Open rotor centrebody scattering

This paper investigates the effect of acoustic scattering from the centrebody of an advanced open rotor engine. The physical mechanisms governing the scattering process are investigated and formulae for predicting noise levels are presented. It is found that centrebody scattering has a negligible effect on rotor-alone tones produced by a subsonic rotor, however, the scattering effect can be significant for rotor-alone tones produced by a supersonic rotor and certain rotor–rotor interaction tones. The paper concludes with an analysis which shows that the centrebody scattered field may be significantly reduced by applying an acoustic liner to the centrebody surface.     

A moving medium formulation for prediction of propeller noise at incidence

This paper presents a time domain formulation for the sound field radiated by moving bodies in a uniform steady flow with arbitrary orientation. The aim is to provide a formulation for prediction of noise from body so that effects of crossflow on a propeller can be modeled in the time domain. An established theory of noise generation by a moving source is combined with the moving medium Green's function for derivation of the formulation. A formula with Doppler factor is developed because it is more easily interpreted and is more helpful in examining the physic of systems. Based on the technique presented, the source of asymmetry of the sound field can be explained in terms of physics of a moving source. It is shown that the derived formulation can be interpreted as an extension of formulation 1 and 1A of Farassat based on the Ffowcs Williams and Hawkings (FW–H) equation for moving medium problems. Computational results for a stationary monopole and dipole point source in moving medium, a rotating point force in crossflow, a model of helicopter blade at incidence and a propeller case with subsonic tips at incidence verify the formulation.     

On vortex–airfoil interaction noise including span-end effects,with application to open-rotor aeroacoustics

A linear analytical model is developed for the chopping of a cylindrical vortex by a flat-plate airfoil, with or without a span-end effect. The major interest is the contribution of the tip–vortex produced by an upstream rotating blade in the rotor–rotor interaction noise mechanism of counter-rotating open rotors. Therefore the interaction is primarily addressed in an annular strip of limited spanwise extent bounding the impinged blade segment, and the unwrapped strip is described in Cartesian coordinates. The study also addresses the interaction of a propeller wake with a downstream wing or empennage. Cylindrical vortices are considered, for which the velocity field is expanded in two-dimensional gusts in the reference frame of the airfoil. For each gust the response of the airfoil is derived, first ignoring the effect of the span end, assimilating the airfoil to a rigid flat plate, with or without sweep. The corresponding unsteady lift acts as a distribution of acoustic dipoles, and the radiated sound is obtained from a radiation integral over the actual extent of the airfoil. In the case of tip–vortex interaction noise in CRORs the acoustic signature is determined for vortex trajectories passing beyond, exactly at and below the tip radius of the impinged blade segment, in a reference frame attached to the segment. In a second step the same problem is readdressed accounting for the effect of span end on the aerodynamic response of a blade tip. This is achieved through a composite two-directional Schwarzschild's technique. The modifications of the distributed unsteady lift and of the radiated sound are discussed. The chained source and radiation models provide physical insight into the mechanism of vortex chopping by a blade tip in free field. They allow assessing the acoustic benefit of clipping the rear rotor in a counter-rotating open-rotor architecture.     

The possibility of efficient calculation of the scattering amplitude caused by an inclusion in a complicated incident field

The algorithm of calculating the scattering amplitude for an inclusion in a homogeneous medium is described. The algorithm is based on the ability of the scattering amplitude to satisfy the homogeneous Helmholtz equation in the variables coinciding with the coordinates of the inclusion. The solution to the problem is represented as a series expansion in inverse powers of the source-inclusion distance. The expression for the scattering amplitude of a multipole point source is derived. Examples of calculating the scattering amplitude by the proposed method are presented.     

中国散裂中子源多功能反射谱仪屏蔽设计

本文介绍了利用蒙特卡罗粒子输运程序MCNPX2.5.0进行中国散裂中子源多功能反射谱仪屏蔽设计的屏蔽需求、辐射源项、计算方法和设计结果等内容.在计算中考虑慢化器泄漏源项、中子导管损失源项等不同辐射源项,使用分步计算和源项角度偏移、源项能量偏移、几何分裂等多种减方差方法,在保证计算结果精度的同时提高计算速度.在谱仪束线传输段、第二中子开关、散射室等的屏蔽计算中,通过比较了不同条件下的所需屏蔽确定最终屏蔽设计,确保谱仪屏蔽外人员可到达区域的剂量低于安全限值2.5μSv/h.     

Study of scattering from turbulence structure generated by propeller with FLUENT

In this article, the turbulence structure generated by a propeller is simulated with the computational fluid dynamics (CFD) software FLUENT. With the method of moments, the backscattering radar cross sections (RCS) of the turbulence structure are calculated. The scattering results can reflect the turbulent intensity of the wave profiles. For the wake turbulence with low rotating speed, the scattering intensity of HH polarization is much smaller than VV polarization at large incident angles. When the turbulence becomes stronger with high rotating speed, the scattering intensity of HH polarization also becomes stronger at large incident angles, which is almost the same with VV polarization. And also, the bistatic scattering of the turbulence structure has the similar situation. These scattering results indicate that the turbulence structure can also give rise to an anomaly compared with traditional sea surface. The study of electromagnetic (EM) scattering from turbulence structure generated by the propeller can help in better understanding of the scattering from different kinds of waves and provide more bases to explain the anomalies of EM scattering from sea surfaces.     

The diffraction of sound by an impedance sphere in the vicinity of a ground surface

The problem of sound diffraction by an absorbing sphere due to a monopole point source was investigated. The theoretical models were extended to consider the case of sound diffraction by an absorbing sphere with a locally reacting boundary or an extended reaction boundary placed above an outdoor ground surface of finite impedance. The separation of variables techniques and appropriate wave field expansions were used to derive the analytical solutions. By adopting an image method, the solutions could be formulated to account for the multiple scattering of sound between the sphere and its image near a flat acoustically hard or an impedance ground. The effect of ground on the reflected sound fields was incorporated in the theoretical model by employing an approximate analytical solution known as the Weyl-van der Pol formula. An approximation solution was suggested to determine the scattering coefficients from a set of linearly coupled complex equations for an absorbing sphere not too close to the ground. The approximate method substantially reduced the computational time for calculating the sound field. Preliminary measurements were conducted to characterize the acoustical properties of an absorbing sphere made of open cell polyurethane foam. Subsequent experiments were carried out to demonstrate the validity of the proposed theoretical models for various source/receiver configurations around the sphere above an acoustically hard ground and an impedance ground. Satisfactory comparative results were obtained between the theoretical predictions and experimental data. It was found that the theoretical predictions derived from the approximate solution agreed well with the results obtained by using the exact solutions.     

Diffraction of electromagnetic waves by a half-plane which is permeable to a stream of cold plasma

Diffraction of plane electromagnetic waves by a conducting half-plane located in an orthogonal stream of cold plasma is studied. It is assumed that the half-plane has almost no mechanical effect on the particles of the medium. (For example, the half-plane can be a model of a metal grid with fairly small cells.) The general solution of the problem has been obtained by the Wiener-Hopf-Fock technique. The scattering field containing waves of two types is studied analytically and numerically. The behavior of these waves away from the half-plane edge is analyzed. It is shown that the electric field at the edge is finite, and the shadow area is absent under certain conditions. Radiophysical Research Institute of the State University of St. Petersburg., Russia. Translated from Izvestiya Vysshikh Uchebnykh Zavedenii, Radiofizika, Vol. 40. No. 4, pp. 399–419, April, 1997.     

Aerodynamic sound generation of flapping wing

The unsteady flow and acoustic characteristics of the flapping wing are numerically investigated for a two-dimensional model of Bombus terrestris bumblebee at hovering and forward flight conditions. The Reynolds number Re, based on the maximum translational velocity of the wing and the chord length, is 8800 and the Mach number M is 0.0485. The computational results show that the flapping wing sound is generated by two different sound generation mechanisms. A primary dipole tone is generated at wing beat frequency by the transverse motion of the wing, while other higher frequency dipole tones are produced via vortex edge scattering during a tangential motion. It is also found that the primary tone is directional because of the torsional angle in wing motion. These features are only distinct for hovering, while in forward flight condition, the wing-vortex interaction becomes more prominent due to the free stream effect. Thereby, the sound pressure level spectrum is more broadband at higher frequencies and the frequency compositions become similar in all directions.     

旋翼叶片回波建模与闪烁现象机理分析

对旋翼叶片回波建模与闪烁现象进行了综合研究.基于散射点散射系数和分布情况,构建了旋翼叶片回波的散射点模型,并分析了散射点分布对回波的影响;在此基础上研究了回波时域闪烁现象的物理散射机理,并结合时频分析和横向分辨率分析了微多普勒特征及时频域闪烁现象;对两类不同分布间隔的散射点模型进行了仿真,并与积分模型进行对比性实验,结果验证了闪烁现象物理分析的合理性.该研究成果在旋翼目标的探测识别领域具有一定的理论与应用价值.     

Frequency-domain method for discrete frequency noise prediction of rotors in arbitrary steady motion

A novel frequency-domain formulation for the prediction of the tonal noise emitted by rotors in arbitrary steady motion is presented. It is derived from Farassat's ‘Formulation 1A’, that is a time-domain boundary integral representation for the solution of the Ffowcs-Williams and Hawkings equation, and represents noise as harmonic response to body kinematics and aerodynamic loads via frequency-response-function matrices. The proposed frequency-domain solver is applicable to rotor configurations for which sound pressure levels of discrete tones are much higher than those of broadband noise. The numerical investigation concerns the analysis of noise produced by an advancing helicopter rotor in blade–vortex interaction conditions, as well as the examination of pressure disturbances radiated by the interaction of a marine propeller with a non-uniform inflow.     

激光脉冲在各向异性散射介质内的瞬态热效应

本文考察了激光脉冲在吸收、发射、各向异性散射介质内引起的瞬态热效应。将激光脉冲辐射在介质内的传递过程分为两个子过程：发射－衰减－反射过程和吸收－散射过程。用光线踪迹法结合节点分析导出辐射传递系数和辐射源项,用控制容积法解瞬态能量方程。检验结果表明,本文的计算方法准确。在此基础上,考察了散射特性、初始温度对激光脉冲响应的影响。     

基于微多普勒效应的旋翼弦长激光探测方法研究

为实现基于微多普勒效应的旋翼目标激光探测与识别,研究了面目标旋翼对激光回波的调制作用.利用物理光学法中面元散射回波叠加原理,构建了矩形面旋翼的微多普勒激光回波模型.通过仿真,利用时频分析方法提取了异于线目标模型的微多普勒特征.机理分析证实该特征反映弦长即旋翼横向尺寸信息,据此提出了相干探测激光回波的矩形旋翼弦长计算方法.不同展弦比旋翼的回波仿真结果与理论公式吻合较好,验证了该方法的有效性.误差分析表明,与进行单一窗长条件下的短时傅里叶变换相比,利用改变窗长的方法分别提取时间、频率信息可有效减小弦长计算误差至1.58%.该模型可实现对旋翼飞行器弦长尺寸的计算,为进一步的旋翼形状探测识别提供了依据.     

TM plane wave scattering and diffraction from a randomly rough half-plane: (part II) An evaluation of the diffraction kernel

In a previous paper (part I), it has been shown that a random wavefield from a randomly rough half-plane for a TM plane wave incidence is written in terms of a Wiener-Hermite expansion with three types of Fourier integrals. This paper studies a concrete representation of the random wavefield by an approximate evaluation of such Fourier integrals, and statistical properties of scattering and diffraction. For a Gaussian roughness spectrum, intensities of the coherent wavefield and the first-order incoherent wavefield are calculated and shown in figures. It is then found that the coherent scattering intensity decreases in the illumination side, but is almost invariant in the shadow side. The incoherent scattering intensity spreads widely in the illumination side, and have ripples at near the grazing angle. Moreover, a major peak at near the antispecular direction, and associated ripples appear in the shadow side. The incoherent scattering intensity increases rapidly at near the random half-plane. These new phenomena for the incoherent scattering are caused by couplings between TM guided waves supported by a slightly random surface and edge diffracted waves excited by a plane wave incidence or by free guided waves on a flat plane without any roughness.     

同位素Tl-201的单光子发射CT影像的康普顿散射校正

给出一种基于康普顿散射理论的Tl-201 SPECT影像的散射校正方法,此方法仅考虑一次散射和二次散射的影响.计算中将散射介质分成散射小元,然后积分求出每一小元内所有电子的散射光子数,一个电子的散射几率由Klein-Nishina公式确定,散射光子被分配至散射小元中心对应的探测器接收孔位置.辐射源的奇点问题也通过这种积分方法解决.误差主要来自于计算中有限的散射元体积和受限制的散射介质,但计算的线源响应函数和散射比与Monte Carlo计算结果相符,计算时间缩短40倍.     

水雾红外隐身的冷/热目标效应

人工水雾对抗红外成像制导导弹时,会因为蒸发对流强、辐射热流弱而使水雾形成冷目标;也可能因为辐射热流过强、散热弱而形成热目标。为详细揭示该现象,以Mie理论为基础,通过辐射传递方程和能量守恒方程的耦合计算,建立了水雾红外隐身产生冷目标或热目标效应的数学模型。应用蒙特卡洛法与本文算法作对比,验证了模型的正确性;将水雾视为吸收、发射、各向异性散射介质,考虑水雾自身辐射、多重散射和各种换热过程,比如辐射热流、两相流的热传导、热对流、紊流热扩散以及雾滴蒸发等,反映了水雾热遮蔽所产生的冷/热目标效应。     

Spectropolarised ray-tracing simulations in densely packed particulate medium

Light scattering from particulate medium is simulated using the Monte Carlo ray-tracing technique. The medium is modelled as a randomly packed medium of ellipsoidal grains with stochastically rough surfaces, with an optional thin coating. Optical properties are modelled using a wavelength-dependent complex refractive index and taking Fresnelian reflections and refractions from the interfaces. The size and shape of the grains are assumed to be large and smooth enough for geometric optics to apply reasonably well.The ray-tracing technique uses parallel, weighted rays for computing simultaneously over a wide wavelength spectrum and a small roughness range, and scaling to obtain a large range of sizes and absorbities simultaneously. Polarisation is fully accounted for. The multiobservation technique is effectively used at each scattering point. The scattering from thinner sample layers is also received as a subresult.Simulations are run for a set of model samples to study the effects and sensitivities regarding the values of certain parameters. It has been found that the size and composition of the grains affect the scattering in a unique and invertible way. The shape of the grain causes similar significant effects that must certainly be taken into account if any accuracy is required, although inverting for the shape is difficult without further constraints. The packing density has a small but observable effect. Polarisation can be used to study the composition of low-albedo objects.     

THE SOUND FIELD OF A ROTOR IN A STATIONARY DUCT

A method is developed for the prediction of noise from rotors in an axisymmetric duct at rest. The technique combines a previously developed model for noise from disc sources with a boundary integral equation method for scattering from the duct surface. Recent developments in the theory of Gaussian quadrature and generalized elliptic integrals are used to simplify the implementation of the formulation. The sound field of a simplified model ducted rotor is then calculated and its structure examined in the framework of known features of the field around rotating sources. It is found that, as for an open rotor, the sonic radius plays an important role in the structure of the field.     

单级高负荷向心透平三维黏性非定常计算

对一台单级高负荷向心透平进行了三维黏性定常和非定常计算,计算得到的动叶出口以及下游的周向平均流场与文献提供的实验结果符合良好。在此基础上对流动的非定常特性进行了分析,发现由于动叶转速较高,且动叶下游不存在下一级静叶的干涉,流动的非定常效应主要体现在叶片排之间的区域以及动叶通道进口,动叶出口以及下游流动的非定常特性并不明显。非定常计算结果透平的级效率随时间的波动幅度达到了1.3%。     

矢量气动声学的理论研究进展及应用

气动声学的声比拟理论以密度、声压等标量为波动算子变量,建立非齐次波动方程,描述流体运动及与边界作用诱发声音的辐射,但标量无法直接描述声能量的传播过程和途径.在流体力学研究中,标量用于描述当前当地的物质状态,而矢量用于描述质量和能量的传输.借鉴上述思想,开展了矢量气动声学的研究,概述矢量气动声学的理论研究进展及应用,主要包括:（1）以声粒子速度为变量,采用声比拟理论的思想直接从Navier-Stokes方程出发推导建立了气动声学的矢量波动方程及两种频域解;（2）综合利用声压和声粒子速度的积分解,直接求解声源周围的瞬时和有功声强矢量场,直观显示声能量的传播途径,应用于旋转声源辐射声能量的传播分析,揭示了亚音速旋转声源辐射声能量的3种传播模式:螺旋模式、声学黑洞模式和R-A模式;（3）采用球谐级数展开方法建立旋转点/紧凑声源辐射噪声的声压和声粒子速度的频域解析解,在此基础上推导了声功率谱的频域解析解,建立了识别旋转叶片声源在空间域和频域分布特征的方法;（4）综合利用矢量气动声学方法和等效源方法,显示声源和散射边界周围声强矢量场的分布特征和能量传播途径,直接揭示了阻抗边界主要的吸声位置以及直接计算得到阻抗边界的吸收声功率.