轴流压气机叶片优化设计

开发了基于梯度法的数值优化程序,并与三维粘性流场求解程序相结合对跨音压气机动叶片进行了以绝热效率最大为目标的三维气动优化设计。先对其进行了沿弦长方向掠设计,绝热效率可提高约0．65％。再对所得掠叶片进行叶型中弧线优化设计得到最终叶片,与初始叶片相比绝热效率提高达1．05％。优化结果表明,动叶片的单纯掠型叶片改进气动性能有限,而弦向掠与中弧线的联合优化设计可以显著改善叶片排内流动状况,并具有良好的变工况性能。     

跨音风扇转子弯掠结合的数值优化设计

为了研究弯掠结合对风扇气动性能的影响,采用基于雷诺平均N-S方程的全三维流场模拟程序和基于遗传算法的数值优化程序,对跨音风扇转子NASA Rotor67进行了优化设计.首先对所开发的三维N-S方程求解程序进行了实验验证,完善了遗传算法和响应面方法相结合的具有全局寻优能力的优化程序,以总压比最大为设计目标,应用该优化方法对NASA Rotor67进行弯掠两个自由度的气动优化设计.结果表明,弯掠联合的采用可以有效地改善流场内的流动状况,在质量流量和绝热效率严格满足约束条件的情况下,总压比提高了1个百分点;该优化方法是可行的.     

多级轴流透平通流三维气动优化研究

燃气轮机单机功率的增大使得透平级负荷不断增加,从而对通流部分的气动造型提出了更高的要求.采用包括弯叶片和非轴对称端壁的三维通流造型系统对某两级高压透平进行了优化设计研究.优化结果表明,使用弯叶片或非轴对称端壁造型,能够改善流道内部压力分布,抑制二次流的发展,提高透平效率,分别使透平整机绝热效率提高0.37％和0.17％;而同时采用二者进行联合优化时,整机绝热效率提高了0.48％.     

压气机分层优化气动设计体系研究

基于压气机分层次气动优化设计思想,结合了优化算法、CFD(计算流体力学)技术与压气机气动设计程序,利用商业软件,建立了压气机气动优化设计平台,将气动优化设计思想融入到了压气机气动设计多个阶段,以实现压气机气动设计使性能最优化的目的.应用商业通用优化平台进行了轴流压气机一维、S2反问题气动优化设计,并采用NUMECA提供的全三维优化设计平台对压气机进行了全三维气动优化设计.计算结果表明:分层气动优化设计是提高压气机气动性能的有效手段,先进的优化算法在气动设计的各阶段都能够比传统设计手段更大限度地实现压气机性能的最优化.     

可控曲率技术在某高负荷轴流风扇气动优化设计中的应用

针对高负荷跨音速风扇级内部强逆压力梯度、强黏性剪切与可压缩跨音速流动特征,基于通道几何曲率控制技术开展高负荷跨音速风扇级的气动优化设计。通过合理调整通道几何曲率分布规律,在设计条件下,获得了一个高负荷风扇级气动新结构。结果表明:优化后的高负荷风扇级总压比达到2.490,绝热效率大于87%,质量流量达到25.8 kg/s,具备了较宽的高效率工作范围;叶片通道几何曲率从动力学层面上对通道附面层乃至主流具有重要的导流以及整流效果。     

整机环境下的风扇_增压级叶片气动优化

采用自主研发的三维粘性气动优化设计平台对某双涵道风扇/增压级进行了气动设计优化;采用NURBS技术对该风扇/增压级各排叶片进行了参数化造型,包括二维叶型的参数化表达以及基选线的弯、扭联合造型;采用NUMECA商用软件进行了风扇/增压级三维内外涵联算作为气动性能评估指标;基于该风扇/增压级三维内外涵联算,采用iSIGHT优化软件对风扇/增压级各排叶片进行了气动优化设计.在整机流量降低0.342 8%的情况下,内涵增压级效率提高了1.43%;对风扇优化,在整机流量基本不变的情况下,整机效率提高了1.566%,并扩大了增压级的稳定工作范围.     

基于复合进化算法和Navier-Stokes方程求解技术的透平叶栅气动优化设计

提出了基于复合进化算法和Navier-Stokes方程求解技术的透平叶栅气动设计方法。复合遗传算法是结合进化算法与单纯形法,通过对群体中的最差个体采用单纯形法进行改造,提高进化遗传算法的搜索效率。透平叶栅的气动优化设计目标是总压损失最小。总压损失的计算采用Reynolds平均Nayier-Stokes方程求解技术,紊流模型采用Baldwin-Lomax代数紊流模型。优化设计变量是叶栅型线参数化Bezier曲线控制点坐标,优化设计得到叶栅的总压损失减小了20％。设计结果证明了本文所提出的优化技术对透平叶栅气动设计是一种有效的方法。     

蒸汽透平高压级扭叶片的气动优化设计

提出了一种实现截面局部扭转、控制喉部面积的扭叶片参数化造型方法.用控制喉部面积替代流量约束,对某蒸汽透平高压级动叶进行了气动优化设计;另一方面以流量差异和气动效率为目标函数,采用非支配排序遗传算法(NSGA-II)进行了多目标并行优化设计.两种方法的结果吻合较好.结果表明,本文的优化方法是有效的,扭积叠造型有助于提高蒸汽透平高压级的气动效率.     

透平叶片的气动优化设计系统

发展了一个叶轮机械叶片全三维粘性杂交问题的气动优化设计系统。该系统包括分析技术与组合优化技术的耦合：前者基于高精度、鲁棒型的数值分析方法，已成功地用于蒸汽透平叶片的流动分析．并经详细考核已将其纳入到了实际的叶片气动设计体系；后者基于优秀的iSIGHT商用优化平台．通过对多种优化方法的集成从而发展了组合的叶片全三维气动优化策略。数值结果与试验数据的比较表明了这一气动优化设计系统真正纳入到工业设计体系是完全可能的。     

定桨距风力机气动优化设计优化方向分析

简述风力气动优化设计的模型和方法，分析定桨距风力机桨叶外形变化对气动性能的影响，指出气动优化设计应考虑的优化目标和主要参数，并根据该方法对２００ｋＷ定桨距风力机进行了气动优化设计，给出优化结果并加以分析比较。     

基于数值优化的跨音速压气机动叶三维设计

实验验证了三维粘性流场求解程序,然后采用基于梯度法的数值优化程序对跨音压气机动叶积叠线进行优化设计,得到了弯掠结合的三维叶片,并对其进行了数值模拟及详细的流场分析.结果表明采用弯掠的三维动叶可以有效的改变叶片排内三维激波结构,降低尾迹损失,显著提高动叶的整体绝热效率,并使动叶具有更加良好的变工况性能.     

跨声速压气机转子前缘积叠线的数值优化设计

采用数值优化方法对跨声速压气机转子NASA rotor37前缘积叠线进行了数值优化设计.本优化设计以绝热效率为目标函数,总压比与质量流量为约束条件,进行单目标有约束的优化设计.详细地分析对比了几何形状、总体性能及流场的变化.结果表明,叶片后掠并且加入弯曲,其激波的波形变得倾斜.在中部,强度有所削弱;在底部区域,激波有所后掠.同时指出,单一工况点的设计对变工况性能的控制能力不足.     

Aerodynamic sweeping study and design for transonic compressor rotor blades

<正>The objective of the present paper is to study the sweep effect on the blade design performance of a transonic compressor rotor.The baseline to be modified and swept is a designed well efficient transonic single rotor compressor. The first part of the present study is concerning the sweep effect with straight leading edge.In this case fixing the hub section the swept blade is formed by tilting the leading edge with whole blade forwards and backwards axially.The second part is to use an optimization strategy with simple gradient-based optimum-searching method and multi-section blade parameterization technique to search and generate an optimal swept rotor with curved arbitrary leading edge.Its adiabatic efficiency is a little bit greater than that of the reference un-swept rotor.     

Blade parameterization and aerodynamic design optimization for a 3D transonic compressor rotor

The present paper describes an optimization methodology for aerodynamic design of turbomachinery combinedwith a rapid 3D blade and grid generator(RAPID3DGRID),a N.S.solver,a blade parameterization method(BPM),a gradient-based parameterization-analyzing method(GPAM),a response surface method(RSM)withzooming algorithm and a simple gradient method.By the use of blade parameterization method a transonic com-pressor rotor can be expressed by a set of polynomials,and then it enables us to transform coordinate-expressedblade data to parameter-expressed and then to reduce the number of parameters.With changing any one of theparameters and by applying grid generator and N.S.solver,we can obtain several groups of samples.Here onlyten parameters were considered to search an optimized compressor rotor.As a result of optimization,the adiabaticefficiency was increased by 1.73%.     

A Study of 3D Aerodynamic Design for a Transonic Compressor Blading Optimized by the Locations of Aerofoil Maximum Thickness and Maximum Camber

A design procedure for improving the efficiency of a transonic compressor blading was proposed based on a rapid generation method for three-dimensional blade configuration and computational meshes, a three-dimensional Navier-Stokes solver and an optimization approach. The objective of the present paper is to design a transonic compressor blading optimized only by selection of the locations of maximum camber and maximum thickness for the airfoils at different span heights and to study how do these two design parameters affect the blade performance. The blading configuration and the computational meshes can be obtained very rapidly for any given combination of maximum camber and maximum thickness. The computational grid system generated is used for the Navier-Stokes solution to predict adiabatic efficiency, total pressure ratio and flow rate. As a main result of the optimization, adiabatic efficiency was successfully improved.     

Development and analysis of novel six-lobe helical rotors for hydrogen fuel cell vehicle roots blowers

This paper suggests a novel six-lobe Roots profile to improve the performance of Roots blowers in hydrogen fuel cell vehicles. Mathematical models for rotor profile generation and geometric characteristics are established. A working process simulation model for Roots blowers is developed based on the lumped parameter method and is verified by experimental results. The key profile parameters are discussed and optimized in views of geometric and thermodynamic performance. Case studies are conducted to reveal the detailed performance map difference between several design cases. Results show that a trade-off exists between the rotor cavity volume and adiabatic indicated efficiency for Roots blowers. The proposed profile broadens the design space of rotors in tooth height and achieves a flexible adjustment for the leakage through the blow-hole and contact line. As a consequence, compared to conventional Roots profiles, the proposed rotor profile achieves higher adiabatic indicated efficiency under the same rotor cavity volume.     

向心式通风机级的数值模拟及变工况特性研究

以完全气体作为流动工质,设计了单级向心式通风机,并进行了流场模拟和变工况特性研究。首先采用BladeGen构造动叶叶型,并对动叶叶型进行参数化;然后采用数值模拟方法得到流场参数,以级效率为目标函数,以总压比为约束条件,在Workbench平台上对动叶叶型参数进行优化,得到最佳的动叶叶型;在已设计好的动叶基础上,利用单圆弧构造法设计静叶并设置在动叶后面,得到向心式通风机级;最后分析不同流量,不同转速下所设计的向心式通风机级的变工况特性。     

Development of an axial-type fan with an optimization method

An axial-type fan that operates at a relative total pressure of 671Pa and a static pressure of 560Pa with a flowrate of 416.6m³/min is developed using an optimization technique based on the gradient method. Prior to the optimization of the fan blade, a three-dimensional axial-type fan blade is designed based on the free-vortex method along the radial direction. Twelve design variables are applied to the optimization of the rotor blade, and one design variable is selected for optimizing a stator which is located behind the rotor to support a fan-driving motor. The total and static pressure are applied to the restriction condition with the operating flowrate on the design point, and the efficiency is chosen as the response variable to be maximized. Through these procedures, an initial axial-fan blade designed by the free vortex method is modified to increase the efficiency with a satisfactory operating condition. The optimized fan is tested and compared with the performance obtained with the same class fan to figure out the optimization effect. The test results show that the optimized fan not only satisfies the restriction conditions but also operates at the same efficiency even though the tip clearance of the optimized fan is greater than 30%. The experimental and numerical tests show that this optimization method can improve the efficiency and operating pressures on axial-type fans.     

高负荷跨音速压气机转子气动设计及附面层抽吸研究

本文设计了一跨音速压气机转子,其叶尖切线速度420 m/s,在确保动叶出口参数的同时,压比达到3.2,绝热等熵效率88.7%。数值模拟表明,60%叶高到叶顶区域,气体分离严重。为了有效控制分离,本文初步探讨了抽吸附面层对转子性能的影响。结果表明抽气能明显影响附面层的发展与激波的空间结构,转子局部性能得到改善。