NUMERICAL ANALYSIS OF THE INFLUENCE OF THE TIP CLEARANCE FLOWS ON THE UNSTEADY CAVITATING FLOWS IN A THREE- D IMENSIONAL INDUCER

To clarify the influences of the tip clearance flows on the unsteady cavitating flow,the three-dimensional unsteady cavitating flows through both the two-dimensional cascades and the three-dimensional inducer with and without tip clearance are performed numerically.The governing equations for the compressible fluid flow with the DES turbulence model are employed with the assumption of the isentropic process of liquid phase.The evolution of cavities is represented as the source/sink of vapor phase.The basic equations in the curve linear coordinate are solved by the finite difference method.As the results of the three-dimensional cavitating flows through the two-dimensional cascades,the tip clearance flows from the pressure side to the suction side of the blade produces the tip vortex cavitation,which affects the sheet cavitation on the leading edge of the next blade and enhances the blockage effect near the casing than the flows without tip clearance.On the other hand,in the case of the three-dimensional inducer,the large backflow cavitation is observed around the inlet of the inducer,where the cavities are developed on the casing by the tip clearance flows.The large pressure gradient between the non-cavitating pressure side and the cavitating suction side enhances the tip clearance flows.The calculation considering the tip clearance reproduces the developed cavitation region similar to that of experimental visualizations.Additionally,the backflow cavitation rotates with the speed slower than the rotation speed of the inducer.Then,the rotation of backflow cavitation causes the periodic fluctuation of the outlet pressure greater than that of the inlet pressure.     

三维水翼云空泡非定常特性数值分析及试验验证

采用Singhal空化模型和修改的κ-εRNG湍流模型,数值模拟了三维扭曲水翼非定常空泡流动及其云空泡的动态脱落,空泡形态、流场等定性结果与相应的试验结果进行了比较。预报的回射流和侧射流的流动特性,以及云空泡的动态脱落的主要特征与试验结果相一致。计算结果表明,对于外形为凸形的片状空泡,侧射流是片状空泡脱落的主要原因。     

通气空泡重力效应研究

该文基于VOF方法和有限体积法,求解气水多相流动的RANS方程及标准湍流模式,研究了通气空泡的重力效应.结果表明模拟得到的绕圆盘通气空泡的重力效应与Buyvol的分类准则吻合,通过数值模拟复演了通气空泡的双涡管泄气模式;证实由于与尾空泡的相互作用,重力作用下绕航行体通气空泡在尾部附近出现下沉,航行体上的空泡截面呈现出"月牙"形;阻力随空化数而减小,并在空泡完全包裹住航行体前部锥段时出现突降.     

绕轴对称体三维非定常空化流动的数值与实验研究

采用数值和实验相结合的方法研究了绕轴对称体三维非定常空化流动现象。实验中,采用高速摄像的技术和动态测力系统对绕半球型和平头型轴对称体的非定常空化流场及其动力特性进行了分析,观察了在不同空化数下,绕半球型和平头型轴对称体的空泡形态;测量了轴对称体受到的阻力,并对阻力信号进行了时频分析,得到了在非定常空化阶段,轴对称体动力特征频率。基于实验现象,发展了一种基于密度修正的分域空化流动的计算方法,并与实验结果进行了对比,结果表明:该方法可以较好的模拟绕轴对称体三维非定常空化流动现象。绕不同头型轴对称体的空化流场结构均存在明显的三维非定常流动特性,并且,空化流场形态与动力特征频率存在高度的相关性,不同头型轴对称体的非定常空化流场结构存在较大的差异,半球型轴对称体空泡流动的脉动主要是空泡尾部的高频小脱落引起的,而平头型轴对称体的空泡流脉动成分主要是大尺度的漩涡空泡团的周期性脱落。     

导弹垂直发射出筒过程中通气空泡流研究

将通气空泡技术应用于导弹水下垂直发射出筒过程,通气空泡是高速航行体获得稳定空泡的一种重要技术。采用基于Mixture多相流模型的有限体积法求解RANS方程,结合动网格技术,对水下垂直发射导弹出筒过程的轴对称流场进行了数值模拟,研究导弹的流体动力特性和通气空泡的演化。结果表明通气空泡可减小导弹出筒过程中的阻力和改善导弹的流体动力载荷。     

新型叶剖面设计及叶剖面参数对空泡特性影响的研究 …

本文是新型叶剖面设计及叶剖面参数对空泡特性影响的研究的第一部分：新型叶剖面设计，基于Ｅｐｐｌｅｒ的机翼叶剖面设计理论给 种新螺旋浆叶剖面设计方法。     

空泡在任意流场中的运动研究

本文从理论上较全面地分析了空泡在任意流场中的受力，在空泡运动中，考虑了变形场、有气体扩散、流体的可压缩性等因素的影响，建立了空泡在任意流场中的三维运动控制微分方程，给出了计算空泡运动的数值方法，并求解了空泡在一混流式水轮机转轮流场中的运动。     

钝体尾迹区通气空泡流动特性研究

该文采用实验的方法开展了不同雷诺数和通气量下钝体尾迹区通气空泡流动特性的研究,依据雷诺数Re和通气率Q_v建立了通气空泡气液两相流的流型图谱。根据通气空泡流动特征,将其分为两大类,分别是旋涡脱落型和相对稳定型。当通气率为Q_v=0.086 6时,雷诺数的改变不影响空泡流型,均属于旋涡脱落型。当通气率为Q_v=0.278时,钝体尾部有空泡包裹,随着雷诺数的增加,空泡长度显著减小,空泡形态由相对稳定型向旋涡脱落型转变。当雷诺数保持一致时,随着通气率的增加,均出现了由旋涡脱落型向相对稳定型转变的趋势。随着雷诺数的增加,由旋涡脱落型转变为相对稳定型所需要的通气率增大。     

SUPERCAVITY MOTION WITH INERTIAL FORCE IN THE VERTICAL PLANE

The curvilinear motion in a vertical plane is one of the most important features of the supercavitating vehicle. It is of great significance to study the controllability and the maneuverability of the supercavitating vehicle. Models are built for the effects of the angle of attack, the gravity and the inertial force in the curvilinear motion in the vertical plane. Numerical simulations are carried out for the supercavity motion based on these models combined with the Logvinovich model. It is shown that the maximum deviation displacement in the outward normal direction of the trajectory with a constant curvature, which occurs in the tail of the supercavity, increases as the cavitation number or the curvature radius of the supercavity trajectory decreases under the condition that other model and flow parameters are kept constant. For a varied curvature, the supercavity shape changes evidently because of the change of the ambient pressure, but with the same trend as in constant curvature. The deviation displacement increases along the supercavity length gradually.     

NUMERICAL STUDY OF THE PITCHING MOTIONS OF SUPERCAVITA-TING VEHICLES

The pitching motions of supercavitating vehicles could not be avoided due to the lost water buoyancy.In order to have some insight for the design of the supercavitating vehicles,the fixed frequency and free pitching motions are investigated.A numerical predicting method based on the relative motion principle and the non-inertia coordinate system is proposed to simulate the free pitching motions of supercavitating vehicles in the longitudinal plane.Homogeneous and two fluid multiphase models are used to predict the natural and the ventilated supercavitating flows.In the fixed frequency pitching motions,a variety of working conditions are considered,including the pitching angular velocities and the supercavity scales and the results are found to be consistent with the available experimental results in literature.The mesh deformation technology controlled by the moment of momentum equation is adopted to study the free pitching motions and finally to obtain the planing states proposed by Savchenko.The numerical method is validated for predicting the pitching motions of supercavitating vehicles and is found to enjoy better calculation efficiency as comparing with the mesh regeneration technology.