圆柱定程干涉法纯轴向模式间声速测量结果不一致性分析

气相声速是流体的基础热物理性质,圆柱定程干涉法是最精确的气相声速测量手段之一。纯轴向共振模式(以下简称纯轴向模式)是圆柱定程干涉法测量声速的常用模式,但不同纯轴向模式测量结果间存在不一致性。本文从声学共振和耗散理论的基本原理出发,结合实验测量数据,分析实验测量中的各类非理想影响因素,揭示了纯轴向模式间出现不一致性的内在机理,为圆柱定程干涉法测量的模式选择提供了理论依据。研究结果表明:奇数和偶数模式在壳体开孔和壳体振动影响方面各有优势;对于奇偶性相同的模式,模式数越大的共振模式受到边界层效应影响越小而受到分子弛豫的影响越大:在远离共鸣腔固有频率的区域内,对于模式数相差不大的纯轴向模式,其测苗结果经修正后,不一致性可降至较低水平。     

圆柱定程干涉法纯轴向模式间声速测量结果不一致性分析EI北大核心CSCD

气相声速是流体的基础热物理性质,圆柱定程干涉法是最精确的气相声速测量手段之一。纯轴向共振模式(以下简称纯轴向模式)是圆柱定程干涉法测量声速的常用模式,但不同纯轴向模式测量结果间存在不一致性。本文从声学共振和耗散理论的基本原理出发,结合实验测量数据,分析实验测量中的各类非理想影响因素,揭示了纯轴向模式间出现不一致性的内在机理,为圆柱定程干涉法测量的模式选择提供了理论依据。研究结果表明:奇数和偶数模式在壳体开孔和壳体振动影响方面各有优势;对于奇偶性相同的模式,模式数越大的共振模式受到边界层效应影响越小而受到分子弛豫的影响越大:在远离共鸣腔固有频率的区域内,对于模式数相差不大的纯轴向模式,其测苗结果经修正后,不一致性可降至较低水平。     

不同介质中超声波传播速度测量方法之比较

基于共振干涉法、相位法和反射回波法测量了空气和水中超声波的传播速度,比较了三种方法的优缺点,共振干涉法和相位法可测量气体和液体中的声速,反射回波法可测量液体和固体中的声速;相位法误差最小,共振干涉法误差相对较大。共振干涉法研究了示波器接收的交变电压随传播距离的变化规律,计算得空气和水中超声波的损耗系数分别为0.01381、0.01829,超声波在水中的损耗较大。使用Origin软件直线拟合,对实验结果进行分析和评价。     

基于超声波干涉的峰谷法计算声速值及实验误差探讨

介绍了基于Cassy Lab软件下的超声波干涉实验,提出了利用超声波干涉现象测量声速的方法.根据干涉理论推导了峰谷法测量声速的计算公式.分析和探讨了峰谷法计算声速的误差来源和改进方法.     

干涉法测量气体低压下声速的实验研究

介绍了干涉法测量气体声速的试验原理和变程干涉声速测量的实验系统,使用本套测量系统测得的气体声速的精度可达5×10-4。根据热力学原理,分析了气体声速与理想气体比定压热容之间的物理关系。在本套实验系统上测得了一批高精度的新环保制冷剂的气相声速数据,并可进一步确定其理想气体比定压热容.     

二维高超声速后台阶表面传热特性实验研究

高超声速后台阶流动是大气层内高速飞行器发动机设计、表面热防护以及高超声速拦截器红外成像窗口气动光学效应校正等诸多先进高超声速技术研发过程中所涉及的一类基础流动问题. 研究高超声速后台阶流动特性对有效提升飞行器综合性能, 进一步掌握高超声速流动机理具有重大基础 意义. 本文以二维高超声速后台阶流动为研究对象, 在KD-01高超声速激波风洞中测量了二维后台阶模型表面传热系数和表面静压, 并将实测台阶下游表面传热系数分布同采用高超声速边界层理论所得估计值进行了比较. 为进一步验证实验结果, 使用NPLS技术测量了其中一种实验状态下台阶周围流动结构. 研究发现, 对于二维高超声速后台阶流动, 台阶下游表面传热分布受台阶处边界层外缘流动特性的直接影响; 在台阶下游分离区和再附区内, 气体黏性占主导作用; 在台阶下游远场区域, 边界层流动特性趋同于平板边界层; 下游边界层基本结构取决于台阶处边界层相对厚度. 对高超声速后台阶流动, 若使用数值模拟方法研究气动热问题, 应当使用湍流模型.     

利用自发布里渊散射测量液体声速

为了克服共振干涉法在液体的热力学声速和高频声速测量方面精度不高的问题, 本文建立了一种基于自发布里渊散射原理的测定液体声速的实验装置. 利用法布里-珀罗干涉仪对散射光进行扫描滤波, 数据采集卡结合光子计数器对散射光进行探测, 设计了一种散射光信息采集分析方法. 该实验方法有效的解决了传统布里渊散射方法中信号失真的问题, 显著地提升了液体声速测量精度. 对308.6–906.2 MHz内298.15 K饱和液相CCl₄声速进行了测量, 测量结果与文献值具有较好一致性. 利用法布里-珀罗干涉仪周期性扫描的滤波原理, 通过在测量得到的布里渊频移上加减整数倍个自由波谱区, 得到了更大频率的波谱信息, 进而设计一种测定介质高频声速的方法. 对CCl₄在5406.1–5521.0 MHz频段内的声速进行了测量. 实验结果显示, CCl₄的热力学声速随频率无明显变化, 而高频声速随频率的增大呈增大趋势且远大于热力学声速, 证实CCl₄具有色散现象.     

尖楔模型结构对脉动压力测量影响实验研究

高超声速边界层转捩与湍流研究是当前空气动力学研究的一个热门领域,脉动压力测量技术在高超声速风洞背景噪声测量和边界层内扰动波发展研究实验中得到了广泛应用.脉动压力传感器由于灵敏度高、测量频率范围宽,其测量结果受多方面因素影响.文章以尖楔模型为研究对象,在常规高超声速风洞中开展了模型背面凸起对表面脉动压力测量结果影响的实验...     

声速测量及声波的波动学规律研究

声速除了可利用共振干涉法和相位比较法测量外,还可以用干涉、衍射及“洛埃镜”反射等方法测量．声速实验的改进,不仅可扩展声速测量的方法,而且也可加深学生对波动学规律和本质的理解．     

基于圆柱定程干涉法测量气体黏度的探索

黏度是流体的重要输运性质, 实验测量是获取黏度数据的基本手段. 圆柱定程干涉法是目前测量气相声速最精确的方法之一, 其测量参数为工质的声学共振频率和共振峰半宽. 共鸣腔中气相工质的黏性会导致共振频率的偏移和共振峰半宽的增加, 是声速测量中的重要非理想影响因素. 但通过对共振频率和共振峰半宽的精确测定, 并结合热边界层、进气导管、声学传感器及壳体振动等其他非理想因素的修正, 可以精确反推获得黏度. 本文从理论上探讨了应用圆柱定程干涉法测量共振频率或者共振峰半宽来得到黏度的新方法, 以氩 (Ar) 为例进行了实验验证, 测量结果与文献值具有较好一致性, 证实了方法的可行性. 关键词： 黏度 圆柱共鸣腔 共振频率 共振峰半宽     

The characteristics of sound radiation from a cylindrical shell coated with multiple compliant layers

The effect of multiple compliant layers on sound radiation from a finite cylindrical shell immersed in an infinite acoustic medium is studied. The transfer matrix is derived according to the continuous boundary conditions at each adjacent interface of the multi-layer system. With the shell theory and the acoustic wave equation, the theoretical model is developed to estimate the characteristics of sound radiation. The numerical calculation results show that the amount of the acoustic radiation power reduction increases as the wave speed or the density of the compliant layer decreases, and using multi-layer system could be more effective on noise reduction than the corresponding uniform single layer.     

Orientation fluctuation trend of Pt and ZnO layers in film bulk acoustic resonator

ZnO-based film bulk acoustic resonator (FBAR) was fabricated with many ZnO/Pt layers by magnetron sputtering. All the layers are good crystallized and highly textured. By crystallographic test, the orientation fluctuation of Pt layer increases with increasing film thickness or stack layers, whereas that of ZnO layer decreases slightly. It is consistent with ZnO grain c-axis tilting observed using transmission electron microscopy. Due to these good quality layers, the device has a high resonate frequency of 3.94 GHz.     

Roles of initial condition and vortex pairing in jet noise

This is a study of the effect of initial condition on sound generated by vortex pairing in a low Mach number, cold air jet (0·15 ⩽ M ⩽ 0·35). Data has been taken, both flow velocity fields and sound pressure far fields, in a quality anechoic facility, with careful documentation of the effect of initial condition on the sound field of jets of two different geometries (i.e., circular and elliptic). Explanations are presented for most of the observed effects by applying Möhring's theory of vortex sound to vortex filament models of coherent structures in the jets. The explanations also draw upon experience with coherent structure dynamics. The sound source of interest here is that associated with the pairing of shear layer vortices. The evolution of these vortices is greatly affected by the initial condition as is their resultant sound field. The elliptic jets with laminar boundary layers show azimuthal directivity, namely, sound pressure levels in the minor axis plane were greater than in the major axis plane. This difference decreases as the nozzle boundary layer undergoes natural transition with increasing jet speed. When the nozzle boundary layer is tripped, making it fully turbulent and removing the shear layer mode of pairing, the elliptic jet sound fields become nearly axisymmetric. What appears to be the most acoustically active phase of vortex pairing has been modeled, and the resulting sound field calculated for the circular jet. Supporting evidence is found in the experimental data for the validity of this model. The model explains the connection between the initial condition and the far field sound of jets. Interestingly, a general result of Möhring's theory is that motions of vortex rings (of any arbitrary shape) can produce only axisymmetric sound fields if the rings remain in a plane. This implies that the observed asymmetric directivity of the laminar elliptic jet sound field must be due to non-planar ring motions of the vortical structures. The primary contribution of this paper is to examine quantitatively the role of vortex pairing in the production of jet noise; the results are used to reemphasize that “pairing noise” cannot be dominant in most practical jet sound fields, contrary to claims by other researchers.     

Large amplitude ion-acoustic double layers in a plasma havingvariable-charge dust grain particles

The dust grain charging effect on large amplitude ion-acoustic double layers in a dusty plasma are investigated by the numerical calculation. The nonlinear structures of ion-acoustic double layers are examined, showing that the characteristics of the double layer sensitively depend on the dust charging effect, the influence of the ion temperature, the electrostatic potential, and the Mach number. The flow of the plasma current to the surface of dust particles increases the dust charge numbers. The effect of the ion temperature decreases the propagation speed of the ion-acoustic double layers and decreases the dust charge numbers. It is found that rarefactive double layers can propagate in this system. New findings of large amplitude ion-acoustic double layers with the dust charging effect and finite ion temperature in a dusty plasma are predicted     

Standing shear waves in rubberlike layered media

Standing shear waves arising in layered media the shear modulus of which varies in a stepwise manner at the plain boundaries between the layers are considered. A general solution is obtained for the shear wave amplitudes in a resonator with an N-layer structure the lower boundary of which performs harmonic vibrations while a finite-mass plate is attached to the upper boundary. Results of calculations and measurements are presented for a resonator with a structure in which nondeformable metal layers alternate with elastic rubberlike polymer layers. It is shown that the resonance frequencies of such a resonator can be controlled by changing the number of layers and their thicknesses. It is demonstrated, both experimentally and theoretically, that, from the resonance curve of a resonator with a two-layer structure, it is possible to determine the shear modulus of one of the layers under the condition that the elasticity of the other layer is known. The method of separation into a finite number of layers is used to analyze the resonance characteristics of a one-dimensional resonator filled with a rubberlike medium the properties of which continuously vary in the direction perpendicular to the shear displacements. The choice of the number of layers depending on the type of inhomogeneity is analyzed.     

最大负荷设计之：角区分离预测与控制

角区分离对叶轮机性能有重要影响.本文根据角区流动特征推导出描述角区三维附面层的等效二维附面层模型,并结合二维附面层分离准则,建立了角区分离判定准则.理论分析表明:为抑制角区分离,应尽量增大叶表吸力面与端壁相交二面角;为抑制角区分离,应使二面角α沿流向逐渐增大,或使二面角α沿流向逐渐减小过程尽量平缓,尤其在二面角α较小区域更应如此.鉴于此,建议风扇/压气机设计中应严格监控角区二面角大小及二面角流向变化梯度,以实现对角区分离的良好控制.结论也适用于其它叶轮机.     

Shear waves in a resonator with cubic nonlinearity

Shear waves with finite amplitude in a one-dimensional resonator in the form of a layer of a rubber-like medium with a rigid plate of finite mass at the upper surface of the layer are investigated. The lower boundary of the layer oscillates according to a harmonic law with a preset acceleration. The equation of motion for particles in a resonator is determined using a model of a medium with a single relaxation time and cubical dependence of the shear modulus on deformation. The amplitude and form of shear waves in a resonator are calculated numerically by the finite difference method at shifted grids. Resonance curves are obtained at different acceleration amplitudes at the lower boundary of a layer. It is demonstrated that, as the oscillation amplitude in the resonator grows, the value of the resonance frequency increases and the shape of the resonance curve becomes asymmetrical. At sufficiently large amplitudes, a bistability region is observed. Measurements were conducted with a resonator, where a layer with the thickness of 15 mm was manufactured of a rubber-like polymer called plastisol. The shear modulus of the polymer at small deformations and the nonlinearity coefficient were determined according to the experimental dependence of mechanical stress on shear deformation. Oscillation amplitudes in the resonator attained values when the maximum shear deformations in the layer were 0.4–0.6, which provided an opportunity to observe nonlinear effects. Measured dependences of the resonance frequency on the oscillation amplitude corresponded to the calculated ones that were obtained at a smaller value of the nonlinear coefficient.     

印度洋中北部声速剖面结构的时空变化及其物理机理研究

海洋的声速结构对水下声传播有重要影响,在印度洋中北部复杂多变的海洋物理和水文环境中, 获取声速剖面的时空统计分布规律对水下目标探测和水下声通信有重要意义. 由于垂直梯度法在声速结构分析中的局限性及其在印度洋中北部海域的适用性问题, 采用多元统计分析中的最优分割法对声速跃层进行分析,并应用最近10年的地转海洋学实时观测阵 数据对印度洋中北部海域声速剖面的特征量进行了计算,获得了声速跃层的垂直结构特征和时空变化规律; 还利用经验正交函数(EOF)表示方法,分析了印度洋中北部声速剖面拟合精度随EOF阶次的分布特点. 根据印度洋的海洋物理特征,揭示了声速剖面特征量时空演变的内在物理机理.研究结果表明: 最优分割法是适合印度洋声速结构的跃层判断方法,并提出了相应的判断准则参数; 声速剖面拟合精度随EOF阶次变化的区域性分布特征较明显,其季节性变化较小; 印度洋中北部的深海声道轴只在5°S以南明显存在,在15°S---25°S 附近海域存在三个跃层;印度洋中北部声速剖面结构可分为单跃层、双跃层Ⅰ型、 双跃层Ⅱ型和三跃层四种类型以及春夏秋冬四个季节模态. 声速剖面的分析结果对于水声传播和声纳系统的使用具有一定参考意义.     

激光聚焦扰动作用下高超声速边界层稳定性实验研究

在马赫数6、单位雷诺数3.1×10⁶/m的条件下对半锥角7°直圆锥边界层稳定性开展了实验研究.以激光聚焦于流场中局部空间而产生的膨胀冲击波作为人工添加的小扰动,分析了该扰动对高超声速圆锥边界层流动稳定性的影响.实验中利用响应频率达到兆赫兹量级的高频压力传感器对圆锥壁面脉动压力进行测量,通过对压力数据进行短时傅里叶分析和功率谱分析发现,相比于不添加激光聚焦扰动的结果,添加激光聚焦扰动使边界层中第二模态波的出现位置提前,且扰动波的幅值大幅度地增加,在相同的流向范围内,激光聚焦扰动将边界层中的扰动波从线性发展阶段推进到非线性发展阶段,其对边界层中扰动波发展的促进效果明显.同时,激光聚焦位置的不同对边界层中扰动波的发展也具有不同的影响.当激光直接聚焦于圆锥壁面X=100 mm位置时,边界层中频率为90 kHz的扰动波幅值增长最快,在X=500 mm的位置处其幅值放大倍数为3.81,相比而言当激光聚焦位置位于圆锥前方自由来流中时,边界层幅值增长最快的扰动波频率大幅减小为73 kHz,相同范围内,其幅值放大倍数为4.51倍.由此可见,当激光聚焦位置位于圆锥上游的自由来流中时,其对边界层中扰动波的影响更为显著.