离心叶轮气动声场的数值计算与分析

采用SIMPLEC算法对Ghost叶轮的三维非定常流场进行了数值模拟。利用计算所得流场结果并结合Lighthill和Lowson声学方程计算了由叶片表面非定常脉动力产生的气动噪声。计算结果表明:气动噪声的峰值主要集中在基频及其谐波附近;与静止的点声源相比,运动的点声源不仅使声场存在明显的多普勒效应,还会使声场的强度产生较大的变化;但对转速恒定的旋转点声源,加速度的变化对声场的影响可以忽略;从声场的分布来看,整个旋转叶轮可以看成是一个按简谐变化的偶极子源,数值计算结果与理论分析的结果吻合良好。     

含尘离心风机中边界层对叶轮侵蚀的影响

本文采用二维可压缩紊流边界层计算模型,计算了离心风机内考虑边界层影响后的粒子轨迹和粒子与叶片表面的碰撞角、碰撞速度、磨损率沿叶片(相对弧长)的变化规律,计算结果表明:对于小直径的粒子,无粘流动假设是不合适的,计及边界层的影响,对于准确预测风机内的粒子轨迹和磨损是必不可少的。     

曲率和旋转对离心叶轮叶片上湍流边界层的影响

本文将曲率和旋转项引入二维湍流边界层动量方程中,导出动量损失厚度的积分关系式。分析了曲率和旋转对湍流结构的直接影响,并提出壁面速度分布律的修正表达式。     

横向喷流对低速大攻角细长旋成体非对称气动特性影响研究

采用风洞试验和数值模拟相结合的方法,对雷诺数Re=55 000条件下细长旋成体有、无横向喷流时大攻角非对称特性进行了分析.通过风洞试验发现了旋成体在法向和侧向进行喷流时其大攻角非对称气动特性与无喷流时的区别,通过数值模拟方法对几个典型工况下旋成体有、无横向喷流时的非对称气动特性进行了分析,揭示了喷流对旋成体非对称流动分离的影响.通过风洞试验发现当细长旋成体进行法向控制时无喷流、喷流位于迎风区和喷流位于背风区的旋成体表现出了不同的非对称流动特性:首先喷流位于迎风区时攻角范围在20°～40°之间有喷流和无喷流旋成体所产生的侧向力方向相反,攻角大于40°之后侧向力系数的方向发生了改变,与无喷流时的侧向力系数方向相同,但是其绝对值要比无喷流时的侧向力系数小.其次喷流位于背风区时攻角在15°～35°之间有喷流时的侧向力系数绝对值要明显比无喷流时大,在随后的40°～70°之间旋成体侧向力系数变化规律与无喷流的趋势相似.当细长旋成体进行侧向控制时由于沿侧向的喷流所产生的直接力使得攻角范围在0°～20°之间和大于45°时有喷流的旋成体侧向力系数绝对值要比无喷流时大,但是攻角在25°～40°之间时旋成体...     

串列叶片式前向离心风机气动与噪声特性的优化研究

对采用串列叶片的某前向离心风机内部三维非定常流动进行了数值计算,重点研究了串列叶片不同叶片相对长度和不同叶片相对周向位置两个参数对风机气动性能及气动噪声的影响.通过响应面方法对数值结果进行二次回归拟合,得到两个参数与风机效率和A声级间的函数关系,并进行了优化分析.数值结果表明:两个参数对串列叶片式前向离心风机效率和A声级均有较大影响,合理的串列叶片设计能够在保持气动性能基本不变的情况下降低风机的气动噪声.将可靠的CFD数值技术与响应面方法结合起来用于指导离心风机的改进及试验设计是可行的,本文的研究结果可为串列式离心风机在节能与降噪的总体设计方面提供参考.     

圆角化对方柱气动性能影响的流场机理

方形截面柱体的圆角化处理是常用的流动控制方法,但其流场作用机理尚未被澄清.采用大涡模拟方法,在雷诺数为2.2$\times$10$^{4}$时,考虑风攻角的影响,对均匀流作用下的标准方柱和圆角方柱的气动性能和流场特性进行了研究,定量分析了圆角化气动措施和风攻角变化对分离泡特性的影响规律,从流场角度澄清了圆角化气动措施对方柱气动性能的影响机理.研究表明:与标准方柱相比,圆角方柱的表面风压、气动力和涡脱强度呈整体下降的趋势,但圆角方柱的斯特劳哈尔数更高;圆角方柱的"分离泡流态'发生在更小的风攻角范围内,分离泡的出现会进一步造成方柱的尾流变窄,涡脱强度减弱;随着风攻角的增大,分离泡的长度会逐渐减小直至消失,分离泡的中心会逐渐向方柱前角(迎风向)和方柱壁面移动;与标准方柱相比,圆角方柱的气流发生初次分离的位置向下游移动,分离后的剪切层更贴近方柱,因而更易发生再附现象;方柱尾流宽度的减小和涡脱强度的减弱是导致圆角方柱气动力减小和斯特劳哈尔数增大的主要原因.      

基于空气-雪两相流动力学仿真的滑雪板界面特性及其减阻性能研究

在冬奥会的比赛中滑雪板是重要的比赛装备,滑雪板与雪的界面特性极大地影响了滑雪板的性能.滑雪板与雪的界面同时存在雪、空气与滑雪板三者的耦合作用且作用时间短,因此常规的试验研究难度很大.计算流体动力学(CFD)仿真是研究流体界面性能的重要手段,可以模拟真实滑雪条件下,滑雪板滑行时的界面状态,量化分析界面的作用力等物理量.本文中以单板滑雪板作为研究对象,单板滑雪板在滑动界面上涉及到空气与雪两相流体问题.因此,本研究中采用CFD仿真的方法对坡面障碍单板进行分析研究.结合滑雪板的运动位姿状态,将结构分为4个变量参数进行分析,结果显示侧刃弦长对界面作用力影响最大,并探究结构最优组合;攻角则分为5个不同参数进行分析,结果显示雪板抬起角度为5°左右时,可以起到降低滑动界面作用力的效果.滑雪板结构与攻角的优化,可为后续的滑雪板设计与运动员运动过程中滑雪板姿态起到指导作用.     

进口导叶／叶轮／扩压器非定常相干的数值与实验研究

在不同进口导叶预旋角度下,采用非定常的方法对进口导叶/叶轮/扩压器三部件之间非定常相干进行了数值与实验研究,探讨了三部件之间动静相干的机理.结果表明,在进口导叶/叶轮/扩压器三部件相干时,最大的脉动压力出现在叶轮和扩压器之间的动静交界面上.当进口导叶预旋角度存在时,叶轮与扩压器之间无叶区内的非定常流动以叶轮叶片通过频率和1/2叶片通过频率为基频;而当扩压器进口安装角增大时,径向间隙内的流动则主要以1/2叶片通过频率为基频.在不同的配置下,湍流强度和非定常度均有朝向轮盘增加的趋势.在进口导叶正预旋60°同扩压器进口安装角为17°时的配置有增大湍流强度和非定常度的趋势.     

阻旋栅对梳齿密封动静特性影响研究

阻旋栅可改变密封进口流体周向流动与进口预旋,是提高系统稳定性的主要方法之一.本文作者应用计算流体力学方法研究了阻旋栅几何参数对梳齿密封动静特性的影响,计算分析了阻旋栅在不同长度、间隙、周向个数及不同进口预旋比下密封流场分布与动力特性系数,并与无阻旋栅梳齿密封进行对比.研究表明:阻旋栅能够有效抑制密封进口周向流动、降低密封腔室周向压力;随着阻旋栅周向个数与阻旋栅间隙的减小,其抑制效果增强,阻旋栅长度的增加对周向速度影响则越来越小;提高预旋比将使密封内流体周向速度增加.与传统梳齿密封相比,具有阻旋栅的梳齿密封直接阻尼增加,交叉刚度降低,进而有效阻尼提高.阻旋栅间隙s=0.20 mm、长度l=3.25 mm、数量n=90时密封有效阻尼较大,系统稳定性最好.     

叶片型线对离心油泵性能的影响

以65Y60型离心油泵为研究对象，研究了液体不同粘度下叶片型线对泵性能的影响。首先，利用本课题组独立开发的准三元叶片设计程序以反问题方式设计了两种型线。这两种型线叶片前半部分与原一元叶轮叶片的型线不同、后半部分与一元叶轮相同。然后在不同粘度下将三个叶轮进行性能对比实验。研究表明，叶片进口附近的型线的改变对泵性能有较大影响；适当增大叶轮后盖板流面上的叶片流体动力负荷有助于提高离心油泵输送粘油时的水力性能。     

Study of the aerodynamic characteristics of cone-sphere models in a hypersonic flow

The aerodynamic characteristics of cone-sphere models are studied at Mach numbers M = 6, 8.4, and 12 to 13 over a wide Reynolds number range. Models of a braking device (sphere) were connected with a load (frustum of a cone) by means of shrouds. The dependences of the aerodynamic coefficients C _x and C _y on the angle of attack α were obtained for different relative dimensions of the load and the braking device, shroud lengths, and Mach and Reynolds numbers. The effect of the above-mentioned parameters on the aerodynamic characteristics of the models is analyzed. The C _x (Re_D) dependences of load-parachutemodels in a symmetric flow are determined over the wide Mach and Reynolds number ranges 6 ≤ M ≤ 13 and 3 · 10³ ≤ Re_D ≤ 3 · 10⁶.     

Effect of one-sided unsteady energy supply on aerodynamic characteristics of airfoils in a transonic flow

The possibility of controlling the aerodynamic characteristics of airfoils in transonic flight regimes by means of one-sided pulsed-periodic energy supply is studied. Based on the numerical solution of two-dimensional unsteady gas-dynamic equations, the change in the flow structure in the vicinity of a symmetric airfoil at different angles of attack and the aerodynamic characteristics of the airfoil as functions of the amount of energy supplied asymmetrically (with respect to the airfoil) are determined. The results obtained are compared with the data calculated for the flow past the airfoil at different angles of attack without energy supply. It is found that a given lift force can be obtained with the use of energy supply at a much better lift-to-drag ratio of the airfoil, as compared to the case of the flow past the airfoil at an angle of attack. The moment characteristics of the airfoil are found. __________ Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 49, No. 6, pp. 82–87, November–December, 2008.     

基于涡尾迹方法的风力机气动性能分析

基于(势流)涡尾迹方法开发了水平轴风力机叶片气动性能分析程序,采用固定尾迹涡模型和自由尾迹模型分别对气动设计性能进行计算分析,得到风力机设计工况下的涡位置、诱导因子、功率系数及扭矩系数等气动性能参数,并与设计结果对比。结果表明,涡尾迹方法能够快速准确地计算风力机叶片气动性能参数,对风力机叶片气动分析,固定尾迹涡模型较自由尾迹模型计算时间短,具有较好的实用性。     

相对弯度对低雷诺数流动中翼型动态气动力特性的影响

以固定翼微型飞行器为研究背景,研究了相对弯度对低雷诺数流动中翼型动态气动力特性的影响规律。采用Roe迎风差分格式和双时间步迭代方法,数值求解拟压缩性修正不可压Navier-Stokes方程组,给出了数值算法与实验数据的对比验证。以翼型弦长为特征长度,在Re=500~50000情况下,选取不同最大相对弯度和不同最大相对弯度位置的翼型,计算了其等速上仰时的动态气动力,结果表明后者对气动力的影响比较显著,把最大弯度位置布置在翼型弦向40%的地方要比布置在30%和50%两处所获得的动态升阻比大。     

Study of the aerodynamic stability of a blunt cone with a side flap in a hypersonic flow

The stationary and time-dependent aerodynamic coefficients of a slender blunt cone with a flap located near the base section of the model are experimentally investigated. The freestream parameters (M_∞ = 6, Re _L = 0.88 × 10⁷, and γ = 1.4) ensured a turbulent regime of flow over the conical surface and the flap. At high angles of attack (α ～ 10°) laminar-turbulent transition is observable in the separation zone on the leeward side of the body. Emphasis is placed on the determination of the trimming angles of attack for different positions of the center of rotation and the static and dynamic stability coefficients (the model oscillation damping coefficient).     

An aerodynamic ROM of the blade subjected to wake based on Fourier method for flow

A reduced-order model (ROM) is presented based on Fourier method for flow to predict aerodynamic forces of blades subjected to periodic time-varying upstream wakes. In the method, a time-varying wake is decomposed into harmonic waves by fast Fourier transformation. Using the Fourier method for flow and neglecting the cross-coupling between harmonics, the aerodynamic forces caused by the wake are represented by a linear combination of harmonics with the same frequencies as the wake. The coefficients of the aerodynamic force harmonics are interpolated at the per-fitted curves of the normalized Fourier coefficients (coefficients of aerodynamic forces harmonics corresponding to a unit simple harmonic excitation)–frequency relationship. A blade example is used to show the ability of the proposed method. The results indicate that the ROM method can predict the aerodynamic forces of blades caused by wakes efficiently and accurately. The amplitude levels of wakes have a linear impact on the accuracy of the ROM. Neglecting the higher-order cross-coupling between the harmonics in the ROM method is acceptable.     

Study of the Effect of the Depth of the Cavity of a Braking Device on the Aerodynamic Drag of a Model in Transonic and Supersonic Flow

The flowfield and the aerodynamic drag of a model consisting of a pair of bodies (leading body a cylinder and trailing body a hollow cylinder) connected by a cylindrical bar along the axis of symmetry is experimentally investigated at Mach numbers ranging from 0.6 to 1.7. In the course of the experiments, the trailing body cavity depth and the connecting bar length were varied.__________Translated from Izvestiya Rossiiskoi Academii Nauk, Mekhanika Zhidkosti i Gaza, No. 2, 2005, pp. 186–192.Original Russian Text Copyright © 2005 by Pilyugin and Khlebnikov.     

Effect of inlet volute wrap angle on the flow field and performance of double inlet gas cyclones

In response to the divergent understanding of double inlet cyclone performance in the literature, the effect of inlet volute wrap angle on the performance and flow field of double inlet cyclone separator was studied by Computational Fluid Dynamic (CFD) method. The results showed that the inlet volute wrap angle can affect the comparison results of the single and double inlet gas cyclones with the same total inlet cross-sectional area and velocity. 0° and 90° volute double inlet improved the efficiency mainly by separating particles below 10 μm, while 180° volute double inlet had no separation advantage for any particles, so the symmetrical double inlet does not always improve the efficiency, and the appropriate inlet volute wrap angle should be selected according to the actual situation, otherwise, the expected performance requirements of the symmetrical double inlet cyclone cannot be achieved. Compared with the flow field, it is found that the inlet volute wrap angle changed the tangential velocity of the symmetrical double inlet cyclone separator, thus changing the performance.     

LES study on the influence of the diffuser inlet angle of a centrifugal pump on pressure fluctuations

Large-Eddy Simulations are conducted on a centrifugal pump at design and reduced flow-rates for three diffuser geometries, to investigate the effect of changing the diffuser inlet angle on the overall performance and the pressure fields. In particular, pressure fluctuations are investigated, which affect the unsteady loads acting on the pump, as well as vibrations, noise and cavitation phenomena. The considered modification of the diffuser geometry is targeted at decreasing the incidence angle at the off-design flow-rate by rotating the stationary blades of the pump around their leading edge. Results are compared against those of an earlier study, where the same modification of the diffuser inlet angle was achieved by increasing also the radial gap between impeller and diffuser, whose blades were rotated relative to their mid camber location. The comparisons across cases demonstrate that the radial gap between the trailing edge of the impeller blades and the leading edge of the diffuser blades has a more profound influence on pressure fluctuations, compared to the angle of incidence on the diffuser blades of the flow coming from the impeller.     

叶片与蜗舌相对位置对离心泵性能数值模拟精度影响的研究

本文选择RANS方程和RNG k-ε湍流模型,采用有限体积法,在假定流动定常的前提下对离心泵中叶片与蜗舌不同相对位置时的流场进行数值模拟,总结分析了各性能参数的计算误差在不同的相对位置时的变化规律.通过叶片与蜗舌不同相对位置时对各性能参数计算误差的均方差进行比较,认为存在一个合适的相对位置使得对各性能参数的总体预测精度保持最高,为数值方法分析离心泵的性能提供了指导.