回转体边界层转捩区声辐射的预报方法研究

基于边界层理论和转捩区声辐射理论,利用Liepmann理论Krane偶极子声源改进模型,在研究回转体表面的压力梯度和声衍射损失对转捩区声辐射影响的基础上,改进了回转体边界层转捩区声辐射的预报方法。结果表明:与零压力梯度相比,逆压梯度下的转捩区将导致更高的噪声辐射,利用改进方法预报的噪声级与实验值的一致性较好。     

圆柱绕流气动声的偶极子及四极子源法定量研究

以亚临界三维圆柱绕流的气动噪声为对象,研究声类比理论中偶极子及四极子源模型在预测低Mach数流动气动声的可靠性及准确性。使用大涡模拟(LES)得到非定常流场,并依据声类比中的Curle等效偶极子面源和Lighthill四极子体源模型,提取相应的声源数据,经Fourier变换得到涡脱落频率处的声源信息,进而定量预测圆柱绕流的气动声。结果表明:Curle模型的结果与实验结果吻合良好,Lighthill体源模型预测的准确性依赖于声源区域截断,不恰当的声源截断将导致错误的声场预测。      

套管井体胶结状态对井孔中声传播的影响

从波动方程出发,利用匹配边界条件,木文推导出套管井中由单极子和多极子声源激发的井内声场定解表达式及相应的导波色散方程．利用实轴积分法和快速傅里叶交换数值方法,具体计算了套管井中不同胶结情况时由单极子声源和偶极子声源激发的井轴上不同源距处的全波列波形。结合套管井中的轴对称导波模式,分析了胶结状况对套管井中单极子和偶极子声源激发的声场的影响．研究结果表明：仅利用普通单极子声源或偶极子声源进行套管井测井,难以区分出套管胶结良好、套管与水泥为滑移胶结和自由套管情况三种不同的胶结情况;只有把普通单极子声源测井与偶极子声源测井结合起来,才有可能准确评价套管的胶结情况。     

船舶无空泡螺旋桨非定常推力脉动及其诱导线谱噪声分析

对船舶无空泡螺旋桨非定常推力脉动及其诱导的线谱噪声进行了研究,主要目的在于螺旋桨非定常推力脉动理论预报方法的验证。基于速度势面元法计算得到非均匀流场中无空泡螺旋桨的推力脉动,在大型循环水槽中利用非定常动力仪测试得到全附体船后螺旋桨的脉动推力,以脉动推力作为声源项预报得远场线谱噪声。一阶叶频非定常推力系数理论计算值与试验值最大相差29.3%,由此引起的线谱噪声差别为3.0 dB。上述结果表明,面元法预报船后螺旋桨非定常推力脉动已达到较高精度,为船舶螺旋桨低频线谱噪声的预报提供了物理基础和重要参数。      

环境因素对海-气界面低频异常声透射的影响研究

针对海中声源在海-气界面低频异常声透射问题, 根据两层媒质声传输模型, 分析了大气声速和密度与气压、气温、湿度及海水中声速和密度与海温、盐度间的关系, 研究了低频声透射和传输受温度、气压、盐度、湿度等因素的影响, 分析了各因素对声透射和传输的影响程度. 结果表明: 1) 声透射到大气中的声功率与气温、湿度负相关, 与海温、盐度、气压正相关; 2) 单极子与水平偶极子声源辐射到海中的声功率与海温、盐度负相关, 而垂直偶极子声源辐射到海中的声功率与海温、盐度正相关; 3) 声透射指向性与海温正相关, 与气温负相关; 4) 低频声透射受温度影响最大, 其次是盐度, 受气压和湿度影响较小, 垂直偶极子声源的声透射受温度影响大于水平偶极子和单极子声源.     

源于边界层转捩区的单极子声辐射

基于 Ｌｉｇｈｔｈｉｌｌ方程和 Ｇｒｅｅｎ理论,本文对边界层转捩区声辐射机理进行了分析和讨论,并对转捩区内各声源的基本类型作了分类．分析结果表明;边界层转捩区的声辐射由转捩区内处于完全湍流状态的流体流动引起的向边界展外辐射的声场以及另两个附加声场组成;边界层转捩区声源的主要类型为单极子、偶极子和四极子声源;本文的分析为Ｌａｕｃｈｌｅ模型提供了理论依据,证明了利用Ｌａｕｃｈｌｅ模型估算转捩区远场声辐射基本准确可靠．     

应用于有源声辐射控制的一种组合次级声源

在分析多通道单极子次级源控制系统的基础上,提出一种幅度调节型组合次级声源,这种组合源由两个单极子声源构成,单极子声源的间距远小于声波的波长。文中就组合次级源在自由场中对不同初级声源辐射噪声的控制进行理论分析和实验验证,并与同等条件下的单极子次级源控制系统的降噪性能进行了比较分析。数值计算和实验结果均表明,对于不同的初级声场,在次级通道数相同的情况下,组合次级源控制系统可以得到比单极子次级源控制系统高的降噪量。     

汽车涡轮增压器同步谐波噪声仿真与优化*

针对增压发动机急加速急减速时产生的增压器同步谐波噪声问题,该文通过噪声仿真技术进行分析与优化。首先,分析该噪声的特征与传播路径;其次,建立流场仿真模型。利用剪切应力输运湍流模型与分离涡流模拟湍流模型对增压器进行稳态与非稳态瞬态流场分析,提取非稳态流场的叶轮与压气机流道表面的偶极子声源;最后,建立噪声传播模型,计算该增压器压气机的进气口声场分布。通过理论分析与试验相结合的方法,优化叶轮轮缘与压气机壳体的配合型线,将该增压器噪声的阶次峰值最大降低约15.3 dB(A),消除了同步谐波噪声,且对发动机性能几乎无影响。该噪声的解决方法可以为压气机气动噪声优化提供有价值的参考。     

T型三通水管路噪声特性数值研究

水管路系统工作运行中会产生较大的管路振动和流噪声.作为偶极子声源,充液管路内湍流激发的脉动压力会形成流噪声,且激励管壁产生流激振动噪声.为了揭示水管道系统的流激振动噪声与流噪声特性的区别,基于有限元方法对不同厚度的充液管路声学模态、结构模态以及耦合模态进行计算;基于计算流体力学联合声学边界元的混合计算方法探讨变流速下流...     

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。     

The displacement-thickness theory of trailing edge noise

The problem of estimating the sound generated by turbulent boundary layer flow over the edge of a rigid half-plane is re-examined. A theory is proposed which is strictly valid at low Strouhal numbers based on boundary layer width, wherein the flow inhomogeneities are specified in terms of the fluctuations in the boundary layer displacement thickness. This enables account to be taken of changes in the properties of the turbulence as it translates past the edge, which are shown to result in the appearance of an acoustic dipole whose axis is aligned with the mean flow, and which supplements the radiation field predicted by conventional methods [1,2]. Detailed comparison is made with acoustic and surface pressures which are calculated according to the evanescent wave theory of edge noise [3–5].     

Shielding of Prof-Fan cabin noise by the fuselage boundary layer

Recent flight tests of a Prop-Fan (advanced technology turboprop) model mounted on a business aircraft revealed noise levels on the fuselage surface considerably lower than was expected from theoretical calculations and other test experience. In this paper the role of the fuselage boundary layer in shielding the surface from noise via classical refraction effects is examined. In order to study the physical phenomenon with minimum mathematical complexity, the boundary layer is modeled by concentrating its shear in an infinitesimally thin layer displaced an effective boundary layer thickness from a rigid wall. Incident energy is assumed to arrive in plane waves. For the Prop-Fan model at its design cruise Mach number of 0·8, the theory indicates a strong shielding effect. The shielding diminishes at lower flight Mach number and for larger sound wavelengths. At full scale, the shielding effects will be less than in model scale because the wavelength of the dominant noise is larger relative to the fuselage boundary layer thickness.     

Random particle methods applied to broadband fan interaction noise

Predicting broadband fan noise is key to reduce noise emissions from aircraft and wind turbines. Complete CFD simulations of broadband fan noise generation remain too expensive to be used routinely for engineering design. A more efficient approach consists in synthesizing a turbulent velocity field that captures the main features of the exact solution. This synthetic turbulence is then used in a noise source model. This paper concentrates on predicting broadband fan noise interaction (also called leading edge noise) and demonstrates that a random particle mesh method (RPM) is well suited for simulating this source mechanism. The linearized Euler equations are used to describe sound generation and propagation. In this work, the definition of the filter kernel is generalized to include non-Gaussian filters that can directly follow more realistic energy spectra such as the ones developed by Liepmann and von Kármán. The velocity correlation and energy spectrum of the turbulence are found to be well captured by the RPM. The acoustic predictions are successfully validated against Amiet’s analytical solution for a flat plate in a turbulent stream. A standard Langevin equation is used to model temporal decorrelation, but the presence of numerical issues leads to the introduction and validation of a second-order Langevin model.     

Noise simulation of aircraft engine fans by the boundary element method

Numerical simulation results of the civil aircraft engine fan stage noise in the far field are presented. Non-steady-state rotor–stator interaction is calculated the commercial software that solves the Navier–Stokes equations using differentturbulence models. Noise propagation to the far acoustic field is calculated by the boundary element method using acoustic Lighthill analogies without taking into account the mean current in the air inlet duct. The calculated sound pressure levels at points 50 m from the engine are presented, and the directional patterns of the acoustic radiation are shown. The use of the eddy resolving turbulence model to calculate rotor–stator interaction increases the accuracy in predicting fan stage noise.     

Numerical analysis of dipole sound source around high speed trains

As the maximum speed of high speed trains increases, the effect of aeroacoustic noise on the sound level on the ground becomes increasingly important. In this paper, the distribution of dipole sound sources at the bogie section of high speed trains is predicted numerically. The three-dimensional unsteady flow around a train is solved by the large eddy simulation technique. The time history of vortices shows that unstable shear layer separation at the leading edge of the bogie section sheds vortices periodically. These vortices travel downstream while growing to finally impinge upon the trailing edge of the section. The wavelength of sound produced by these vortices is large compared to the representative length of the bogie section, so that the source region can be regarded as acoustically compact. Thus a compact Green's function adapted to the shape can be used to determine the sound. By coupling the instantaneous flow properties with the compact Green's function, the distribution of dipole sources is obtained. The results reveal a strong dipole source at the trailing edge of the bogie section where the shape changes greatly and the variation of flow with time is also great. On the other hand, the bottom of the bogie section where the shape does not change, or the leading edge and boundary layer where the variation of flow with time is small, cannot generate a strong dipole source.     

水下翼型结构流噪声实验研究

为测量流激水下翼型结构的流噪声,提出了一种混响箱测量方法。在重力式水洞中搭建了一套实验测量系统,利用混响箱法测量了水下翼型结构模型的辐射声功率。在此基础上研究了流速及结构参数(厚度、肋、声学覆盖层)对其辐射声功率的影响。结果表明:当流速小于5 m/s时,辐射声功率随流速的6次方增长,符合偶极子的辐射规律;当流速大于5 m/s时,辐射声功率随流速的10土1次方规律增长,不再按偶极子的规律辐射;若对水下翼型结构模型加厚、加环肋及外部敷设黏弹性材料,均可在一定程度上抑制流噪声。此研究方法可对水下复杂结构的辐射声功率测量及结构优化设计提供一定的参考。      

Diffraction of sound from a dipole source near to a barrier or an impedance discontinuity

Pierce's formulation for the diffraction of spherical waves by a hard wedge has been extended to the case of the sound field due to a dipole source. The same approach is also used to extend a semiempirical model for sound propagation above an impedance discontinuity due to a dipole source. The resulting formulas have been validated by comparing their numerical solutions with that computed by summing the sound fields due to two closely spaced monopole sources of equal magnitude but opposite in phase. These new formulations are then used to develop a simple model for calculating the dipole sound field diffracted by a barrier above an impedance ground. Applications of these models relate to transportation noise prediction, particularly railway noise abatement, for which dipole sources are commonly used. The numerical predictions have been found to compare reasonably well with indoor measurements using piezoceramic transducers as dipole sources.     

Aeroacoustic sources of motorcycle helmet noise

The prevalence of noise in the riding of motorcycles has been a source of concern to both riders and researchers in recent times. Detailed flow field information will allow insight into the flow mechanisms responsible for the production of sound within motorcycle helmets. Flow field surveys of this nature are not found in the available literature which has tended to focus on sound pressure levels at ear as these are of interest for noise exposure legislation. A detailed flow survey of a commercial motorcycle helmet has been carried out in combination with surface pressure measurements and at ear acoustics. Three potential noise source regions are investigated, namely, the helmet wake, the surface boundary layer and the cavity under the helmet at the chin bar. Extensive information is provided on the structure of the helmet wake including its frequency content. While the wake and boundary layer flows showed negligible contributions to at-ear sound the cavity region around the chin bar was identified as a key noise source. The contribution of the cavity region was investigated as a function of flow speed and helmet angle both of which are shown to be key factors governing the sound produced by this region.     

Sound radiation from inflow turbulence in axial flow fans

The sound radiated when inflow turbulence is present in axial flow fans has been investigated. Theoretically, two noise radiating mechanisms can be identified: (i) interaction of turbulence with the rotor potential field results in a quadrupole-type volume source distribution, producing “flow-interaction” noise; (ii) impingement of turbulence on the blades results in a dipole-type (fluctuating force) surface source distribution, producing “fluctuating lift” noise. A theoretical expression for the flow interaction sound power in the upstream radiation field has been developed, in terms of parameters that can be experimentally determined by near field flow measurements involving spatial cross-correlations of the fluctuating axial velocity, with respect to both radial and circumferential position. Both these measurements and radiated sound pressure measurements have been made for eight- and ten-bladed rotors of relatively low tip Mach number (< 0·3). The sound pressure measurements revealed the occurrence of band-spreading of discrete tones at the blade passing frequency and its harmonics, as would be theoretically predicted for quadrupole-type sources here. The theoretical predictions and the measurements, respectively, of the sound power radiated upstream were compared. The results indicated that, for the fans tested, the “fluctuating lift” noise strongly predominated over the “flow-interaction” noise. The observed sound power levels were consistent with levels estimated from the theory.