透平叶栅三维形状反问题研究

随着CFD技术的发展,基于伴随方法的求解Euler和NS方程的气动优化设计已成为流体力学形状反问题研究中的热门领域.本文应用该方法对透平叶栅进行三维气动优化设计,详细推导了Euler方程伴随系统的偏微分方程组及其各类边界条件,首次给出了透平内流伴随方程边界条件的具体形式,并给出伴随变量的物理意义.结合拟牛顿算法发展了三维透平叶栅形状反问题气动优化算法,并给出了算法的流程.     

复杂约束环境下基于控制理论的透平叶栅气动优化

本文应用控制理论,基于网格节点位置坐标直接变分法建立了N-S方程的伴随系统.以叶栅通道内熵增最小为目标函数,并以流量为约束条件,详细推导了具有约束条件的二维N-S方程伴随系统的偏微分方程组及其相应的边界条件和敏感性导数的表达式。建立了基于黏性连续伴随方程和N-S方程的二维叶栅气动优化设计系统,并成功地应用于某一跨音速叶栅的优化设计。对计算结果的分析表明,该方法能够适用于透平叶栅气动优化设计。     

应用控制理论的叶栅气动反设计

基于控制理论的气动设计方法作为一种基于梯度的优化方法,通过引入伴随系统计算目标函数的敏感性导数,大大降低设计成本.本文将基于控制理论的气动设计方法应用到透平叶栅的气动反问题中,应用Euler方程研究了二维叶栅的压力反设计问题,并讨论了该方法具体实施中的关键问题,包括采用非均匀B样条进行二维叶栅造型;应用Thompson时间相关边界条件理论进行伴随方程特征分析;研究伴随方程的数值求解方法,构造伴随方程的耗散通量.通过算例证明了该气动设计方法适用性好,速度快,可以大大节约计算成本.     

基于离散伴随方法的透平叶栅反设计

研究构建了基于离散伴随方法的叶轮机械叶栅气动反设计系统,将离散伴随系统从无黏环境扩展到了黏性环境,编程实现了黏性离散伴随求解器;改善了叶栅参数化方式并重新编程实现了叶栅参数化程序,解决了叶栅参数化过程中叶栅尾缘附近区域型线波动的问题。利用该系统对某二维跨声速透平叶栅在给定叶型壁面目标压力分布的情况下,通过构造目标函数将叶栅反设计问题转化为气动优化设计问题,成功进行了气动压力反设计。结果证明本文建立的叶栅反设计系统能够有效进行压力反设计,验证了本文建立的基于离散伴随方法叶轮机械叶栅气动反设计方法的正确性与有效性。     

基于控制理论和N-S方程的二维叶栅气动优化算法

基于控制理论的气动优化方法的计算量与设计变量无关,可快速精确地完成控制变量的灵敏度分析.本文以出口熵增最小为目标函数,详细推导了二维 N-S 方程伴随系统的偏微分方程组及其相应的边界条件和敏感性导数的表达式.以拟牛顿算法为优化求解器,利用 CFD 方法求解流动变量,采用时间推进方法求解伴随方程,建立了基于黏性伴随方法和 N-S 方程的二维叶栅气动优化设计算法.     

基于离散伴随方法的透平叶栅气动优化设计

本文研究并给出了基于离散伴随理论和自动微分技术构建离散伴随系统的方法、伴随系统的求解策略以及基于离散伴随方法的透平叶栅气动优化设计流程,建立了相应的优化设计系统。利用该优化系统在无黏环境下,以叶栅通道进出口的熵增率为目标函数、以叶栅通道内的质量流量为约束,对某二维跨音速透平叶栅进行了气动优化设计。与优化前相比,优化后透平叶栅进出口熵增率减少8.82%,质量流量变化幅度小于0.003%。优化结果表明,本文提出的优化系统能够有效改善透平叶栅的气动优化性能,验证了本文提出的基于离散伴随方法的透平叶栅气动优化设计方法的正确性与有效性。     

高负荷低压涡轮的多级气动优化设计

采用多级涡轮气动优化设计流程对某四级高负荷低压涡轮进行多级气动优化设计.首先采用准三维设计减少静叶叶片数,并初步提高性能,然后应用多级局部优化进一步提高总体性能.优化联合采用人工神经网络和遗传算法对各列叶栅进行三维局部优化.流场计笄采用全三维粘性流N-S方程求解.通过优化设计,改变了级负荷系数和切向升力系数在各级中的分布,改善了各列的性能,总效率提高0.6%,总流量基本不变,总体性能提高.     

叶栅内定常及非定常粘性流动数值模拟

本文给出了一个模拟叶栅内准三维定常和非定常粘性流动的数值方法。对于定常流动,采用ＴＶＤ Ｌａｘ－Ｗｅｎｄｒｏｆｆ格式和代数湍流模型求解雷诺平均Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程,使用当地时间步长和多网格技术使计算加速收敛到定常状态;对于非定常流动,使用双时间步长和全隐式离散,采用与求解定常流动相似的多网格方法求解隐式离散方程。文中给出了ＶＫＩ透平叶栅内的定常流结果和１．５级透平叶栅内的非定常数值结果。     

叶轮机三维反方法伴随方程推导及其应用

通常的叶轮机械三维反方法存在以下问题:与使用者的经验相关;难以考虑多叶排之间的气动匹配;不能保证取得最优解等。本文创新性地将反方法与伴随方法相结合,充分利用伴随方法的计算时间与优化变量个数无关的特性,以期克服反方法的诸多问题,建立三维自动化的优化设计体系。本文首先推导了反方法的中弧线生成方程;在此基础上得到的Euler方程的伴随方法及其边界条件,中弧线生成方程的伴随方程及其边界条件;进一步地,本文开发了相应的设计体系;最后本文以亚琛1-1/2涡轮级为算例验证了本方法的有效性。     

非轴对称端壁与三维叶片联合成型气动设计优化

耦合自适应差分进化算法,非轴对称端壁与叶片联合成型参数化方法和RANS方程求解技术,提出了非轴对称端壁与叶片联合成型设计优化方法。利用该方法,完成了某小展弦比透平叶栅的气动设计优化,并且详细分析了最优设计叶片三维参数化及非轴对称端壁造型对气动性能的影响,验证了本设计优化方法的正确性和有效性。     

升力系数不变时跨音速机翼阻力优化设计

基于共轭方程的优化设计理论,应用三维欧拉方程进行了升力系数不变时跨音速机翼阻力优化设计研究,根据给定的目标函数推导了在物理空间上表述的共轭方程及边界条件,研究了共轭方程的数值求解方法及目标函数对设计变量的敏感性导数求解问题,发展了一种跨音速机翼阻力优化设计方法,应用该设计方法进行了跨音速机翼阻力优化设计研究,优化后机翼表面的激波强度减弱很多,有效减少了波阻.     

汽轮机小长径比静叶片的优化径向积叠

应用粘性流动数值计算对叶轮机械叶片进行设计，能够使设计者对几种不同设计方案进行分析以满足设计要求，并获得最佳设计方案．本文采用三维N．S方程组和Baldwin-Lomax湍流模型，对一个小长径比的汽轮机导叶进行三维粘性流场数值模拟．计算结果表明，采用合适的周向弯曲（优化径向积叠）同样可以提高短叶片的效率．本计算方法可用来分析和研究叶片径向积叠形式对径向和周向流量平均绝热效率的影响，以获得较优的积叠形式．     

Heat transfer prediction on transonic turbine blades

The design and optimization of turbine blades submitted to high-temperature flows require the prediction of aerodynamic and thermal flow characteristics. A computation method for aerothermal viscous flows has been developed. The method is based on a compressible boundary layer approach. Tests were performed on turbine blade configurations. These tests include most difficulties that can be encountered in reality: laminar-turbulent transition, separation bubbles, strong accelerations, shock waves. Predictions of the wall heat transfer prove to be satisfactory.     

A time-reversal lattice Boltzmann method

In this paper we address the time-reversed simulation of viscous flows by the lattice Boltzmann method (LB). The theoretical derivation of the reversed LB from the Boltzmann equation is detailed, and the method implemented for weakly compressible flows using the D2Q9 scheme. The implementation of boundary conditions is also discussed. The accuracy and stability are illustrated by four test cases, namely the propagation of an acoustic wave in a medium at rest and in an uniform mean flow, the Taylor–Green vortex decay and the vortex pair–wall collision.     

Level set based structural topology optimization for minimizing frequency response

For the purpose of structure vibration reduction, a structural topology optimization for minimizing frequency response is proposed based on the level set method. The objective of the present study is to minimize the frequency response at the specified points or surfaces on the structure with an excitation frequency or a frequency range, subject to the given amount of the material over the admissible design domain. The sensitivity analysis with respect to the structural boundaries is carried out, while the Extended finite element method (X-FEM) is employed for solving the state equation and the adjoint equation. The optimal structure with smooth boundaries is obtained by the level set evolution with advection velocity, derived from the sensitivity analysis and the optimization algorithm. A number of numerical examples, in the frameworks of two-dimension (2D) and three-dimension (3D), are presented to demonstrate the feasibility and effectiveness of the proposed approach.     

Dynamic Modeling and Analysis of Wind Turbine Blade of Piezoelectric Plate Shell

This paper presents a theoretical analysis of vibration control technology of wind turbine blades made of piezoelectric intelligent structures. The design of the blade structure, which is made from piezoelectric material, is approximately equivalent to a flat shell structure. The differential equations of piezoelectric shallow shells for vibration control are derived based on piezoelectric laminated shell theory. On this basis, wind turbine blades are simplified as elastic piezoelectric laminated shells. We establish the electromechanical coupling system dynamic model of intelligent structures and the dynamic equation of composite piezoelectric flat shell structures by analyzing simulations of active vibration control. Simulation results show that, under wind load, blade vibration is reduced upon applying the control voltage.     

Aerodynamic design optimization by using a continuous adjoint method

This paper presents the fundamentals of a continuous adjoint method and the applications of this method to the aerodynamic design optimization of both external and internal flows.General formulation of the continuous adjoint equations and the corresponding boundary conditions are derived.With the adjoint method,the complete gradient information needed in the design optimization can be obtained by solving the governing flow equations and the corresponding adjoint equations only once for each cost function,regardless of the number of design parameters.An inverse design of airfoil is firstly performed to study the accuracy of the adjoint gradient and the effectiveness of the adjoint method as an inverse design method.Then the method is used to perform a series of single and multiple point design optimization problems involving the drag reduction of airfoil,wing,and wing-body configuration,and the aerodynamic performance improvement of turbine and compressor blade rows.The results demonstrate that the continuous adjoint method can efficiently and significantly improve the aerodynamic performance of the design in a shape optimization problem.