非定常激励抑制轴流叶栅分离的数值分析

本文对大转角压气机叶栅大攻角工况在来流尾迹非定常激励作用下的时空结构进行了数值分析.合理的非定常激励明显提升了叶栅的时均性能,与激励频率对应的涡结构得到强化,其它频率的杂涡被卷吸,无序的吸力面分离流结构变得有序.文中分析了周期性来流尾迹控制分离结构的作用机理,波涡共振促进涡的卷起和配对;湍动能强化动量交换.基于此,比较了两种来流尾迹模式下分离结构对来流周期性的响应问题.另外,针对管道风扇引起的远场噪声,在来流尾迹非定常激励作用下对其降低的可能性进行了设想.     

贯流风扇偏心涡非定常特性研究

本文应用大涡模拟计算并描述了贯流风扇内部旋涡流动的非定常变化细节.研究结果表明,贯流风扇叶片绕流流态复杂,吸力面存在分离流动,叶片出口形成明显的尾迹区.在蜗舌一侧存在偏心涡,由核心区域和外围区域组成.其中偏心涡的核心区域由两至二三个叶道内气流在内径处分离产生的旋涡团组成,在流动过程中涡量由上游的脱落涡得到补充.偏心涡的外围区域由蜗舌附近回流的旋涡团组成,引起蜗舌表而压力脉动,产生干涉噪声.干涉噪声频谱在低频带上具有较大声压级,最大声压级处的频率和叶轮出口侧叶道的脱落涡频率相关.     

有大分离的压气机高压级静叶分离涡模拟研究

将分离涡模拟方法应用于高雷诺数压气机静叶有大分离的复杂流动计算中,研究该方法对分离的模拟能力.采用约280万网格,SA计算仅能得到定常结果.DES计算在叶片中部小分离区域,所得到的非定常波动较弱,尾迹掺混略慢于SA,结果整体上与SA类似.在叶片端壁附近有大分离的区域,DES结果捕捉到了明显的非定常现象与压力波动,计算表明吸力面涡脱落会加强掺混,而端壁分离则会加强尾迹.另外,DES计算比SA更详细地描述了涡结构.这表明DES有比SA更好的模拟大分离的能力.计算结果也加深了对静叶角涡与尾迹发展的认识.     

基于大涡模拟下风力机翼型非定常转捩流动的动态模态分解分析

翼型绕翼流动对风力机整机性能产生重要影响.本文基于大涡模拟方法,得到风力机翼型非定常转捩流动.通过对压力流场的动态模态分解(DMD)分析,发现翼型层流分离泡的生成和发展为流动主要非定常特征,且该特征具有主要频率.预估得到高增长率T-S扰动波频率与DMD模态频率接近,发现高频变化的分离泡由边界层分离点下游不远处的T-S扰动波诱导K-H不稳定性而主导,以及中低频的DMD模态表现为T-S扰动波所引起的湍流结构.对比不同攻角下的DMD分解结果,发现上表面分离泡会逐渐向前移动,长度变短;而下表面分离泡略微后移,长度变化不大.     

DES模型在压气机亚音转子中的应用探讨

本文运用分离涡模拟(DES)方法研究了不同工况下压气机亚音转子的流动情况,分析了其时均与瞬时流场中顶部间隙泄漏流动和根部角区的流动分离.通过与S-A模型计算结果的对比表明,DES模型在模拟顶部泄漏流动及二次泄漏、泄漏流在转子下游与尾迹的干涉时能够捕捉到更强的旋涡结构,在模拟转子根部角区的分离时也能获得更为丰富的流动现象.对不同工况的DES计算表明负荷的上升会使泄漏涡形成的位置向上游移动,从而导致并加剧二次流动,并对叶栅下游泄漏涡与尾迹的干涉产生影响.对设计工况下瞬时流场的分析表明,泄漏涡在叶栅下游体现出周期性的强弱变化,近叶根分离区也体现出明显的非定常性.     

采用FFT-POD的非定常流动控制频谱和能谱特性研究

对数值模拟的不同频率下非定常激励的扩压通道流场采用POD方法分析,对取得的各级模态系数进行频谱分析,对不同变量的能谱进行对比分析,研究非定常激励对流场的控制机理。分析表明:非定常信号能够强制与流场发生共振作用,低阶模态共振作用较强,随之会出现衰减现象;同时流场的"固有频率"不会被改变,只会暂时抑制或加强,流场中的"保护"机制同样如此;动能谱显示非定常激励使流场中代表大涡的2、3阶动能份额增大,同时也增大了流场的第一阶模态拟涡能份额,从而使流场小尺度脉动能量和平直流动能减少。     

动叶尾迹对跨声速压气机静叶非定常分离结构的影响研究

采用数值模拟的方法研究了动叶尾迹对跨声速压气机设计工况下静叶表面和下端壁分离结构的非定常影响规律。首先,采用Rotor37的实验结果验证了数值模拟方法的可靠性。通过对跨声速压气机设计工况的计算,认为定常计算和非定常计算的结果整体上是相似的,非定常计算考虑了动叶尾迹对静叶流场的影响。研究表明,动叶尾迹在向下游输运过程中经历了拉伸、扭曲、积聚和耗散的过程。动叶尾迹使动静叶交界面气流角发生周期性波动。动叶尾迹的扫掠,使静叶前缘闭式分离区域范围发生先增大后减小的周期性波动,使静叶尾缘分离形式呈现由闭式分离向开式分离的周期性转化。动叶尾迹的扫掠在马蹄涡吸力面分支前诱导出一个小尺度的旋涡,并使得静叶根部尾缘和下端壁角区处的螺旋点拓扑结构呈周期性变化。动叶尾迹的扫掠使得静叶压力面的局部高静压区发生周期性的迁移。     

混流式核主泵内流动结构与压力脉动特性关联分析

核主泵内的流动不稳定将会引起严重振动,不利于其安全稳定运行。因此本文基于大涡模拟(LES)数值计算方法对几个典型工况下核主泵内部非稳态流动结构及其压力脉动特性进行全面阐述与关联性分析。研究表明,随着流量的增加,动静干涉作用在导叶出口处逐渐增加;偏工况条件下,导叶出口处压力脉动频谱低频段中均出现复杂激励频率,尤其是靠近出液管附近的导叶出口处。核主泵在偏大流量工况下运行时壳体右侧内部非稳态流动结构相较于壳体左侧更加复杂;在偏小流量工况下运行时壳体底部压力脉动更加剧烈。本文进一步详细描述了核主泵球形壳体内强涡量区的流动结构及其成因,并且发现测点处的压力频谱与涡量频谱有相同的主要激励频率,因此证明核主泵内非定常旋涡流动结构是激励压力脉动的主因之一。     

平板前缘分离抑制的周期性激励研究

本文采用大涡模拟对平板前缘分离在周期性来流激励作用下的流动结构进行了数值研究。将计算得到的结果与实验数据进行了对比。在此基础上,对涡量等值面和Q准则可视化手段进行了比较。通过研究不同外部周期性激励频率抑制分离的效果,讨论了有效外部扰动频率与分离区域特征频率的关系。结果显示,外部频率为f_(shear)、f_(shed)、1/2f_(shear_时分离抑制明显,其中1/2f_(shear)效果最佳。当分离区域显著减小时,流动具有明显的周期性;当在外部扰动作用下的分离抑制效果很弱时,外部扰动无法直接在分离区域中促成对应尺度的涡生成。     

离心泵非设计工况内部流动特性研究

以单级蜗壳式离心泵为研究对象,基于RANS进行了全流场的非定常数值计算,探讨了叶轮的非定常流动特征,重点分析了叶轮出口沿轴向变化的圆周面流域内各节点的压力分布特性。结果表明:在叶片压力面及叶片后缘尾迹区发生了剧烈的湍流脉动现象;不同工况下叶轮出口圆周方向的压力系数C_p均在隔舌附近产生极值;额定工况Q/Q_N=1时,叶轮出口圆周方向的压力系数C_p呈稳定周期性分布,随着工况的改变,压力系数C_p沿蜗壳周向分布不均匀性增加;小流量工况下叶轮流域内发生了明显的流动分离现象,流道内产生了较大尺度的分离涡,破坏了叶轮出口圆周方向压力系数C_p的周期性分布特性;叶轮出口圆周压力系数C_p沿中截面两侧的流域内几乎对称分布;在Q/Q_N=0.2小流量工况下,压力脉动频谱图低频段内出现了较多复杂的激励信号,认为这与流域内的分离涡结构具有一定关联。     

Flow structure of the entrance of a T-junction duct without/with a circular cylinder

The flow characteristics of the trailing edge of vertical vanes installed at the intersection of a T-junction duct were experimentally investigated using particle image velocimetry. The measured velocity field in the branch duct with/without single circular cylinder was studied under different cross velocities and velocity ratios. Additionally, the effect of the locations of cylinder on the flow field was discussed. The positive velocity region, the unsteady flow region and the trailing edge flow region of the vane, have been observed. The positive velocity region existed in almost one half of the measured area. As for the unsteady flow region, the unstable double-vortex structure transformed into a single-vortex structure as the velocity ratio increased. As for the trailing edge flow region of the vanes, the vortex streets could be visualised. Furthermore, the location of cylinder has revealed significant influence on the flow distributions in the trailing edge flow regions of the vanes. The flow structure without cylinder in the measured area is dependent on combinations of the cross velocity and velocity ratio, whereas that with cylinder is dependent on the velocity ratio. The vorticity fields were analysed in each region, and the velocity components revealed the cause of airflow trajectory.     

Prediction of aerodynamic sound from circular rods via spanwise statistical modelling

The Ffowcs Williams and Hawkings’ acoustic analogy is combined in the time domain with a statistical model in order to take into account the three-dimensional character of the vortex shedding process from a rod in a uniform stream. By applying the model to a two-dimensional unsteady Reynolds averaged Navier-Stokes flow computation, it is shown that the three-dimensional effects, like spectral broadening around the shedding frequency, are partially recovered. The ad hoc statistical model relates a spanwise random distribution of the vortex shedding phase and wall pressure modulations to an arbitrary spanwise correlations. The phase distribution is applied to the tonal pressure signals of the computation and the resulting ad hoc signals are fed into the acoustic analogy. The study is carried out for a rod based Reynolds number of 2.2×10⁴ for which the rod wake is turbulent. Numerical results compare favourably to those of an accompanying experiment.     

Flow visualization of vortex structure in a pulsed rectangular jet

Pulsating jet is visualized using hydrogen bubble method to clarify the vortex nature in the near field of the jet. This study focused on the development in space and time of vortex structures evolution in low aspect-ratio rectangular jet with pulsation. Pulsation means large-amplitude, low-frequency excitation which is expected to increase the mixing and spreading of the jet and to accelerate its transition from a rectangular form to an axisymmetric form. It was deemed appropriate to investigate whether jet characteristics of a pulsating, submerged jet flow can be altered by including pulsations. The difference of the vortex deformation process is discussed in relation to pulsating conditions. Consequently, the pulsation leads to the formation of vortices at regular intervals, which are larger than those occurring in a steady jet. The results show that the streamwise interaction, between leading vortex and trailing vortex rolled up at nozzle lips, strengthens with increasing pulsating frequency. The spanwise drift of the vortex becomes strongly apparent at large amplitude and high frequency conditions. The drifting start position does not change regardless of pulsating condition. The convection velocity of vortex increases at lower frequency and larger amplitude.     

Visualization of three-dimensional flow structures in the wake of an inclined circular cylinder

In the previous measurements of the aerodynamic sound generated from an inclined circular cylinder, it is reported that the sound pressure level (SPL) changes with the aspect ratio and the inclined angle. Therefore, we have investigated the changes in the vortex structure of the wake considered as one of the causes of the SPL variation. Using the low-noise wind tunnel, the velocity fluctuation in the wake is measured to obtain the correlation length. Moreover, the flow visualization is performed with a hydrogen bubble method and a numerical analysis method in order to clarify how the wake structure changes by variations of aspect ratio and inclined angle. As a result of this investigation, it is shown that the spanwise structure of Karman’s vortex is highly influenced by the interference of Karman’s vortex with the bottom endplate, and that the influence on the spanwise structure in the wake becomes greater as the aspect ratio decreases and the inclined angle increases.     

The influence of the wake on the stability of cantilevered flexible plates in axial flow

Cantilevered flexible plates in axial flow lose stability through flutter. Using the inextensibility condition for the cantilevered nonlinear plate equation of motion and the unsteady lumped-vortex model to calculate the fluid loads, a flutter boundary has been obtained. In the time-domain analysis performed to this end, the wake behind the oscillating cantilevered plate is assumed to issue tangentially from the free trailing edge and extend downstream with an undulating form. The influence of the wake on system stability may be characterized in terms of the non-dimensional mass ratio, reduced flow velocity and flutter frequency. For large values of the mass ratio, the plate vibrates with high frequency and high-order mode content. It is shown that the wake has less influence on system stability for long plates than it does for short ones.     

有厚度平板尾缘可压缩剪切层中的涡结构数值模拟

采用一个新型Fu Ma高精度UCD5 SCD6紧致差分算法,通过直接求解二维Navier Stokes方程,成功实现了有厚度平板尾缘可压缩剪切层中涡结构的数值模拟,并考查了平板厚度对其的影响.计算对流马赫数M_c=0.3,平板厚度分别为1,2,3,4个参考长度.结果表明,增加平板厚度可促使平板尾缘可压缩剪切层中的涡提前卷起,有利于两股气流混合.     

Wavelet multi-resolution analysis of initial condition effects on near-wake turbulent structures

The effects of initial conditions on turbulence structures of various scales in a near wake have been investigated for two wake generators with the same characteristic dimension, i.e., a circular cylinder and a screen of 50% solidity, based on the wavelet multi-resolution analysis. The experimental investigation used two orthogonal arrays of sixteen X-wires, eight in the (x, y)-plane, and eight in the (x, z)-plane. Measurements were made atx/h (x is the streamwise distance downstream of the cylinder andh is the height of the wake generator) = 20. The wavelet multi-resolution technique was applied to decomposing the velocity data, obtained in the wakes generated by the two generators, into a number of wavelet components based on the central frequencies. The instantaneous sectional streamlines and vorticity field were thus ‘visualized’ for each wavelet component or central frequency. It was found that the behavior of large- and intermediate-scale structures depend on the initial conditions and the small-scale structures are independent of the initial conditions. The contributions from the wavelet components to the time-averaged Reynolds stresses and vorticity were estimated. Both the large-scale and intermediate longitudinal structures make the most significant contributions to Reynolds stresses in the circular cylinder wake, but the contribution from the large-scale structures appears dominating in the screen wake. The relatively small scale structures of the circular cylinder wake contribute most to the total rms spanwise vorticity.     

柔性旋涡发生器对翼型前缘分离的自适应控制

采用边长为10 mm的三角形柔性和刚性旋涡发生器，安装在二维NACA0018翼型上翼面前缘不同弦长处，用于控制翼型前缘分离流动.实验在低速直流式风洞中进行，以翼型弦长为特征长度的Reynolds数Re=1.1×105，采用单丝热线风速仪测量尾流速度剖面.分别研究柔性和刚性两种材料的三角形旋涡发生器对翼型前缘分离的控制效果.实验结果表明，与刚性旋涡发生器相比，柔性旋涡发生器利用来流能量实现自适应控制，使剪切层下移，从而明显抑制前缘分离.      

光学炮塔气动载荷的非稳态特性

采用耦合J-B模型的IDDES模型与双时间步LU-SGS方法开展炮塔非稳态气动载荷的数值仿真研究。炮塔流动会发生分离,天顶位置的分离角大于90°;当流动绕过炮塔时,形成马蹄涡、脱落涡街等非稳态流场结构,导致气动载荷也具有非稳态特性;炮塔顶点的脉动静压功率谱在1.6~40.0 kHz进入各向同性均匀湍流的惯性子区,基本满足Kolmogrov的-5/3定律;气动力以阻力为主,横向力的脉动幅值大,气动力矩则以俯仰力矩为主,滚转力矩的脉动幅值大,偏航力矩可以忽略不计;气动力和力矩的功率谱主要集中在1 kHz以下,存在多个尖峰频率,主频约为230 Hz (斯特劳哈尔数为0.15)。在ATP系统设计之初,需要考虑光学炮塔所受气动载荷的非稳态特性,并规避尖峰频率尤其是主频的谐振破坏问题。