自由面对潜艇尾流场流动特性影响研究

潜艇周围绕流场流动特性会影响潜艇的机动性能, 特别是近水面航行时, 自由面的存在会增大潜艇尾流场的复杂程度.为探究潜艇在近水面航行时自由液面对潜艇尾流场流动特性的影响机理,借助大型水下三维粒子图像测速技术开展潜艇尾流场流动特性研究.首先通过美国泰勒水池标准模型实验结果对试验方法准确性进行验证; 随后,用验证后的模型试验方法对潜艇尾流场进行测量,得到不同潜深工况、不同速度下的桨盘面轴向速度以及脉动速度,同时辅以数值模拟对试验无法测得的兴波波系及中纵剖面速度场加以补充,从兴波角度阐述了自由面对潜艇尾流场流动特性影响机理. 研究结果表明:潜艇在近水面航行时, 随着Fr增大,桨盘面处轴向速度云图中上方等值线整体趋于扁平化, 较4D潜深工况,1.5D潜深工况出现局部脉动速度极大值, 且脉动速度结构整体下移; 自由面存在时,艇体与自由面间流场速度明显增大, 特别在桨盘面区域, 流场速度明显提升.随着Fr增大, 桨盘面处的自由液面高度逐渐降低,这就导致了桨盘面位置出现更大的流体速度, 即造成了桨盘面伴流场挤压现象.      

自由面对潜艇尾流场流动特性影响研究

潜艇周围绕流场流动特性会影响潜艇的机动性能,特别是近水面航行时,自由面的存在会增大潜艇尾流场的复杂程度.为探究潜艇在近水面航行时自由液面对潜艇尾流场流动特性的影响机理,借助大型水下三维粒子图像测速技术开展潜艇尾流场流动特性研究.首先通过美国泰勒水池标准模型实验结果对试验方法准确性进行验证;随后,用验证后的模型试验方法对潜艇尾流场进行测量,得到不同潜深工况、不同速度下的桨盘面轴向速度以及脉动速度,同时辅以数值模拟对试验无法测得的兴波波系及中纵剖面速度场加以补充,从兴波角度阐述了自由面对潜艇尾流场流动特性影响机理.研究结果表明:潜艇在近水面航行时,随着Fr增大,桨盘面处轴向速度云图中上方等值线整体趋于扁平化,较4D潜深工况, 1.5D潜深工况出现局部脉动速度极大值,且脉动速度结构整体下移;自由面存在时,艇体与自由面间流场速度明显增大,特别在桨盘面区域,流场速度明显提升.随着Fr增大,桨盘面处的自由液面高度逐渐降低,这就导致了桨盘面位置出现更大的流体速度,即造成了桨盘面伴流场挤压现象.     

金属往复滑动摩擦噪声源的识别

对金属往复滑动摩擦噪声进行了声学和动力学测量 ,通过对声压级和加速度进行时间历程波形分析、功率谱分析 ,确认摩擦噪声是由参加相对滑动的摩擦副的 1个或 2个部件的振动辐射所产生 ,摩擦噪声的声源体为参加摩擦运动的振动部件     

涡轮增压器离心压气机非稳态工况流场分析

利用商用 CFD 软件对一小型车用离心压气机建立了数值模型,并将模拟结果与实验结果进行了对比:稳态的设计转速最高压比相差不超过 0.5%,最高效率相差不超过1.5%;非稳态模拟和实验得到的失速频率均为 3000Hz,模拟结果真实可信.主要利用设计转速下小流量工况时的非稳态数值模拟结果对喘振发生前离心压气机各部件的非稳态流动特点进行了详尽阐述.研究结果表明:小流量工况时离心压气机各部件均出现非稳态流动现象,这种非稳态效应在各部件中表现出不同的特点,且随着流量的减小这种非稳态效应会不断加剧.     

基于结构化网格的导管螺旋桨敞水性能计算和艇桨干扰分析

本文采用结构化网格建模求解RANS方程,建立了导管桨和艇桨组合体的水动力性能数值计算方法.计算中以JD75简易导管与Ka4-70螺旋桨组合的导管螺旋桨及其与SUBOFF艇体模型的组合体为研究对象,利用RNG k-ε湍流模型封闭RANS方程得到控制方程.通过滑移网格方法计算了导管桨敞水性能,然后将该桨置于全附体SUBOFF潜艇模型后,计算螺旋桨与主艇体间的干扰特性,文中对流场等结果进行了分析比较.     

潮流能发电平台的水动力特性及动力响应分析

运用水动力学软件AQWA对潮流能发电平台进行了频域分析,得到不同重心高度、不同水深、遭遇不同浪向角条件下平台各自由度幅值响应算子随波浪圆频率的变化曲线。再对平台进行了风浪流联合作用下的时域耦合分析,研究不同系泊角度对平台运动响应和系泊缆张力的影响。计算结果表明:纵荡幅值响应算子峰值随浪向角的增大而逐渐减小,横荡幅值响应算子峰值随浪向角的增大而增大,纵荡、横荡上主要表现为与波浪的低频共振,浪向角较小会产生较大的垂荡运动、纵荡运动、纵摇运动,浪向角较大会导致较大的横摇运动;水深小于10m时,海底对波浪的反射作用对平台纵荡和艏摇运动影响比较明显;小范围内的重心高度变化对平台各自由度幅值响应算子影响较小。当系泊角度为45°时,系泊系统对平台运动响应的控制更好,且此时系泊系统的安全系数最大,主要系泊缆受力更加合理,平台更安全。     

小型高速离心压气机级内部的三维流场分析

利用三维数值模拟技术对微型燃气轮机中的离心压气机部分进行了数值分析,得到了离心压气机设计转速下的级特性曲线和各通流部件中的流动情况。数值分析表明:设计转速下压气机的级特性非常陡峭;整个特性线范围内离心叶轮基本在亚音速情况下工作,而径向扩压器是在跨音速条件下工作,离心压气机整机的最大流量是由径向扩压器的喉部面积决定的;离心压气机级内部各通流部件之间流动的相互干扰是引起流动分离的重要原因,各通流部件之间流动的相互匹配和协调将决定了离心压气机整机的性能和稳定性。     

湍流边界层流场与噪声实验研究

在重力式水洞中进行了水翼及半翼湍流边界层流场与噪声的实验研究。测量了水翼及半翼边界层附近的湍流脉动速度场;测量了半翼翼型表面三点处的压力脉动及其辐射噪声,测量了水翼内部测点的噪声及外部辐射噪声,在不同流速、不同攻角、光滑和粗糙翼面的情况下都进行了测量分析。试验结果发现,上述因素对模型的边界层湍流速度场有显著影响,15度攻角时,翼面附近湍流强度要比0度时大得多,粗糙翼面附近的湍流强度比光滑的大,而湍流强度随来流速度的变化不大,u(来流）方向和v方向的湍流强度量级相当;一般地,翼面压力脉动、翼内部噪声及外部噪声都是随来流速度的增大而增大,随攻角的增大而增大,粗糙翼面时的结果要比光滑翼面的大。从压力脉动与噪声测量结果与相应的流场测量结果比较可知,可以从湍流区域的湍流强度来判断出声源强度的定性变化。     

不同路面激励下车内噪声预测与板件声学贡献量分析

利用有限元模拟计算的方法对不同路面激励下车内噪声进行了预测, 并分析了板件对声 学的贡献量. 使用MATLAB软件生成了B级和C级路面谱. 由NASTRAN软件计算 出车身结构在不同路面谱激励下1$\sim$200\,Hz的频率响应结果, 在LMS Virtual. Lab声学软件中, 根据声传递向量技术预测驾驶员和乘客耳旁声压级响应. 还探讨了 声腔结构表面阻抗特性对车内噪声的影响. 并针对C级路面谱激励, 通过车身各板件对 驾驶员右耳声压的面板贡献量分析, 找出了结构优化的重点区域, 为降低车内声压检测点噪 声进行相关的声学处理提供参考依据.     

不稳定波辐射噪声

本文通过系统的实验证明在低马赫数时射流中的不稳定波对于噪声辐射具有重要的贡献。不稳定波辐射噪声的主要特点表现为:当射流上游条件充分乾净时远场声谱中有一族离散的谱峰,峰值频率对应于射流中She-laycr modes的特征频率和它们的干涉频率;各特征频率的声源位置和相应的混合层中的涡对卷并位置重合;远场声辐射呈天线效应;声源位置固定,无多善勒频移。     

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。     

Interactions of a propeller with a stator-induced circumferentially varying flow

The interactions of a circumferentially varying stator cascade and a downstream fixed pitch propeller were investigated experimentally. The global performance of the components and the coupled system were systematically investigated through force and moment measurements on the propulsor model in a water tunnel. In addition, the wake of the cyclic stator cascade with and without the propeller was investigated downstream from a propulsor model using the Stereoscopic PIV technique. A cyclic distribution of the stators’ deflections resulted in non-axisymmetric distributions of the flow field downstream of the stator array. The stator distribution alone produced a significant side force that increased linearly with stator pitch amplitude. When a propeller was incorporated downstream from the cyclic cascade, the side force from the stator cascade was reduced, but a small normal force and pitching moment were created. The generation of these secondary forces and moments can be related to the redistribution of the tangential flow from the cyclic cascade into the axial direction by the retreating and advancing blade states of the fixed pitch propeller.     

轴流泵参数化设计及应力与模态特征分析

以船用轴流式喷水推进泵为对象,探索了轴流泵参数化设计、水动力性能、静强度和结构声学特征分析的数值途径。轴流泵叶轮采用升力法设计,导叶采用流线法设计,叶片三维造型在NUMECA参数化设计平台中完成。轴流泵水动力性能校核由粘性CFD计算完成,CFD计算同时提取得到叶片分布式水动力载荷。叶片静强度校核由ANSYS有限元计算叶片应力和应变特征完成,应力分析时同时考虑水动力载荷、重力载荷和离心力载荷。叶片结构声学特征分析由NASTRAN有限元计算叶片模态振型和振型频率完成。计算结果表明,轴流泵扬程和功率满足设计指标,效率达87.13%;叶轮叶片形变相对于叶顶间隙来说为极小量,可忽略不计,叶片存在局部应力集中现象,最大应力小于许用应力,满足静强度要求;叶片前四阶振型特征与分析经验一致,且振型频率远离轴频、叶频及其谐频特征频率,能够避免共振产生。     

Finite element modelling of sheared flow effects on the radiation characteristics of acoustic sources in a circular duct

The recent interest in propeller noise generation, stimulated by development of new propeller types for commerical propjets, has generated a need for the ability of measure the noise characteristics of propellers. However, wind tunnel noise measurements are affected by reflections from the wind tunnel walls. Computer codes predicting the free-field noise of a propeller and its noise field in a circular wind tunnel allow validating the use of wind tunnel measurements to predict free-field noise characteristics. A wind tunnel contains flow which is uniform in the duct axial direction, but can vary in the radial direction. It can be shown that a third-order differential equation governs the acoustic pressure field for such a duct containing radially sheared subsonic flow. This third-order problem is then posed as a coupled pair of equations which are second-order in terms of acoustic density and first-order in terms of an artificial variable which represents the effects of the flow being sheared. It is shown that this form of the problem allows a natural extension of the existing numerical solution techniques for non-sheared flow. The sheared flow problem is presented, and a finite element method is developed to yield a solution for propeller-type acoustic forces. The finite element code and method are refined with numerical experiments, and results are presented for a specific propeller and duct geometry. Good agreement is shown between this method and an alternate approach to the sheared flow problem using a piecewise constant representation of the velocity in the boundary layer. This validates both the numerical methods.     

Non-intrusive aerodynamic loads analysis of an aircraft propeller blade

The flow field in a cross-sectional plane of a scaled Beaver DHC aircraft propeller has been measured by means of a stereoscopic PIV setup. Phase-locked measurements are obtained in a rotational frequency range from 18,900 to 21,000 rpm, at a relative Mach number of 0.6 at ¾ propeller radius. The use of an adapted formulation of the momentum equation in differential form for rotating frame of references, integrated with isentropic relations as boundary conditions, allowed to compute the pressure field around the blade and the surface pressure distribution directly from the velocity data in the compressible regime. The procedure, extended to the computation of the aerodynamic lift and drag coefficients by a momentum contour integral approach, proved to be able to couple the aerodynamical loads to the flow field on the moving propeller blade, comparing favorably with a numerical simulation of the entire scaled model. Results are presented for two propeller rotation speeds and three different yawing angles.     

叶片与蜗舌耦合对离心风机性能和旋转噪声影响的数值研究

利用三维N-S方程和RNGk-ε湍流模型对离心风机内部的非定常粘性流场进行了数值模拟,分析了不同时刻叶片与蜗舌所处的不同相对位置对风机瞬时性能、叶轮出口流动以及对蜗舌处的静压分布和静压脉动的影响。同时指出,改进特定时刻叶片与蜗舌处于特定相对位置时风机的瞬时性能是提高风机总体性能的一条新的途径。此外,还尝试运用一种新的方法,即不用求解声场而直接依据非定常流场中的静压脉动分析了蜗舌处主要气动噪声源的位置及其成因。     

Heat transfer characteristics in a sudden expansion pipe equipped with swirl generators

This investigation is aimed at studying the heat transfer characteristics and pressure drop for turbulent airflow in a sudden expansion pipe equipped with propeller type swirl generator or spiral spring with several pitch ratios. The investigation is performed for the Reynolds number ranging from 7500 to 18,500 under a uniform heat flux condition. The experiments are also undertaken for three locations for the propeller fan (N = 15 blades and blade angle of 65°) and three pitch ratios for the spiral spring (P/D = 10, 15 and 20). The influences of using the propeller rotating freely and inserted spiral spring on heat transfer enhancement and pressure drop are reported. In the experiments, the swirl generator and spiral spring are used to create a swirl in the tube flow. Mean and relative mean Nusselt numbers are determined and compared with those obtained from other similar cases. The experimental results indicate that the tube with the propeller inserts provides considerable improvement of the heat transfer rate over the plain tube around 1.69 times for X/H = 5. While for the tube with the spiral spring inserts, an improvement of the heat transfer rate over the plain tube around 1.37 times for P/d = 20. Thus, because of strong swirl or rotating flow, the propeller location and the spiral spring pitch become influential on the heat transfer enhancement. The increase in pressure drop using the propeller is found to be three times and for spiral spring 1.5 times over the plain tube. Correlations for mean Nusselt number, fan location and spiral spring pitch are provided.     

3D pressure imaging of an aircraft propeller blade-tip flow by phase-locked stereoscopic PIV

The flow field at the tip region of a scaled DHC Beaver aircraft propeller, running at transonic speed, has been investigated by means of a multi-plane stereoscopic particle image velocimetry setup. Velocity fields, phase-locked with the blade rotational motion, are acquired across several planes perpendicular to the blade axis and merged to form a 3D measurement volume. Transonic conditions have been reached at the tip region, with a revolution frequency of 19,800 rpm and a relative free-stream Mach number of 0.73 at the tip. The pressure field and the surface pressure distribution are inferred from the 3D velocity data through integration of the momentum Navier-Stokes equation in differential form, allowing for the simultaneous flow visualization and the aerodynamic loads computation, with respect to a reference frame moving with the blade. The momentum and pressure data are further integrated by means of a contour-approach to yield the aerodynamic sectional force components as well as the blade torsional moment. A steady Reynolds averaged Navier-Stokes numerical simulation of the entire propeller model has been used for comparison to the measurement data.     

“Analysis of the propeller wake evolution by pressure and velocity phase measurements”

In the present study an experimental analysis of the velocity and pressure fields behind a marine propeller, in non-cavitating regime is reported. Particle image velocimetry measurements were performed in phase with the propeller angle, to investigate the evolution of the axial and the radial velocity components, from the blade trailing edge up to two diameters downstream. In phase pressure measurements were performed at four radial and eight longitudinal positions downstream the propeller model at different advance ratios. Pressure data, processed by using slotting techniques, allowed reconstructing the evolution of the pressure field in phase with the reference blade position. In addition, the correlation of the velocity and pressure signals was performed. The analysis demonstrated that, within the near wake, the tip vortices passage is the most important contribution in generating the pressure field in the propeller flow. The incoming vortex breakdown process causes a strong deformation of the hub vortex far downstream of the slipstream contraction. This process contributes to the pressure generation at the shaft rate frequency.     

Flow-acoustic coupling in coaxial side branch resonators with rectangular splitter plates

Flow past symmetrically located side branches mounted in a duct can give rise to pronounced flow oscillations due to coupling between separated shear layers and standing acoustic waves. The acoustically-coupled flows were investigated using digital particle image velocimetry (PIV) in conjunction with unsteady pressure measurements. Global instantaneous, phase- and time-averaged flow images were evaluated to provide insight into the flow physics during flow tone generation. Onset of the locked-on resonant states was characterized in terms of the acoustic pressure amplitude and frequency of the resonant pressure peak. Structure of the acoustic noise source was discussed in terms of patterns of generated acoustic power, which was evaluated by applying the vortex sound theory in conjunction with global quantitative flow imaging and numerical simulation of the acoustic field. In addition to the basic side branch configuration, the effect of bluff rectangular splitter plates located along the centerline of the main duct was investigated. The first mode of the shear layer oscillation was inhibited by the presence of the plates, which resulted in substantial reduction of the amplitude of acoustic pulsations and the strength of the acoustic source.