基于近似技术的涡轮叶片气动优化设计

根据五次多项式方法进行三维涡轮叶片的参数化建模,采用N-S方程和湍流模型进行三维流场分析计算,以K-S函数法作为优化方法,利用近似技术加速循环优化速度,建立了一种基于近似技术的涡轮叶片的气动优化方法。将气动效率和总压比作为目标函数,对涡轮叶片进行多目标气动优化、形状优化。算例表明本文提出的涡轮叶片优化设计方法是有效的。     

基于可行域调整策略的多约束材料优化设计

研究基于可行域调整策略的多约束结构材料优化问题。建立了以结构柔顺度为目标函数,考虑体积、位移、结构自振频率为约束条件的结构材料优化模型和目标函数及约束函数近似式,并采用可行域调整策略和对偶算法求解。典型结构材料优化设计结果表明:可行域调整策略使优化过程平稳,获得的序列细观结构拓扑构型清晰;相比于单一体积约束结构拓扑优化求解,考虑多约束结构拓扑优化能获得更好的黑白占优解。     

植物叶脉自然选择过程的拓扑优化模拟研究

为了研究叶脉及其分布形式(叶脉序)对改善植物叶片动力学特性的影响,并发掘其工程价值,通过拓扑优化模拟叶脉的发生和自然选择过程。基于变密度法对一系列以真实植物叶片为基础建立的"双层薄板结构"叶片的有限元模型进行了拓扑优化;在拓扑优化过程中,以变形能最小(自然频率最大)为目标函数,以85%的体积缩减量为约束条件,得出了5种不同尺寸模型的拓扑优化结果。结果表明:5种模型的拓扑优化结果分别与真实的阔叶叶片脉序和条形叶片脉序相吻合,本文方法是可行的;5种模型优化后的自然频率分别提高了55.28%、296.89%、81.35%、220.37%、61.78%,植物叶脉对增强叶片动力学性能是具有显著贡献的。研究结果为板壳结构加强筋的优化设计提供了仿生学参考。     

基于区间的不确定多目标优化方法研究

基于非线性区间优化,提出了一种不确定多目标优化方法.基于区间序关系和区间可能度,把不确定多目标的目标函数和约束转化为确定性的目标函数和确定性的约束.对于复杂的工程优化问题,为了提高效率,采用拉丁方试验设计方法,构建响应面近似模型,并基于近似模型进行不确定多目标优化,从而形成了非线性区间优化方法与近似模型相结合的高效不确定多目标优化方法.数值算例表明了该方法的有效性和工程实用性.     

柔性伸缩蒙皮支撑结构的多目标拓扑优化

针对柔性伸缩蒙皮支撑结构的多目标拓扑优化问题,分析了其实际应用中的优化对象及目标函数,提出使用六边形对设计域进行离散的方法,并建立离散模型与位矩阵的映射关系。采用基于位矩阵的NSGA-Ⅱ（Non-dominated Sorting Genetic Algorithm Ⅱ）进行求解。优化过程中引入个体连通性分析以提高计算效率。通过对可行个体进行有限元分析,获得其目标值;使用罚函数法对不可行个体加以惩罚,最终得到一组互不支配的支撑结构。结果表明,本方法可为柔性伸缩蒙皮支撑结构的多目标拓扑优化问题提供可行、有效的解,也可用于求解其它二维多目标拓扑优化问题。     

基于SIMP材料插值模型的周期性结构拓扑优化

利用SIMP材料插值模型研究了双方向周期性结构的拓扑优化。为了使结构获得具有双方向周期性的拓扑形式,将优化域分成若干个子域,并构建了一个虚拟子域;将各子域内各单元的相对密度的平均值和应变能的平均值作为虚拟子域内单元的相对密度和应变能,以结构的最小柔度为目标函数,单元相对密度为设计变量,构建了周期性拓扑优化问题的数学模型,并在数学模型中加入额外的约束条件;采用优化准则法推导出虚拟子域设计变量的迭代公式,利用体积约束计算出拉格朗日乘子;通过平面矩形悬臂梁结构算例获得了具有双方向的周期性拓扑形式,验证了利用SIMP材料插值模型实现双方向周期性拓扑优化的可行性和有效性。     

连续纤维增强复合材料结构基频最大化设计

与传统的金属材料相比, 纤维增强复合材料在强度、刚度、抗断裂等诸多方面具备更优良的性能, 目前纤维增强复合材料已在汽车、航空航天等工业领域得到了广泛应用. 本文提出一种求解连续纤维增强复合材料结构无阻尼自由振动下的基频最大化问题的拓扑优化方法. 为了实现结构拓扑构型与纤维角度的同步优化, 建立了以准许的材料用量体积分数为约束、以结构的一阶特征值为目标函数的动力学拓扑优化模型, 该模型包括表征结构拓扑构型的密度设计变量和表征纤维方向的角度设计变量. 详细推导了特征值目标函数关于密度设计变量和角度设计变量的解析灵敏度列式, 并采用移动渐进线方法 (method of moving asymptotes, MMA) 进行了优化求解; 最后通过3个数值算例验证本文方法的有效性, 其中包括一个以刚度最大化为目标的静力学优化算例, 和两个以一阶特征值为目标的动力学优化算例. 结果表明, 所提方法优化迭代过程稳健, 收敛快, 能够在实现结构拓扑构型与纤维角度的一体化优化的同时, 有效提高结构的频率.      

柔性伸缩蒙皮支撑结构的多目标拓扑优化

针对柔性伸缩蒙皮支撑结构的多目标拓扑优化问题,分析了其实际应用中的优化对象及目标函数,提出使用六边形对设计域进行离散的方法,并建立离散模型与位矩阵的映射关系。采用基于位矩阵的NSGA-Ⅱ(Nondominated Sorting Genetic Algorithm Ⅱ)进行求解。优化过程中引入个体连通性分析以提高计算效率。通过对可行个体进行有限元分析,获得其目标值;使用罚函数法对不可行个体加以惩罚,最终得到一组互不支配的支撑结构。结果表明,本方法可为柔性伸缩蒙皮支撑结构的多目标拓扑优化问题提供可行、有效的解,也可用于求解其它二维多目标拓扑优化问题。     

MA对偶-信赖域算法在非线性不等式约束优化问题中的应用研究

针对含有非线性不等式约束条件的优化问题,提出了MA对偶-信赖域算法。在每次迭代过程中,基于信赖域方法和问题的逼近属性,构造了原优化问题中目标函数和约束函数的移动渐进线函数,由此建立简单的子优化问题。运用对偶方法求解子问题得到原优化问题的下降方向,再用线搜索方法取得搜索步长,最后得到下一步的迭代点。应用数学推理证明了该算法的全局收敛性。以悬臂梁最小柔度问题为例,应用MA对偶-信赖域算法对优化问题进行了求解,数值算例的结果表明,MA对偶-信赖域算法在求解非线性约束优化问题时比MMA和GCMMA算法的迭代次数少,收敛速度快。     

基于高斯原理的非理想系统动力学建模

高斯原理给出了通过求函数极值、从可能运动中鉴别出真实运动的规则, 它可以使得多体系统动力学问题不需通过求解微分(代数)方程, 而是采用求解最小值的优化方法来解决, 从而提供了一种适用于优化算法的建模思路, 因此, 如何定义恰当的高斯拘束函数是动力学优化方法得以实现的前提. 对于理想系统而言, 约束对系统的作用可以通过约束方程来体现, 故高斯拘束可表达为系统质点加速度的函数, 系统的动力学问题因此可以描述为目标函数为高斯拘束函数、优化变量为质点加速度的约束最优化问题; 当系统中需要考虑干摩擦等非理想因素时, 部分相互作用不能被所定义的约束方程所涵盖而需要采用额外的物理规律来描述, 这种相互作用破坏了原有的针对理想系统的高斯拘束函数的极值特性. 基于变分类的高斯原理, 推导并证明了目标函数以理想约束力所表达的非理想系统的极值原理, 针对目前文献中用于非理想系统的高斯原理进行了讨论, 指出其实际为文中的极值原理在非理想约束力与理想约束力无明显关联时的一种特殊表达形式, 当非理想约束力与理想约束力有明显的函数关系(如库仑摩擦定律中滑动摩擦力与法向约束力间的线性关系)时, 该形式失效; 同时根据文中的极值原理, 得到了考虑库仑摩擦时非理想的多体系统动力学问题的优化模型. 例子中分析了优化模型及相应的线性互补性模型的关系, 分析发现在满足刚体滑动问题的唯一性条件下二者互为充分必要条件, 从而证明了文中优化模型的可靠性; 并采用优化计算方法进行了动力学模拟, 模拟结果显示了将高斯原理与优化算法相结合的可行性及有效性.      

Numerical simulation of flapping‐wing insect hovering flight at unsteady flow

A computational fluid dynamics (CFD) analysis was conducted to study the unsteady aerodynamics of a virtual flying bumblebee during hovering flight. The integrated geometry of bumblebee was established to define the shape of a three‐dimensional virtual bumblebee model with beating its wings, accurately mimicking the three‐dimensional movements of wings during hovering flight. The kinematics data of wings documented from the measurement to the bumblebee in normal hovering flight aided by the high‐speed video. The Navier–Stokes equations are solved numerically. The solution provides the flow and pressure fields, from which the aerodynamic forces and vorticity wake structure are obtained. Insights into the unsteady aerodynamic force generation process are gained from the force and flow‐structure information. The CFD analysis has established an overall understanding of the viscous and unsteady flow around the virtual flying bumblebee and of the time course of instantaneous force production, which reveals that hovering flight is dominated by the unsteady aerodynamics of both the instantaneous dynamics and also the past history of the wing. A coherent leading‐edge vortex with axial flow and the attached wingtip vortex and trailing edge vortex were detected. The leading edge vortex, wing tip vortex and trailing edge vortex, which caused by the pressure difference between the upper and the lower surface of wings. The axial flow, which include the spanwise flow and chordwise flow, is derived from the spanwise pressure gradient and chordwise pressure gradient, will stabilize the vortex and gives it a characteristic spiral conical shape. Copyright © 2006 John Wiley & Sons, Ltd.     

A novel method for automated grid generation of ice shapes for local‐flow analysis

Modelling a complex geometry, such as ice roughness, plays a key role for the computational flow analysis over rough surfaces. This paper presents two enhancement ideas in modelling roughness geometry for local flow analysis over an aerodynamic surface. The first enhancement is use of the leading‐edge region of an airfoil as a perturbation to the parabola surface. The reasons for using a parabola as the base geometry are: it resembles the airfoil leading edge in the vicinity of its apex and it allows the use of a lower apparent Reynolds number. The second enhancement makes use of the Fourier analysis for modelling complex ice roughness on the leading edge of airfoils. This method of modelling provides an analytical expression, which describes the roughness geometry and the corresponding derivatives. The factors affecting the performance of the Fourier analysis were also investigated. It was shown that the number of sine–cosine terms and the number of control points are of importance. Finally, these enhancements are incorporated into an automated grid generation method over the airfoil ice accretion surface. The validations for both enhancements demonstrate that they can improve the current capability of grid generation and computational flow field analysis around airfoils with ice roughness. Copyright © 2004 John Wiley & Sons, Ltd.     

飞艇尾翼脉动压力特性实验研究

在中航气动院FL-9低速风洞中,进行了飞艇尾翼脉动压力特性实验研究。测量了尾翼的脉动压力,着重分析了各测量点的脉动压力系数、频谱和相关性系数等特性。结果表明:脉动压力系数由尾翼前缘向后缘逐渐增大。尾翼的中部和前缘脉动压力系数随迎角无明显变化,在迎角超过8°以后,尾翼后缘的脉动压力系数随迎角增大而急剧增加。连续变迎角测量结果与固定迎角测量结果相比,脉动压力系数产生了明显的迟滞特性。尾翼上表面脉动压力的自相关系数和互相关系数从前缘到后缘逐渐降低,且前缘表现出显著自相关性,下翼面脉动压力基本互不相关。     

Influence of film thickness and cross-sectional geometry on hydrophilic microchannel condensation

Condensation in hydrophilic microchannel is strongly influenced by the channel cross-sectional geometry and the condensing surfaces hydrophobicity, which govern the evolution of the liquid film. This work makes progress on studying the relationship between channel geometry and condensation through flow regime visualizations, film-thickness measurements with optical interferometery, and temperature profile measurements with heat flux distribution construction. The hydrophilic microchannels have aspect ratios ranging from 1 to 5 and hydraulic diameters from 100 μm through 300 μm. The experimental measurement qualitatively matches the prediction of previous theoretical models accounting for the surface tension effect, which highlights the importance of surface tension force and channel geometry in the microchannel condensation. Pressure drop and mean heat flux measurements show that a larger channel is favorable for minimizing the pressure drop, while a smaller channel size and higher aspect ratio are desirable for maximizing the mean heat flux. The optimization of the channel geometry for a given application lies in the trade-off between these two factors.     

乘波体压缩面变化对其气动性能影响分析

乘波体是一种利用激波包裹特性获得高升阻比的高速飞行器构型.已有研究中,乘波体气动性能的改善主要依赖于给定源流场条件下的前缘型线优化.本文采用数值优化和计算流体力学模拟为主要手段分析了乘波体压缩面变化对其气动性能的影响,以期有效拓展乘波体的设计空间.主要内容如下:首先给出了一种基于表面局部变形的乘波体设计方法.其次结合运用增量修正参数化方法、计算流体力学分析和微分演化算法构造了乘波体压缩面外形气动优化设计流程,以一种椭圆锥形流场生成的乘波体作为基准构型开展了无黏优化.之后从优化结果中选择升阻比递增的6个典型构型进行前缘钝化处理后,基于N-S方程对其气动性能进行了评估.最后综合依据无黏/黏性计算结果分析了乘波体压缩面变化对其气动性能的影响.结果表明该部分形状的改变对乘波体气动性能影响十分明显,在升力面积不变的条件下,乘波体压缩面形状变化可导致其升阻比出现成倍变化,即使在升力不减条件下,升阻比较基准构型也可获得超过14%的提升.此外,还可导致乘波体相对压心系数出现明显偏移.     

LES study on the influence of the diffuser inlet angle of a centrifugal pump on pressure fluctuations

Large-Eddy Simulations are conducted on a centrifugal pump at design and reduced flow-rates for three diffuser geometries, to investigate the effect of changing the diffuser inlet angle on the overall performance and the pressure fields. In particular, pressure fluctuations are investigated, which affect the unsteady loads acting on the pump, as well as vibrations, noise and cavitation phenomena. The considered modification of the diffuser geometry is targeted at decreasing the incidence angle at the off-design flow-rate by rotating the stationary blades of the pump around their leading edge. Results are compared against those of an earlier study, where the same modification of the diffuser inlet angle was achieved by increasing also the radial gap between impeller and diffuser, whose blades were rotated relative to their mid camber location. The comparisons across cases demonstrate that the radial gap between the trailing edge of the impeller blades and the leading edge of the diffuser blades has a more profound influence on pressure fluctuations, compared to the angle of incidence on the diffuser blades of the flow coming from the impeller.     

Aerodynamic optimization of the flat-plate leading edge for experimental studies of laminar and transitional boundary layers

This work is concerned with the design of a leading edge for a flat-plate model used to study laminar and transitional boundary layers. For this study, the flow over the complete boundary-layer model, including leading edge, flat section, and trailing-edge flap, is modeled. The effect of important geometrical features of the leading edge on the resulting pressure distribution, starting from the well-known symmetric modified super ellipse, is investigated. A minimal pressure gradient on the measurement side of the plate is achieved using an asymmetrical configuration of modified super ellipses, with a thickness ratio of 7/24. An aerodynamic shape optimization is performed to obtain a novel leading edge shape that greatly reduces the length of the non-zero pressure gradient region and the adverse pressure gradient region compared to geometries defined by ellipses. Wind tunnel testing is used to validate the numerical solutions.     

Features of the turbulent flow around symmetric elongated bluff bodies

The flow fields around three elongated bluff bodies with the same chord-to-thickness ratios but distinct leading and trailing edge details were measured at a Reynolds number of 3×10⁴. These models each represent a case where: leading edge shedding dominates, trailing edge shedding dominates and a case where there is a balance between the two. The results show that the vortex street parameters vary between the models, and in particular, the shedding frequencies are significantly altered by the geometry. However, contrary to the current understanding for shorter bluff bodies, the scale of the recirculation region is found to be similar for each model, even though the shedding frequency changes within the range from 0.15 to 0.24. Also, the base pressure does not follow trends with shedding frequency expected from shorter bluff bodies. A force balance of the recirculation region shows that the near wake of each body is significantly affected by the Reynolds shear stress distribution and the resultant force due to the pressure field in the mean recirculation region. These differences infer that the distinct vortex formation characteristics depend on the state of the trailing edge shear layers. The boundary layers at the trailing edge have been quantified, as have the leading edge separation bubbles, and the marked differences in the wake details are shown to depend on the leading edge separation.     

Effects of varying Reynolds number, blowing ratio, and internal geometry on trailing edge cutback film cooling

Three-dimensional mean velocity and concentration fields have been measured for a water flow in a pressure side cutback trailing edge film cooling geometry consisting of rectangular film cooling slots separated by tapered lands. Three-component mean velocities were measured with conventional magnetic resonance velocimetry, while time-averaged concentration distributions were measured with a magnetic resonance concentration technique for flow at two Reynolds numbers (Re) differing by a factor of 2, three blowing ratios, and with and without an internal pin fin array in the coolant feed channel. The results show that the flows are essentially independent of Re for the regime tested in terms of the film cooling surface effectiveness, normalized velocity profiles, and normalized mean streamwise vorticity. Blowing ratio changes had a larger effect, with higher blowing ratios resulting in surface effectiveness improvements at downstream locations. The addition of a pin fin array within the slot feed channel made the spanwise distribution of coolant at the surface more uniform. Results are compared with transonic experiments in air at realistic density ratios described by Holloway et al. (2002a).     

Effects of notches on the surface pressure field downstream of a wall-mounted spoiler

Notched spoilers have been observed to be more effective than uniform spoilers to suppress the flow-induced cavity resonance of vehicles with open sunroofs. In this study, a few mechanisms possibly involved in buffeting suppression from notched spoilers were investigated experimentally and numerically. One objective was to investigate the spatial coherence and phase of the wall pressure fluctuations downstream of notched spoilers in comparison with the same quantities for uniform spoilers. Another objective was to gather detailed measured data to allow the verification of computer simulations of the flow over the notched spoiler. Experiments were performed to measure the velocity and wall pressure fields downstream of spoilers mounted on the rigid floor of a closed test section wind tunnel. Efforts were made to reproduce the spoiler and wind tunnel geometry and boundary conditions of the experimental setup in the numerical simulations. The numerical investigation used the Lattice Boltzmann Method (LBM), with the so-called Very Large Eddy Simulation (VLES) viscosity turbulence model. The results of the numerical investigation were in satisfactory agreement with measured data at low frequencies, where buffeting is expected to occur. The results suggested that the notches break down the homogeneity of the leading edge cross-stream vortices predominantly responsible for the cavity excitation. This decreased the cross-stream coherence of the surface pressure field, thereby reducing the magnitude of the net equivalent excitation force acting over the surface downstream.