MHD控制超声速边界层的理论研究和数值分析

对MHD(mechanisms of magnetohy drodynamics)控制超声速平板湍流边界层的机理进行了理论研究和数值模拟. 理论上,采用等离子体低频近似碰撞频率模型,建立等离子体中电子和离子的力平衡方程,得到等离子体速度、极化电场以及边界层速度. 数值上,通过空间HLLE格式、LU--SGS时间推进求解时均磁流体动力学湍流方程,其中湍流模型采用sst--k\omega双方程模型. 研究结果表明:(1)边界层速度的理论结果和数值结果误差在7%范围内;(2)只有磁场而电场为零时,洛仑兹力起到减小摩阻的作用. 施加电场后,洛仑兹力能够加速边界层低速区流体;(3) 在边界层外层,越靠近壁面,作用参数越小;而在边界层近壁区黏性底层,虽然惯性力减小, 但黏性力却迅速增加,因此越靠近壁面,作用参数反而越大,加速低速流的代价增加.      

跨声速激波边界层相互作用的被动控制

运用激波管风洞在Ｒ＿（ｅ∞／ｍ＝３×１０￣７，Ｍ＿∞＝０．７３２－０．８１７范围内，在厚度比为１２％的圆弧翼型半模型和厚度比为１４％的超临界翼型半模型上，对被动控制现象及其若干规律进行了实验研究。结果表明，不同空腔深度的开孔壁和导管连通壁均可对壁面激波与边界层的相互作用实现被动控制，使得沿以上两种模型表面的马赫数峰值、逆压力梯度和激波强度明显减小。这对于飞行器将起到减阻作用，如将这一原理和方法用于超、跨声速压气机内激波与边界层相互作用的控制，将提高压气机的效率和工作的稳定性。     

跨声速激波边界层相互作用的被动控制

运用激波管风洞在Ｒ＿（ｅ∞／ｍ＝３×１０￣７，Ｍ＿∞＝０．７３２－０．８１７范围内，在厚度比为１２％的圆弧翼型半模型和厚度比为１４％的超临界翼型半模型上，对被动控制现象及其若干规律进行了实验研究。结果表明，不同空腔深度的开孔壁和导管连通壁均可对壁面激波与边界层的相互作用实现被动控制，使得沿以上两种模型表面的马赫数峰值、逆压力梯度和激波强度明显减小。这对于飞行器将起到减阻作用，如将这一原理和方法用于超、跨声速压气机内激波与边界层相互作用的控制，将提高压气机的效率和工作的稳定性。     

柴油机废气涡轮增压器压气机的气动噪声源特性研究

基于雷诺时均方程(RANS)及双方程湍流模型,建立了船用大功率增压器压气机的内部流场计算模型;计算了压气机叶轮流道内的流速分布和湍流流场,得到叶片顶部出口附近的流速分布在1.02马赫和1.1马赫之间;采用基于声比拟的数值积分方法(FW-H方程),得到了压气机叶轮的气动噪声源,并比较了主叶片和分流叶片顶部出口位置的气动噪声频谱特征,发现两者的噪声级及叶频分布存在差异。计算表明:压气机在轴频及其谐波频率处的噪声远小于叶频噪声,主流叶片及分流叶片紊流的噪声成因不同;压气机内部流噪声源的大小主要取决于气流速度;压气机转速由8000r/min增加至16000r/min、由16000r/min增加至22000r/min,流噪声的幅值约增加12dB。     

计算多级轴流压气机阻塞系数和减功系数的新方法

讨论了轴流压气机环壁边界层的流量阻塞效应和减功效应,提出了一种工程上可以简便适用波压气机设计和分析用的新的阻塞系数和减功系数计算方法,并应用于二台导叶可调及淡可调的十多级轴流压气机变工况的性能分析计算,结果与实验值吻合良好。     

液体边界层对平板结构振动阻尼效应分析

本文分析了液体边界层对平板振动的阻尼效应，基于液体的Stokes边界层理论，建立了考虑液体边界层阻尼效应的平板振动单自由度系统运动方程，利用Laplace变换方法求解了运动方程，得到了平板结构的位移响应解答，制作了一个单自由度质量-弹簧系统来测量水体粘滞阻尼效应，并将理论与试验结果进行了对比分析，表明Stokes边界层理论能较好模拟水体的粘滞阻尼特性，边界层阻尼明显减小了结构的动力响应，本文最后讨论了所提的分析方法的适用范围．     

离心压气机的堵塞与喘振

本文在离心压气机试验工作基础上对堵塞与喘振现象进行了分析,介绍了计算叶片扩压器与叶轮堵塞流量的方法以及设计中导风轮进口喉部面积与叶片扩压器喉部面积应保持的正确比例。计算结果与试验数据进行比较获得了较好的一致性。本文还介绍了叶片扩压器与叶轮流道静压分布的测量结果,并结合试验现象运用边界层概念对离心压气机喘振问题进行了分析。      

离心泵叶片边界层分离对水动力特性的影响

给出了离心泵叶片近壁表面流体粘性流动的分析方法,通过对叶片压力面边界层参数的计算和边界层分离的判断,确定分离型和流线型叶片型线,又通过对测试泵的性能对比试验,验证了叶片型线对水动力特性的影响,明确了这种影响主要体现在离心泵的水力效率、动力性能方面,并指出叶片形状的变化是导致其表面流体边界层分离点位置移动的主要原因,它决定了边界层是否分离,而过大的分离将使测试泵的性能下降,振动剧烈、噪声增大,并强调应重视边界层分析在叶片水力设计中的作用,同时给出了叶片型线水力设计的评价依据。所得结论对低比转速离心泵水动力特性的改善有参考价值。     

考虑法向压力梯度的三维旋转边界层计算

本文以量级分析为基础,建立了一般曲线坐标系上的三维旋转边界层方程。对旋转在边界层中的影响进行分析之后,提出了一个能够处理壁面法向压力梯度不为零问题的压力梯度迭代方法。在传统的Box法的基础上发展了一套完整的求解三维旋转边界层的方法和程序,并对螺旋面、压气机转子叶面以及圆柱面上的旋转边界层进行了计算,与他人的计算和实验的对比分析表明,该方法和程序是正确的,可用于求解任意几何物面上的三维旋转边界层。     

水泵叶片表面三维边界层计算

本文用有限差分法计算混流式可逆水力机械水泵工况叶片表面的三维边界层。水泵叶轮中主流区的三维势流由直接边界元法计算。对于叶片面附近的粘性流动。用三维半正交坐标系中的边界层方程表示。为了提高计算精度采用贴体坐标技术生成边界层区域的计算网格。并利用Cebeci等变换函数及Keller差分格式离散方程。用分块解法求解。计算叶轮叶片表面的压力分布与相应试验结果进行了对比。     

Laplace transform method in boundary value problems for the Helmholtz equation

The purpose of this present note is to obtain boundary integral equation formulations of boundary value problems for the two-dimensional Helmholtz equation. The intergral equations are derived using the Laplace transform method.     

Stability of viscoelastic rectangular plate with a piezoelectric layer subjected to follower force

The effects of a piezoelectric layer on the stability of viscoelastic plates subjected to the follower forces are evaluated. The differential equation of motion of the viscoelastic plate with the piezoelectric layer is formulated using the two-dimensional viscoelastic differential constitutive relation and the thin plate theory. The weak integral form of the differential equations and the force boundary conditions are obtained. Using the element-free Galerkin method, the governing equation of the viscoelastic rectangular plate with elastic dilatation and Kelvin–Voigt distortion is derived, subjected to the follower forces coupled with the piezoelectric effect. A generalized complex eigenvalue problem is solved, and the force excited by the piezoelectric layer due to external voltage is modeled as the follower tensile force; this force is used to improve the stability of the non-conservative viscoelastic plate. For the viscoelastic plate with various boundary conditions, the results for the instability type and the critical loads are presented to show the variations in these factors with respect to the location of the piezoelectric layers and the applied voltages. The stability of the viscoelastic plates can be effectively improved by the determination of the optimal location for the piezoelectric layers and the most favorable voltage assignment.     

不可压粘性流体浸入边界直接力法及软件实现

浸入边界法通过在N-S方程中施加体积力模拟不可滑移固壁边界及动边界，避免生成复杂贴体网格及动网格，极大地节省了网格建模时间及动网格计算消耗。本文提出一种新型附加体积力简化计算方法，将简化附加体积力以源项形式嵌入动量方程迭代中，通过用户自定义函数对CFD软件FLUENT二次开发，实现了浸入边界法和通用流体力学求解器的耦合计算。通过静止圆柱和动圆柱绕流数值模拟进行了验证，并探讨了插值函数对计算精度的影响。研究表明，通过引入浸入边界模型，能够提高计算效率，并实现结构网格背景下复杂边界和动边界的高效建模。     

CONTROL OF BLADE FLUTTER USING CASING WITH ACOUSTIC TREATMENT

Control of blade flutter by use of a nonrigid wall may have several advantages compared with the existing method of suppressing blade flutter; but it indeed leads to numerous theoretical problems which have never been clearly elucidated by the existing theories. In the present investigation a new lifting surface model has been suggested based on the application of generalized Green's function theory and double Fourier transformation technique, which is expressed as various upwash integral equations and the corresponding kernel function. In particular, it is found that the change of wall boundary condition not only affects the eigenvalues of the system but also the eigenfunction normalizing factor in comparison with a rigid boundary condition, and it is these variations that finally affect the flow and acoustic field. In addition, the numerical results show that whether a nonrigid wall has positive or negative effect on suppressing blade flutter will mainly depend on what admittance value the wall possesses. It is clear that this conclusion has two implications. One is that there is indeed some possibility for designing a liner for suppressing blade flutter. The second is that modern jet engines using a nonrigid wall or liner to suppress the noise can introduce a detrimental effect on blade flutter stability.     

The interaction of a shock wave with the boundary layer in a reflected shock tunnel

The influence of a nontotal reflection on the interaction of a reflected shock wave with the boundary layer in a reflected shock tunnel has been investigated. The calculating method of the velocity, the temperature and the Mach number profiles in the boundary layer in reflected shock fixed coordinates has been obtained. To account for equilibrium real gas effects of nitrogen, the numerical results show that the minimum Mach number in the boundary layer has been moved from the wall into the boundary layer with the increasing of the incident shock Mach number. The minimum Mach number, the shock angle in the bifurcated foot and the jet velocity along the wall to the end plate are reduced owing to the increasing of the area of nozzle throat. The numerical results are in good agreement with measurements.     

PIV-based pressure fluctuations in the turbulent boundary layer

The unsteady pressure field is obtained from time-resolved tomographic particle image velocimetry (Tomo-PIV) measurement within a fully developed turbulent boundary layer at free stream velocity of U _???=?9.3?m/s and Re_???=?2,400. The pressure field is evaluated from the velocity fields measured by Tomo-PIV at 10?kHz invoking the momentum equation for unsteady incompressible flows. The spatial integration of the pressure gradient is conducted by solving the Poisson pressure equation with fixed boundary conditions at the outer edge of the boundary layer. The PIV-based evaluation of the pressure field is validated against simultaneous surface pressure measurement using calibrated condenser microphones mounted behind a pinhole orifice. The comparison shows agreement between the two pressure signals obtained from the Tomo-PIV and the microphones with a cross-correlation coefficient of 0.6 while their power spectral densities (PSD) overlap up to 3?kHz. The impact of several parameters governing the pressure evaluation from the PIV data is evaluated. The use of the Tomo-PIV system with the application of three-dimensional momentum equation shows higher accuracy compared to the planar version of the technique. The results show that the evaluation of the wall pressure can be conducted using a domain as small as half the boundary layer thickness (0.5??₉₉) in both the streamwise and the wall normal directions. The combination of a correlation sliding-average technique, the Lagrangian approach to the evaluation of the material derivative and the planar integration of the Poisson pressure equation results in the best agreement with the pressure measurement of the surface microphones.     

On the throughflow with swirling inflow in annular diffuser

In this paper, a throughflow with swirling inflow in an annular diffuser is calculated. Under the assumption of smallcross-flow, the flow near inner and outer wall surfaces is calculated based on the three-dimensional momentum integral equation of the boundary layer. The potential fiow outside the boundary layer is cornputed by means of the iteration method based on the velocity gradient equation along the quasi-orthogonal direction of the meridional projection of the stream-line on the meridional surface and the constancy of fiux equation. The numerical results agree with the experiments quite well. This method is useful for analyzing the throughfiow with pre-swirl in the annular diffuser.     

DNS,LES and RANS of turbulent heat transfer in boundary layer with suddenly changing wall thermal conditions

The objectives of this study are to investigate a thermal field in a turbulent boundary layer with suddenly changing wall thermal conditions by means of direct numerical simulation (DNS), and to evaluate predictions of a turbulence model in such a thermal field, in which DNS of spatially developing boundary layers with heat transfer can be conducted using the generation of turbulent inflow data as a method. In this study, two types of wall thermal condition are investigated using DNS and predicted by large eddy simulation (LES) and Reynolds-averaged Navier–Stokes equation simulation (RANS). In the first case, the velocity boundary layer only develops in the entrance of simulation, and the flat plate is heated from the halfway point, i.e., the adiabatic wall condition is adopted in the entrance, and the entrance region of thermal field in turbulence is simulated. Then, the thermal boundary layer develops along a constant temperature wall followed by adiabatic wall. In the second case, velocity and thermal boundary layers simultaneously develop, and the wall thermal condition is changed from a constant temperature to an adiabatic wall in the downstream region. DNS results clearly show the statistics and structure of turbulent heat transfer in a constant temperature wall followed by an adiabatic wall. In the first case, the entrance region of thermal field in turbulence can be also observed. Thus, both the development and the entrance regions in thermal fields can be explored, and the effects upstream of the thermal field on the adiabatic region are investigated. On the other hand, evaluations of predictions by LES and RANS are conducted using DNS results. The predictions of both LES and RANS almost agree with the DNS results in both cases, but the predicted temperature variances near the wall by RANS give different results as compared with DNS. This is because the dissipation rate of temperature variance is difficult to predict by the present RANS, which is found by the evaluation using DNS results.