叶片吸力侧反曲率设计对流道内激波强度影响的研究

现代航空燃气轮机负荷升高,流道内马赫数提高,激波损失增大,流动熵增增加,气动效率下降,能量损失增加.在大功率高负荷航空燃气轮机中,激波对气动性能影响更加明显.本文对某型航空发动机涡轮叶型进行了改型设计,分析了在不同出口马赫数条件下激波的结构,研究了通过控制激波强度以减小叶型损失的方法.研究发现,吸力侧带有反曲率弧段的叶型对于控制激波强度、减少能量损失作用明显.     

水蒸气跨音速流动中非平衡现象的数值模拟

研究了水蒸气跨音速流动过程中的非平衡相变及凝结冲波现象,揭示了气动激波与非平衡凝结流动之间相互作用的非定常流动规律。采用欧拉形式的控制方程求解两相凝结流动,建立了二维可压缩守恒型计算模型对水蒸气跨音速非平衡流动进行了数值模拟．捕获到了凝结冲波现象,揭示了凝结冲波的非平衡热力学机理,并探讨了尺度效应对两相非平衡流动的影响。研究了凝结冲波与气动激波之间的不同热力学特性和形成机理,并探讨了气动激波与非平衡凝结流动之间相互作用的非定常流动规律。     

湿蒸汽非均质高速凝结流动的数值研究

基于冠状成核机理,建立了湿蒸汽两相非均质凝结流动数值模型,对缩放喷管、汽轮机叶栅和汽轮机级内湿蒸汽两相非均质凝结流动进行了数值模拟．结果表明：与自发凝结相比,非均质凝结流动中杂质颗粒改变了凝结过程;杂质颗粒减小了喷管中凝结激波强度,改变了汽轮机叶栅中的压力分布,降低了蒸汽过冷度,减少了不平衡热力学损失;在汽轮机级内,非均质凝结流动的动、静叶进、出口汽流角接近过热蒸汽流动的动、静叶进、出口汽流角,其动叶前压力高于过热蒸汽的动叶前压力,但级反动度偏离过热蒸汽流动数值．     

超音速叶栅内激波与附面层相互作用的数值分析

通过对超音速透平叶栅流动进行详细的数值模拟,分析叶栅通道中激波与附面层的相互作用.通过对流道中静压、马赫数等参数的研究,综合分析压比和栅距的变化对叶栅中激波系、激波与附面层的相互作用的影响,并将部分模拟结果与实验数据进行了比较.     

叶片顶端跨音速叶型的气动性能分析与优化

应用流动计算分析软件CFX,对某大型汽轮机末级动叶顶部截面叶型的跨音速流动进行了数值模拟研究,分析叶栅中激波结构特征和流动损失机理.采用3阶Bezier曲线表达叶型中弧线,2阶与3阶Bezier曲线组合表达叶型厚度分布,结合Kriging代理模型优化叶型,改善气动性能.结果 表明:末级动叶顶部截面叶型气动损失主要与激波强度及其反射位置有关;叶型优化后,叶栅内激波强度减弱,相比原叶型,激波损失减少约32％,同时削弱了激波对边界层的影响,边界层损失降低约17％;优化叶型总压损失下降24％,气动性能明显提高.     

两相流超音速流动_激波及其应用研究

从两相流体的音速特点出发 ,研究两相超音速流动 ,分析超音速流动导致的激波状况 ,并利用两相激波加速凝结和增压的特点 ,设计了增压换热器。两相流的音速受其压缩性的影响而呈现出与单相流不同的特点 ,其较小的音速值使得两相超音速流动更易实现。两相流激波与波前马赫数密切相关 ,波后汽相凝结、压力升高 ,利用该特点设计的汽水直接接触式换热器 ,具有高效换热和增压的特点     

高亚音速大折转角叶型内激波结构与损失分析

本文采用组合多项式曲线构造了具有高亚音进口条件的大折转角压气机静叶叶型,探索了进一步提高跨音速压气机负荷时,静叶根部区域可能存在的激波结构和损失特征.采用数值模拟方法对不同条件下的高亚音速大折转角压气机叶栅流场进行了数值模拟,结果表明:叶栅内的激波结构与进口马赫数、攻角以及叶型的转角等参数密切相关.通过对叶栅出口的损失分析发现,激波与附面层相互作用改变了原有附面层内的损失分布规律,形成了由激波强度和位置所决定的沿叶片表面法线方向大小基本不变的高损失区域,叶型损失的大小和激波与吸力面最低压力点之间的相对位置密切相关.     

跨音速透平叶栅尾缘劈缝射流气动性能分析

基于定常RANS方程,采用Spalart-Allmaras(S-A)湍流模型,数值模拟某跨音速导叶尾缘劈缝射流的定常流动结构,分析尾缘劈缝射流对尾缘激波结构、尾迹流动特性及叶栅气动性能的影响。研究表明:开缝射流显著降低尾缘压力面侧燕尾波强度,并使激波在相邻叶片吸力面入射点向上游移动;当叶栅出口马赫数小于1.35时射流使吸力面燕尾波强度减弱,而达到1.35后射流使该侧激波强度增大;在不同出口马赫数下射流均能降低叶栅动能损失。     

Laval喷管内蒸汽凝结流动的数值研究

为了研究缩放喷管中湿蒸汽的自发凝结流动,对某Laval喷管中的几何参数及实验工况进行喷管中湿蒸汽凝结两相流动的三维数值模拟。通过以数值模拟结果结合部分工况的压力实验数据进行对比,讨论了喷管中蒸汽自发凝结流动的物理现象。     

受限通道中三维激波与侧壁面作用的数值模拟研究

为了了解超燃冲压发动机中三维斜激波与壁面的相交情况,以冷态模拟为基础,对两种不同形状的斜劈结构产生的斜激波进行数值模拟。当斜劈展向与气流方向成45.0°时,激波和膨胀波结构呈现三维特性,并且激波在两侧壁面处的反射现象不同。以激波面上游为视角,当激波与壁面相交成锐角时会产生马赫反射;而激波与壁面相交成钝角则会以叠加膨胀波的形式减弱激波,并且使激波面的法线方向与壁面的法线方向垂直。由于两侧壁面的影响,随着高度的增加激波强度减弱,同时气体经过斜激波后偏转角度也减小。对于构型Ⅱ,有斜劈的区域产生三维斜激波会延伸到无斜劈区域,此时下壁面与斜激波相交成钝角,同样会以叠加膨胀波的形式减弱斜激波。     

Numerical Investigation of Homogeneous Nucleation and Shock Effect in High-Speed Transonic Steam Flow

A two-dimensional compressible numerical model, in which the thermodynamic state and properties of steam were calculated by the Virial equation, was developed and used to predict the spontaneous condensation phenomenon with homogeneous nucleation in a series of Laval nozzles. The validation of the numerical results was accomplished with the experiment conducted by Moore and the results showed good agreement between numerical simulation and the experiment data. Based on the simulation, the nonequilibrium thermodynamic phenomenon, the condensation shock, and the aerodynamic shock were studied and the difference between the condensation shock and the aerodynamic shock was investigated. In addition, the influence of the aerodynamic shock on the nonequilibrium phase change was revealed.     

Numerical study and control method of interaction of nucleation and boundary layer separation in condensing flow

The spontaneous nucleation flow in turbine cascade was numerically studied. The model was implemented within a full Navier–Stokes viscous flow solution procedure and the process of condensation was calculated by the quadrature method of moments that shows good accuracy with very broad size distributions. Results were presented for viscous and inviscous flow, showing the influence of boundary layer separation and wake vortices on spontaneous nucleation. The results show that the degree of flow separation in wet steam flow is greater than that in superheated steam flow due to condensation shock and that the loss cannot be neglected. Furthermore, the impact of boundary layer separation and wake vortices on velocity profiles and its implications for profile loss were considered. The calculations showed that layer separation and wake vortices influence nucleation rate, leading to different droplet distributions. A method for controlling homogeneous nucleation and for reducing degree of flow separation in high-speed transonic wet steam flow was presented. The liquid phase parameter distribution is sensitive to the suction side profile of turbine cascade, which impacts the nucleation rate distribution leading to different droplet distributions and affects the degree of flow separation. The numerical study provides a practical design method for turbine blade to reduce wetness losses.     

Numerical study and control method of interaction of nucleation and boundary layer separation in condensing flow

The spontaneous nucleation flow in turbine cascade was numerically studied. The model was implemented within a full Navier-Stokes viscous flow solution procedure and the process of condensation was calculated by the quadrature method of moments that shows good accuracy with very broad size distributions. Results were presented for viscous and inviscous flow, showing the influence of boundary layer separation and wake vortices on spontaneous nucleation. The results show that the degree of flow separation in wet steam flow is greater than that in superheated steam flow due to condensation shock and that the loss cannot be neglected. Furthermore, the impact of boundary layer separation and wake vortices on velocity profiles and its implications for profile loss were considered. The calculations showed that layer separation and wake vortices influence nucleation rate, leading to different droplet distributions. A method for controlling homogeneous nucleation and for reducing degree of flow separation in high-speed transonic wet steam flow was presented. The liquid phase parameter distribution is sensitive to the suction side profile of turbine cascade, which impacts the nucleation rate distribution leading to different droplet distributions and affects the degree of flow separation. The numerical study provides a practical design method for turbine blade to reduce wetness losses.     

直接空冷汽轮机末级蒸汽异质／均质成核凝结过程的在线测量

采用新研制的改进型联合探针测量了某300 MW直接空冷机组低压汽轮机末级后部分区域变背压过程中的汽流参数,包括马赫数、攻角、偏转角、静压、流速和蒸汽湿度及水滴尺寸等参数.结果表明:空冷低压汽轮机末级在较高背压时并不处于湿蒸汽状态,随背压降低先出现异质成核凝结,而后才出现均质自发成核凝结.2种凝结状态之间存在着2种凝结机理共存的阶段,在此阶段凝结会出现很大波动.异质成核凝结产生的水滴尺寸大于均质自发成核凝结的水滴.     

Experimental and Numerical Investigation of Condensation Shock in Shock Tube

INTRODUCTIONThehomogeneousnucleationwithsubsequentspon-taneouscondensationofwater,pentanol,andethanolVaPorsinacarriergasareinvestigatedexperimen-tallyandtheoreticallyintheexpansionpartofashocktube.AswasshownbySislianandGlass(l976)forsupercriticalconditionsthecondensationshockwave(Cw)occurs.Thehomogeneousnucleationofwatervaporinacarriergaswasfirststudiedexperimentallyintheex-pansionpartofashocktubeusinglightscatteringbyBarschdorff(1975)andthenumericalsolutionwasaddedbySislianandGlaJss(1…     

Numerical investigation on wet steam non-equilibrium condensation flow in turbine cascade

Based on the two-phase wet steam flow with spontaneous condensation,experimental verification and flow analysis on nozzle and 2D cascade are carried out.The 3D Reynolds-Averaged gas-liquid two-phase flow control equation solver is explored with k ε k p turbulence model.Furthermore,3D flow numerical simulation on the last stage stator of the steam turbine is carried out.The results show that a sudden pressure rise on blade suction surface is mainly caused by the droplet growth in condensation flow.The more backward the condensation position is in cascade passage,the less the sudden pressure rise from condensation is,and the larger the nucleation rate is,the maximum under-cooling and the number of droplets per unit volume are.Interaction of condensation wave and shock wave has imposed greater influence on the parameters of the blade cascade outlet.     

AP1000设计基准事故试验热冲击过程数值模拟

针对AP1000核电厂安全级设备鉴定设计基准事故(DBA)模拟试验第1s热冲击过程,构建了过热蒸汽由储汽罐充入试验仓的模型.利用Fluent流体计算软件对瞬态热冲击过程进行了数值模拟,得到试验系统内气体温度、压力、流速、组分质量分数瞬态变化过程及其空间分布状态.结果表明:超音速蒸汽射流进入试验仓,经挡板减速并改变方向,与仓内空气混合,同时压缩空气,使仓内介质温度和压力快速上升并达到要求值;试验仓内瞬态压力分布均匀,但温度分布取决于蒸汽的流动,随着蒸汽不断充满试验仓,1s后仓内温度分布趋于均匀;储汽罐释放高温高压过热蒸汽充入试验仓的工艺可以满足DBA试验第1s热冲击试验要求.     

Shock wave of vapor-liquid two-phase flow

The shock wave of vapor-liquid two-phase flow in a pressure-gain steam injector is studied by building a mathematic model and making calculations. The results show that after the shock, the vapor is nearly completely condensed. The upstream Mach number and the volume ratio of vapor have a great effect on the shock. The pressure and Mach number of two-phase shock conform to the shock of ideal gas. The analysis of available energy shows that the shock is an irreversible process with entropy increase. __________ Translated from Nuclear Power Engineering, 2007, 28(4): 25–28 [译自: 核动力工程]