大型航空声学风洞消声室建设与校测

风洞试验是进行民用飞机机体噪声研究的重要手段。为了满足航空飞行器低噪声设计在大型风洞中进行气动噪声试验的需求,中国航空工业空气动力研究院建设了FL-10大型低速风洞全消声室。通过在FL-10风洞试验大厅壁面安装吸声尖劈、对洞体外表面进行声学处理、对支撑系统进行隔声处理、对消声换气窗进行降噪处理等手段,建成了气动噪声风洞试验所需的声学环境。按照国家标准中给定的方法,利用张线方法实现了校准声源的布置,测量了消声室内沿不同路径、不同频率噪声的衰减规律,表明FL-10风洞消声室自由场特性达到了相应标准的要求,为后续在该风洞中进行大尺寸机体模型噪声试验奠定了基础。     

运动型汽车排气系统消声器的研究

为了获得运动型排气噪声,本文研究了汽车排气系统消声器结构对运动声学品质的影响。通过改变消声器的内部结构,建立与之对应的GT-Power模型,利用一维流体动力学原理对排气系统的声学性能进行模拟和仿真,并运用声学测试平台测试节气门全开加速时的尾管噪声。验证了去除排气系统的中排消声器并在后排消声器内加入消声棉的结构,可明显提高噪声的运动性,另外,消音棉的利用可以有效降低高频噪声,消声器进气管处的穿孔结构可以有效消除中低频噪声。     

七项声学国家核准介绍

1．GB／T14259声学关于空气噪声的测量及其对人影响的评价的标准的根南本标准参照采用国际标准ISO2204＜＜声学关于空气噪声的测量及其对人影响的评价的标准的指南》．它规定了有关噪声测量及其对人们影响的评价方面的基本问题．标准中把噪声问题基本分为两大类：（豆）一个或多个噪声源所辐射的噪声大小和特性的确定，或者规定条件下声源性能预测的问题；（2）噪声对人们各种影响的评价和预测问题．同时对噪声特性作了分类，并对各类噪声绘出了简要的定义．对于第一类噪声问题，本标准叙述了需测的物理量、测量方法的选择及描述问题的严…     

中国科学院声学计量测试站通过国家技术监督局计量标准考核和认证

中国科学院声学计量测试站于1988年12月16日至17日按“中华人民共和国计量法”的要求通过了国家技术监督局的计量标准考核和计量认证。通过考核的计量标准有:电声检定标准装置(一级)、水声换能器校准测试装置(一级)和压电加速度计检定标准(二级),由此该站可以进行声学量值的传递,检定标准电容传声器、声级校准器、声级计、标准噪声源、标准水听器及压电加速度计等声学计量器具和带通滤波器、声频放大器等声学测量仪器。通过计量认证的有关产品质量检验的测试项目有:声学实验室(消声室、半消声室、混响室等)性能测试、噪声源(机电产品)声功率级测试、环境噪声和工业噪声测试、厅堂音质测试、水     

国内声学文献分类索引

声学分类：４３．１０总类；４３．１５标准；４３．２０一般线性声学；４３．２５非线性声学；强声学；４３．２８航空声学；大气声学；４３．３０水声学；４３．３５超声学，量子声学及声的物理效应；４３．４０机械振动和冲击；４３．４５统计声学；４３．５０噪声：影...     

声学消息

声学学报 ２０００年度论文奖揭晓 ２００１年１０月２２日在中国科学院声学所主楼２２９会议室召开了声学学报最佳论文评审会。会议由声学学报主编、声学学报最佳论文评委会主任马大猷院士主持，到会的评委会委员有田静、诸国桢、关定华、杨锦刚、张仁和等，列席会议的有声学学报编辑部籍顺心。 根据声学学报最佳论文评选办法，会议首先对所有推荐论文进行了充分讨论，最后以无记名投票方式选举产生了２０００年年度奖论文，最佳论文奖暂缺。会议一致认为：简晓明、李明轩、张建生《层状介质界面超声检测的理论分析和自适应噪声抵消处理》…     

基于散射矩阵法的飞机壁板声学优化设计

采用散射矩阵法分析夹层板结构声学特性,并对典型的夹层板结构即飞机壁板进行声学优化,预计飞机壁板隔声特性,获得蒙皮、隔声隔热层、内饰板及它们的组合结构的声学性能。针对尾吊飞机客舱后部噪声过大问题,通过增加铺设隔热隔声层以及部分区域优化安装阻尼层等一系列被动降噪处理方法,对主要传递路径的飞机壁板结构进行优化,降低客舱后部噪声水平,并进行试验验证。试验结果表明:散射矩阵法可快速准确获得夹层结构的隔声性能,并与混响室法测试结果吻合较好;在厚度不变的前提下,改变隔热隔声层的铺设方式和材料密度对壁板隔声性能影响较小,但在蒙皮内侧粘贴阻尼层能在一定频段范围提高壁板隔声性能;将优化的壁板构型应用到飞机后舱段侧壁板,舱内噪声水平可降低约3 dB。     

国内声学文献分类索引

（声学分类：4310总类；43．15标准；43．20一般线性声学；43．25非线性声学；强声学；43．28航空声学；大气声学；4330水声学；43．35超声学，量子声学及声的物理效应；43．40机械振动和冲击；43．45统计声学；43．50噪声：影响和控制；4355建筑声学543．60声信号处理，声全息技术；43．63生理声学；43．66心理声学；43．70语言通信；4375音乐与乐器Z4380生物声学；43．85声学测量与仪器；4388换能器；声音的产生与复制设备．）国内声学文献分类索引     

微穿孔板消声器及其在高速气流下的消声性能

《物理》杂志1974年第4期 报导了降低噪声的新手段——微穿孔板吸声结构.本文介绍新型消声器——微穿孔板消声器及其在高速气流下的消声性能.一、消声器和微穿孔板消声器随着近代工业和科学技术的发展,空气动力机械得到越来越广泛的应用,它已经成为国民经济和国防事业中不可缺少的设备.但任何空气动力过程都伴随着噪声的发生.这种由于气体的非稳定过程,或者说由于气体的扰动而产生的噪声,叫做空气动力性噪声.如航空发动机喷气噪声、内燃机和燃汽轮机噪声、压缩气体和大流量蒸汽排汽放空噪声、大型鼓风机和压缩机噪声……等等,皆属空气动力性…     

国内声学文献分类索引

（声学分类：43.10总类；43．15标准；43．20一般线性声学；43.25非线性声学；强声学；43.28航空声学；大气声学；43.30水声学；43.35超声学，量子声学及声的物理效应；43．40机械振动和冲击；43.45统计声学；43.50噪声：影响和控制；43.55建筑声学；43.60声信号处理，声全息技术；43.63生理声学；43．66心理声学；43．70语言通信；43．75音乐与乐器；43.30生物声学；43.85声学测量与仪器；43．88换能器；声音的产生与复制设备）43．10总类射线探伤中的缺陷模型及其检出灵敏度李衍无损检测，1996,18(9)：249射线探伤中的缺陷模型及其检出灵…     

Reverberation cancellation in a closed test section of a wind tunnel using a multi-microphone cesptral method

Nowadays, although aerodynamic data are still primarily sought after during wind tunnel tests, reliable acoustic measurements also become a priority for aircraft designers. In order to gather both kinds of data, aerodynamic and acoustic tests are carried out simultaneously under the same closed test section. This solution has two major drawbacks: the acoustic signals delivered by microphones may be corrupted by the boundary layer expanding on the wind tunnel walls and by the reverberant noise originating from reflective surfaces. Technological solutions can be deployed to reduce the corruption of the signals by the wind tunnel background noise. Methods based on the power cepstrum can be used to reduce reverberation effects by removing the quefrencies due to the echoes in the cepstral domain.     

高速动车组气动噪声试验与仿真分析

通过风洞试验对某高速动车组整车、受电弓及转向架远场气动噪声特性进行分析.试验结果表明,高速动车组远场气动噪声是一宽频噪声,总声能随速度的6.6次方增加;由受电弓引起的远场气动噪声主要集中在中高频,噪声峰值频率随速度变化线性增加;由转向架引起的远场气动噪声主要集中在中低频,噪声峰值频率与速度无关.在此基础上,通过大涡模拟...     

环境风对高速列车气动噪声特性的影响分析

气动噪声随着列车运行速度的提高急剧增加,是高速列车噪声的重要组成部分。本文使用缩比为1:20的三车编组模型,通过三维瞬态延迟分离涡模型求解高速列车的外流场,分析了环境风对流场结构与声源特性的影响;之后使用FW-H方程进行噪声传播计算,分析了不同速度的环境风对高速列车气动声学行为特性的影响。结果表明：高速列车主要的噪声源分布在转向架附近,在环境风的影响下,列车背风侧声源强度高于迎风侧,列车底部声源强度增幅较大。10 m/s以内的环境风会改变高速列车在尾流区域的声学指向性,并使气动噪声增加2.1~8.7 dB。相关结论可以为高速列车气动声学设计等研究提供参考。     

Obtaining absolute acoustic spectra in an aerodynamic wind tunnel

Cost effective methods for identifying and reducing sources of noise have become essential in the design of many modern transport vehicles. Whilst closed-section wind tunnels can readily evaluate aerodynamic performance, obtaining accurate acoustic spectra is often a major challenge because of the poor signal to noise ratios available. In this paper, methods of obtaining absolute spectra from the non-acoustically treated Markham wind tunnel at the University of Cambridge are discussed. Initial measurements with a small monopole source compare well with simulations and show that it is possible to obtain similar spectra from two nested acoustic arrays. However, a series of further experiments with simplified landing gear models show very different spectra from each array. By comparing measurements with simulations, it is shown that negative side lobes affect beamforming source maps. Measurements of an ‘empty tunnel’ cross spectral matrix allow the removal of sidelobes, providing much greater consistency between spectra. Finally, a dipole beamforming vector is used to account for the directivity of the landing gear noise, leading to good agreement between absolute spectra from the differently sized arrays. This analysis demonstrates that data from a phased array in a hard-walled, aerodynamic wind tunnel can provide meaningful acoustic spectra from low-noise models.     

A numerical study of the effects of design parameters on the acoustics noise of a high efficiency propeller

A numerical study of a high efficiency propeller in the aerodynamic noise generation is carried out. Based on RANS, three-dimensional numerical simulation is performed to obtain the aerodynamic performance of the propeller. The result of the aerodynamic analysis is given as input of the acoustic calculation. The sound is calculated using the Farassat 1A, which is derived from Ffowcs Williams–Hawkings equation, and compared with the data of wind tunnel. The propeller is modified for noise reduction by changing its geometrical parameters such as diameter, chord width and pitch angle. The trend of variation between aerodynamic analysis data and acoustic calculation result are compared and discussed for different modification tasks. Meaningful conclusions are drawn on the noise reduction of propeller.     

Measured wavenumber: frequency spectrum associated with acoustic and aerodynamic wall pressure fluctuations

Direct measurements of the wavenumber-frequency spectrum of wall pressure fluctuations beneath a turbulent plane channel flow have been performed in an anechoic wind tunnel. A rotative array has been designed that allows the measurement of a complete map, 63×63 measuring points, of cross-power spectral densities over a large area. An original post-processing has been developed to separate the acoustic and the aerodynamic exciting loadings by transforming space-frequency data into wavenumber-frequency spectra. The acoustic part has also been estimated from a simple Corcos-like model including the contribution of a diffuse sound field. The measured acoustic contribution to the surface pressure fluctuations is 5% of the measured aerodynamic surface pressure fluctuations for a velocity and boundary layer thickness relevant for automotive interior noise applications. This shows that for aerodynamically induced car interior noise, both contributions to the surface pressure fluctuations on car windows have to be taken into account.     

Design and performance of a small-scale aeroacoustic wind tunnel

The D5 aeroacoustic wind tunnel at Beihang University is a newly commissioned small-scale closed-circuit wind tunnel with low turbulence intensity and low background noise. The wind tunnel is built to study both aerodynamic and aeroacoustic performance of aircraft components or scaled models. The wind tunnel has two types of test sections, the closed type test section is used for aerodynamic tests while the open type test section is mainly used for aeroacoustic experiments. Both types of test section are 1 m in height and 1 m in width, and the maximum wind velocity in the test section can be up to 80 m/s. An anechoic chamber is built surrounding the test section to provide the non-reflecting condition. This paper provides an overview of design criteria and performance of the small-scale wind tunnel. The layout of the wind tunnel and some critical design treatments to improve aerodynamic and acoustic performance are discussed in detail. Some experiments are conducted to verify the performance of D5 wind tunnel, results confirm that the turbulence intensity is less than 0.08% in the core of test section and the background noise is comparable with other aeroacoustic wind tunnels. A scaled simplified nose landing gear model is also measured as a benchmark test, results reveal that noise radiated from the model is adequately higher than the background noise for a wide frequency range and remarkably consistent with other results from literatures.     

车辆天窗气动噪声的数值分析与实验研究

本文从汽车天窗气动噪声的机理入手,利用与实车几何尺寸为1:5的简化模型进行了空腔绕流的数值计算,分析了其流场结构及气动噪声产生的原因.在低速静音风洞中进行了不同流速下的流场和声场实验研究,研究了天窗不同位置的速度剪切层变化,以及不同流速下的声压级变化,发现了除了特征频率下的风振噪声,还存在较大频率范围的气动噪声,其随着...     

Acoustic and aerodynamic design and characterization of a small-scale aeroacoustic wind tunnel

The aeroacoustic wind tunnel at Brandenburg University of Technology at Cottbus is a newly commissioned research facility for the experimental study of sound generation from bodies immersed in a fluid flow. The paper discusses the design criteria for the open jet wind tunnel that provides a maximum wind speed of 72 m/s at continuous operation and may be operated with nozzles of different dimension between 35 cm diameter (circular nozzle) and 12 cm by 14.7 cm (rectangular nozzle). Experiments may be performed either in a reverberant or in an anechoic environment. Both the aerodynamic and the acoustic design of the wind tunnel components are discussed in detail. Background noise measurements in the completed facility revealed very low levels comparable to other wind tunnels. The results of aerodynamic wind tunnel calibration confirmed a uniform flow quality in the jet and a very low axial turbulence intensity which is less than 0.2% for the 35 cm nozzle and less than 0.1% for the other nozzles. A final benchmark is provided by results of successful trailing edge noise measurements on an SD7003 airfoil that are presented and compared to results from the literature.