基于神经网络& NURBS技术的叶片优化设计研究

应用流行的神经网络技术与先进的几何描述方法NURBS技术,对某两级风扇进行优化改型设计,特别针对于转子2的根部截面进行优化,通过对优化前后的转子2以及两级风扇的流场气动结构与特性的对比分析表明,该优化设计方法确实可行,具有一定的先进性,能够改善叶轮机械的整体气动特性,可以为叶轮机械的优化设计提供一种新的途径.     

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.     

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。     

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.     

采用NURBS的某级透平叶片全三维气动最优化设计

用NURBS对叶轮机械叶片三维型面和基迭线进行参数化表达,实现了对叶片三维型面和基迭线弯、倾、掠、扭的变形控制.该方法为叶片的自动优化设计提供设计变量.把该方法构建的叶片全三维控制模块集成到基于商业软件iSIGHT的叶片粘性气动优化设计平台中,在该平台上选择优化算法对某级透平叶片进行了全三维气动优化设计实验,优化的目标是使级效率尽可能的高,同时流量不能降低并且动叶叶根前端的温度尽可能低.实验结果表明：优化后的叶型性能有所改善,同时也满足了流量和温度约束条件的要求.图23参5     

单级离心压气机气动性能预测与优化设计

为了提升低转速工况下压气机的气动性能,采用人工神经网络与遗传算法相结合的优化方法对某单级离心压气机离心叶轮的弯特性进行优化计算。利用NUMECA软件对该离心压气机进行了不同转速的数值模拟,得到压气机不同工况下的气动性能。通过设置不同控制参数和曲线形式对离心叶轮叶片进行参数化拟合,以8个改变叶片弯特性的参数为自由参数进行了叶型优化设计,最终得到了优化后的叶轮叶片。结果表明:优化后在低转速的设计工况下离心压气机压比增加了4.69%,稳定裕度拓宽了17.41%。     

基于叶片弯掠技术的优化设计

在三维粘性流场的数值计算程序平台上,利用BP神经网络和遗传算法,通过叶片弯掠技术对一轴流风机的转子叶片的周向弯曲角度进行寻优,以使风扇的气动性能进一步提高。通过对比优化前、后的叶轮发现,优化之后的叶片呈现明显的周向前弯曲特征。测试结果显示,其全压和气动效率分别提高了3.56%和1.27%,失速裕度大幅度拓宽36%以上,上、下端部的损失进一步降低。     

突变偏心距激励下两级离心泵转子系统动力学分析

为分析两级离心泵叶轮偏心距激励突变时转子系统产生振动和冲击的机理,改进了将质量集中于叶轮的方法并建立了悬臂式两级离心泵转子系统动力学方程,得到了2个叶轮在不同方向振动量的无量纲化解析式,提出了无量纲化的偏心距效应系数,以判别不同叶轮偏心距激励突变对整个转子系统振动的影响,最后对叶轮偏心距激励突变时其弯曲振动特性和几何中...     

汽轮机调节级喷嘴组气动优化设计

采用叶轮机械优化设计平台FINE/Design3D对调节级喷嘴组汽道进行全三维气动性能优化设计,在保证工作点不发生偏离的前提下,提高其等熵效率。经过分析,优化后喷嘴组叶片由于采用加载叶型,有效的抑制叶片表面的附面层厚度,降低叶型损失;喷嘴组外端壁型线更加平缓,端壁损失和二次流损失得到了有效地抑制。额定工况下,调节级等熵效率提高了1.8%,并且在其它工况下调节级气动性能都有明显提高。     

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。     

Reconstruction method for running shape of rotor blade considering nonlinear stiffness and loads

The aerodynamic and centrifugal loads acting on the rotating blade make the blade configuration deformed comparing to its shape at rest. Accurate prediction of the running blade configuration plays a significant role in examining and analyzing turbomachinery performance. Considering nonlinear stiffness and loads, a reconstruction method is presented to address transformation of a rotating blade from cold to hot state. When calculating blade deformations, the blade stiffness and load conditions are updated simultaneously as blade shape varies. The reconstruction procedure is iterated till a converged hot blade shape is obtained. This method has been employed to determine the operating blade shapes of a test rotor blade and the Stage 37 rotor blade. The calculated results are compared with the experiments. The results show that the proposed method used for blade operating shape prediction is effective. The studies also show that this method can improve precision of finite element analysis and aerodynamic performance analysis.     

Study on Aerodynamic Design Optimization of Turbomachinery Blades

This paper describes the study on aerodynamics design optimization of turbomachinery blading developed by the authors at the Institute of Engineering Thermophysics, Chinese Academy of Sciences, during the recent few years. The present paper describes the aspects mainly on how to use a rapid approach of profiling a 3D blading and of grid generation for computation, a fast and accurate viscous computation method and an appropriate optimization methodology including a blade parameterization algorithm to optimize turbomachinery blading aerodynamically. Any blade configuration can be expressed by three curves, they are the camber lines, the thickness distributions and the radial stacking line, and then the blade geometry can be easily parameterized by a number of parameters with three polynomials. A gradient-based parameterization analytical method and a response surface method were applied herein for blade optimization. It was found that the optimization process provides reliable design for turbomachinery with reasonable computing time.     

轴流透平机械通流部分泄漏流动及控制技术研究进展

综述了轴流透平机械通流部分泄漏流动及控制技术的研究进展,首先详细介绍了轴流透平机械特别是汽轮机通流部分的泄漏流动特性及其对通流效率的影响,接着介绍了透平机械动叶顶部间隙泄漏流动特性及其对透平级气动性能的影响的研究,讨论了考虑间隙泄漏流动对某四级工业汽轮机气动性能的影响,研究了某汽轮机高压缸平衡孔对透平级气动性能的影响及其作用机制。论文简介了透平机械流动控制技术及其研究进展,最后给出了对透平机械泄漏流动及控制技术的研究展望。     

Design of high-efficiency turbomachinery blades for energy conversion devices with the three-dimensional prescribed surface curvature distribution blade design (CIRCLE) method

The purpose of this paper is to present the advantages of the direct presCrIbed suRface Curvature distribution bLade dEsign (CIRCLE) method for the design of high-efficiency turbomachinery blades. These advantages are illustrated by redesigning several examples of axial turbomachinery blades of interest to energy conversion devices, and discussing in detail the aerodynamic performance and efficiency improvements of the redesigned blades over the original geometries. The two-dimensional (2D) method, originally proposed for turbine blades, has been extended for use with 2D and three-dimensional (3D) turbine, compressor and fan blades, and isolated airfoils. By specification, the method allows joining line segments between the leading edge (LE) and trailing edge (TE) circles or ellipses so that the streamwise distribution of surface curvature and slope of curvature are continuous everywhere from the LE stagnation point to the TE stagnation point. The form of the line segments to prevent the “wiggles” of higher order lines is presented. Also by specification, the CIRCLE method can be integrated with multi-objective heuristic or evolutionary-algorithm optimization methods. The efficacy of the method is examined by: redesigning two 2D turbine blades, one 2D compressor blade, and one 2D isolated airfoil; and by designing one 3D compressor blade row and one 3D turbine blade row. The aerodynamic performance improvements between the original and the sample redesigned blades are discussed in detail, resulting in higher-efficiency blades than the original geometries. Further extension of the method for centrifugal and mixed-flow impeller geometries is a coordinate transformation. It is concluded that the CIRCLE method is a new design environment enabling the original design (or redesign) of high-efficiency 2D and 3D turbomachine blades, with direct applications in a variety of energy conversion devices.     

Adjoint-Based Geometrically Constrained Aerodynamic Optimization of a Transonic Compressor Stage

Efficient method to handle the geometric constraints in the optimization of turbomachinery blade profile is required. Without constraints on the blade thickness, optimal designs typically yield thinner blade to reduce the friction loss, however, at the risk of degraded strength and stiffness. This issue is seldom discussed and existing literature always treat the blade thickness constraint in an indirect manner. In this work, two different geometric constraints on the blade thickness are proposed and applied in the adjoint optimization: one is on the maximum blade thickness and the other is on the blade area. Methods to compute sensitivities of both constraints are proposed and they are integrated into an optimization system based on a finite volume code and a solver for the discrete adjoint equation. Adjoint optimization is conducted to minimize the entropy production in a transonic compressor stage. Results for the adjoint optimization without geometry constraint and two comparative cases are detailed. It is indicated that three cases yield similar performance improvement; however, if geometry constraints are properly handled, the optimal designs have almost the same maximum thickness as the original design, compared to a thinner blade profile with 14% reduction of maximum thickness in the case without geometry constraint. The cases considering geometry constraints also consume slightly reduced Central Processing Unit(CPU) cost. Result of this work verifies the effectiveness of the proposed method to treat geometric constraints in adjoint optimization.     

三维低雷诺数叶片参数化方法研究

叶片参数化是叶轮机械气动优化过程中十分重要的一个环节,它决定着叶片的气动优化空间。传统叶片是通过叶片几何或特征来实现参数化,很少利用气动参数来实现。为了解决该问题,提出一种基于气动参数的三维叶片参数化方法,该方法通过经验公式将气动参数引入叶片参数化过程,并利用几个重要截面中的两条重要特征曲线（中弧线和厚度分布曲线）实现叶片重构。通过对实际叶片进行参数化可以发现：参数化后叶片与原始叶片之间的几何相对误差最大不超过0.01;两者表面压力系数变化趋势基本一致。因此,该方法不仅能够准确描述三维叶片形状,还将气动参数直接设置为优化控制变量,从而有利于优化效率的提高。     

叶轮机械叶片节能新技术

本文研究了增加叶轮机械叶片气动效率的新机理,也是一种新的节能技术,即在叶片某部位增加局部粗糙度可以增加叶片的升阻比,从而提高叶片的气动效率。在叶栅叶片、风机叶片和风力透平叶片进行的多种试验均证实了这一点。本文还地此机理进行了研究,证明由于特定部位的局部粗糙度增加而引起的局部湍流度加大可以起到增加升阻比、提高气动效率的效果。这种技术可以不改动叶轮机叶片的设计,面较方便地达到节能增效的目的。     

叶片可靠性预测的非线性振荡低网格边界元法

为了预测叶轮机械叶片的流体激振可靠性,基于非线性流体激振理论,建立流体结构耦合分析的边界积分方程直接求解格式,采用等效均值和离差的线性化处理来估算可靠度指标,提出了叶片可靠性分析的非线性振荡低网格边界元法。数值计算结果显示,该方法能快速、有效地预测叶片结构的工作性能,可应用于新型叶轮机械的优化概率设计。     

Straight-leaned blade aerodynamics of a turbine nozzle blade row with low span-diameter ratio

Compound-leaned blades have been applied for the design of turbomachinery for reducing secondary flow losses and then improving the aerodynamic performance. The aerodynamics features are not clear enough so far and, therefore, have been investigated by many authors experimentally and numerically. The present study on turbomachinery aerodynamics is emphasized on the leaning effects of straight-leaned turbine nozzle blades with low span-diameter ratio (less than 0.1). This kind of blades has relatively low efficiency. This is due to that the blades are too short and then the loss contours of both tip and hub surfaces are merged with each other. How to increase the efficiency becomes one of the important subjects, which is faced to the turbomachinery community. Effects of straight-leaned blades in a turbine nozzle blade row with low span-diameter ratio have been assessed using three-dimensional steady Reynolds-averaged Navier-Stokes computations.     

汽轮机叶片枞树型叶根轮缘优化研究

叶片是汽轮机中重要的零部件之一,其可靠性直接关系到整个机组的安全运行。因此,通过改进叶片结构来弥补材料强度方面的不足,减少叶片事故,进而提高整个机组的安全性是非常必要的。对汽轮机叶片枞树型叶根轮缘完成了多变量优化分析工作,基于APDL编程语言对枞树型叶根轮缘进行了多参数建模,通过求解7个特征变量的优化值,以达到叶根轮缘最大、等效应力最小的目的;并对具体的叶片分别采用零阶算法结合一阶算法、智能优化算法(遗传算法、粒子群算法、模拟退火算法)及模式搜索等方法进行了优化。分析结果表明,在综合考虑精度及优化时间的情况下,模式搜索算法是解决本问题的最佳方法。研究结果可以为汽轮机叶片叶根轮缘部分的设计提供理论支持,并在一定程度上提高透平机组的运行可靠性。