an adjacent jet can be sufficient to cause a nearly complete masking of the noise of the shielded jet. A significant discovery of this investigation was the importance of the layer of cooler, slower moving ambient air that exists between the twin jet plumes. This inter-jet layer causes acoustic refraction and reflection, and as the nozzle separation increases, the layer extends to shield more of the jet noise sources.     

On the amplification of broad band jet noise by a pure tone excitation

It has been found experimentally that broad band jet noise can be amplified by a pure tone excitation as much as 6 to 7 dB. The jet noise amplification effect takes place at sound pressure levels which are present in real aircraft engines. The experimental investigation was restricted to a cold jet at high subsonic Mach numbers excited by a plane sound wave coming from inside the nozzle. Based on a simplified mathematical model an attenuator has been constructed which is able to reduce the jet noise amplification significantly.