跨声速压气机转子叶顶区域流场非定常计算和POD分析

采用时间精确求解法对跨声速轴流式压气机转子NASA Rotor35单流道进行了三维非定常数值模拟,研究了叶顶区域流场的时间非定常波动特性。将叶顶区域流场的非定常解作为快照,采用本征正交分解(POD)方法提取POD模态,进一步分析了叶顶近失速点流场的流动特性。结果表明:在近峰值效率点的大质量流量工况下,叶顶区域流场呈现出稳定性,基本不发生随时间波动的特性;在近失速点的小质量流量工况下,叶顶区域流场呈现周期性的波动特性,由激波与叶顶间隙泄漏涡形成的破碎、通道中部未形成泄漏涡的相邻叶片泄漏流流线以及来流一起形成的叶顶二次涡是叶顶非定常周期性波动形成的必要条件。     

间隙变化对轴流压气机转子近失速工况叶顶流场的影响研究

为研究间隙变化对轴流压气机转子近失速工况下叶顶流场结构的影响,以轴流压气机转子Rotor37为研究对象,对其叶顶流场进行定常和非定常的数值模拟。计算结果表明：随着叶顶间隙的减小,压气机的总压比和等熵效率均有所提高,稳定运行范围扩大;2倍设计间隙下,叶尖泄漏涡经激波作用后发生膨胀破碎,堵塞来流通道,诱发压气机堵塞失速;0.5倍设计间隙下,吸力面流动分离加剧,发生回流,部分回流与来流在压力面前缘上游发生干涉,进口堵塞加剧,致使部分来流从前缘溢出,导致压气机叶尖失速;不同间隙下压气机失速过程的主导因素不同,大间隙下失速由叶尖泄漏涡破碎的非定常波动引起,小间隙下失速主要由流动分离引发的周期性前缘溢流所主导。     

汽轮机叶顶间隙内非定常流动的数值分析

为了分析叶顶间隙泄漏涡的影响范围、运行轨迹和强度的变化规律,以某汽轮机高压级为研究对象,采用SSTκ-ω湍流模型,应用PISO算法对叶项间隙内的非定常流动进行了数值模拟．结果表明：叶顶间隙泄漏流是有规律的周期性的非定常流动,泄漏涡的影响范围、运行轨迹和强度随时间和叶顶间隙的变化而变化;泄漏流对主流的影响呈现出从弱到强、再从强到弱的周期性变化规律;叶顶间隙泄漏涡在丁／4时刻的强度和影响范围均达到最大,在T／2时刻,静叶脱落涡和动叶吸力面前部的泄漏涡混合形成新的涡系,而动叶吸力面后部的泄漏涡却与其边界层的脱涡混合,离开吸力面．     

叶尖自发射流条件下涡轮非定常流动的数值模拟

为分析自发射流条件下非定常尾迹对叶顶间隙流动、S1流面和S2流面上流场参数、叶尖泄漏比和动叶载荷变化的影响,采用数值模拟方法,以Durham叶栅为原型,将动、静叶栅流场通过滑移网格技术耦合,开展非定常计算。结果表明:在静叶非定常尾迹的影响下,转子区域流场内的流动、叶尖间隙泄漏比及叶片周向载荷均呈现出周期性变化的特征;考虑非定常效应和端壁相对运动效应,相较于无叶尖射流,单孔叶尖自发射流可使泄漏比降低4.57%,比定常计算预测的泄漏比低3.43%,表明要想准确获得叶尖射流条件下的叶栅流动特性和叶尖泄漏抑制效果,其间的非定常效应不可忽略。     

基于动力学模态分解法的轴流压气机叶顶非定常流动分析

对跨声速轴流压气机转子进行非定常数值模拟,采用动力学模态分解法对叶顶区域的非定常流动进行模态分析,进一步认识叶顶区域流场的非定常流动机理.研究发现:动力学模态分解法捕捉到叶顶区域非定常流场的特征频率6.83kHz,对应模态是形成叶顶区域流场非定常波动的主要模态.各阶模态中低阶模态结构主要集中在叶片前缘,表征大尺度的压力...     

端壁相对运动对压气机叶栅间隙流场影响的数值模拟

压气机端壁与叶片间的相对运动是影响叶顶间隙气流流动的重要因素.采用数值模拟的方法考察了端壁运动对不同叶顶间隙压气机叶栅内三维流场的影响.结果表明:端壁相对运动改变了叶栅间隙流场结构,叶栅通道内出现向相邻叶片压力面运动的刮削泄漏涡,上通道涡及叶顶分离涡受到抑制,叶尖负荷增大,间隙泄漏流量增加,叶栅总损失由于叶顶区掺混损失减少而减少.     

汽轮机动叶顶部间隙泄漏流动特性的数值模拟

以一个小展弦比轴流透平级为研究对象,采用数值方法对不同动叶顶部间隙情况下的间隙泄漏流动进行了分析,研究了间隙流和间隙涡的形成、发展及其对透平级性能的影响.以三维流线和极限流线为手段,分析了6种间隙尺寸下动叶顶部的泄漏流和泄漏涡造成的损失及其与主流掺混的过程.结果表明:动叶顶部间隙两侧压力面和吸力面之间的压力差使汽流从压力面被吸入间隙,跨过叶顶,进入相邻叶栅通道的吸力面,导致泄漏流动;与无间隙的情况相比,叶顶间隙的存在使上端壁处的流场发生明显变化,引起损失迅速增长;随着间隙的增大,泄漏涡的产生位置提前,强度增大,从而导致更大的流动损失.     

带有自发射流的涡轮叶顶间隙流场PIV测量

为了探究叶尖射流对涡轮叶栅流场特性的影响,搭建了一个小尺度低速叶栅风洞实验台,利用粒子成像测速(PIV)技术对带有自发射流的涡轮叶顶间隙流场进行了直接测量,获得了低雷诺数(Re=6.46×103~3.23×104)下射流孔附近的流动图像及速度测量结果,展示了叶顶间隙内层流和紊流2种流态下自发射流与泄漏流的相互作用过程,揭示了低雷诺数工况下(涵盖层流到紊流的转捩)叶尖射流抑制泄漏流的作用机理及影响因素,并对叶尖射流尾迹中出现的类卡门涡街的涡分布现象进行了探讨.结果表明:叶尖射流的引入在泄漏流抑制方面取得一定收益,但同时也进一步加剧了叶顶间隙流动的复杂性.     

多变气热参数下大尺度槽深叶顶的流动换热特性

为了研究具有渐缩型面凹槽在不同深度下叶顶间隙的流动换热特性,针对某一级高压涡轮,在发动机五种典型工况下通过改变其凹槽深度,采用k-ω湍流模型以及自适应湍流模拟方法(SATES)分别进行定常和非定常的数值仿真分析。研究结果表明,凹槽深度是影响间隙泄漏流动和叶顶换热特性的重要因素,同时该影响趋势也受涡轮工作状态的限制。相比于深凹槽,浅凹槽方案的间隙泄漏量明显降低,对应的涡轮动叶出口总压损失系数也有所降低,这在涡轮小流量状态时尤为明显。然而,深凹槽设计在降低叶顶热负荷方面表现更好,其中槽深0.8H方案比槽深0.1H方案的叶顶平均努塞尔数降低38.3%～95.3%。定常和非定常两种计算方法主要影响了间隙内局部泄漏量和叶顶前部热负荷的预测值,并未改变流动换热特性的分布趋势。     

机匣处理对子午加速轴流风机扩稳的机理研究

为揭示叶顶间隙泄漏流动的演变趋势以及前置凸台机匣处理对风机的扩稳机理,采用CFD方法对风机内部流场进行了数值计算,获得了叶顶间隙泄漏流与风机非稳定工作状态的关联及前置凸台机匣处理通过控制主流和叶顶泄漏流,提高风机稳定工作范围的机理。结果表明:随着流量的减小,叶顶间隙泄漏流与主流的交界面不断向上游移动,叶顶间隙泄漏流在叶顶通道内造成的流动堵塞不断扩大,最终导致该风机进入非稳定状态;在小流量时前置凸台机匣处理通过对主流阻挡使部分叶顶泄漏流绕过叶片前缘在相邻流道内往下游流动,减小下游的阻塞区域,从而对风机内部的流动起到一定的稳定作用。     

Unsteady tip clearance flow in an isolated axial compressor rotor

Introduction Background It is well known that the rotor tip clearance flow has profound effects on the performance and stability of axial compressor (Wisler[1], Howard[2]). Numerous studies on the tip clearance flow were carried out in the past fifty years. Rain[3] proposed a model to predict the loss due to tip leakage flow assuming that the kinetic energy of the leakage flow velocity component normal to the mean chamber line would be dissipated. Lakshminarayana[4] developed a model to pre…     

Stereoscopic PIV measurements of the flow field in a turbine cascade

This paper presents experimental measurements of the flow field in a Low-speed Turbine Cascade using a stereoscopic particle-image velocimetry(SPIV). During the measurements, a pair of frame-straddling-based CCD cameras were configured at different sides of the laser light sheet, and appropriate tracing particles(DEHS) were employed. The measurements were conducted at the incidence angle of 0 degree and exit Reynolds number of 1.7 × 105 with the tip clearance 1.18% of blade chord. The tip flow features, such as the evolution and breakdown of tip leakage vortex, the horseshoe vortex, turbulence characteristics of tip leakage flow, were studied for the flow field analysis. The results showed that the tip leakage flow/vortex mainly dominate flow fields in the tip region. The tip leakage vortex performs as a concentrated vortex before its breaking down and splitting into small vortices. The highest turbulence intensity mainly occurs in the tip region along with the trajectory of tip leakage vortex, and when the vortex breaks down, the turbulence intensity reduces rapidly. Additionally, the SPIV with this configuration also shows an advantage in investigating the flow structures and mechanism inside the turbine cascade.     

Experimental Investigation of Aerodynamic Performance due to Blade Tip Clearance in a Gas Turbine Rotor Cascade

This study examines how the complex flow structure within a gas turbine rotor affects aerodynamic loss. An unshrouded linear turbine cascade was built, and velocity and pressure fields were measured using a 5-hole probe. In order to elucidate the effect of tip clearance, the overall aerodynamic loss was evaluated by varying the tip clearance and examining the total pressure field for each case. The tip clearance was varied from 0% to 4.2% of blade span and the chord length based Reynolds number was fixed at 2×10⁵. For the case without tip clearance, a wake downstream of the blade trailing edge is observed, along with hub and tip passage vortices. These flow structures result in profile loss at the center of the blade span, and passage vortex related losses towards the hub and tip. As the tip clearance increases, a tip leakage vortex is formed, and it becomes stronger and eventually alters the tip passage vortex. Because of the interference of the secondary tip leakage flow with the main flow, the streamwise velocity decreases while the total pressure loss increases significantly by tenfold in the last 30% blade span region towards the tip for the 4.2% tip clearance case. It was additionally observed that the overall aerodynamic loss increases linearly with tip clearance.     

1,5级变几何涡轮非定常流动特性研究

可转导叶由于端部间隙和转轴的存在,会产生复杂的二次流动。本文对LISA涡轮进行变几何改型,采用几何约化法对该1.5级变几何涡轮进行数值模拟,详细探究了可转导叶间隙高度对可转导叶（S1）涡系的流动细节和载荷的影响,并深入研究其非定常流动对下游叶排的干涉及二次流输运过程的影响。计算结果表明：泄漏涡（LV）、角涡（CV）和通道涡（PV）共同组成了可转导叶的涡系;可转导叶端部间隙高度影响流动损失和级效率大小,设计间隙下该变几何涡轮S1时均总压损失系数Y为10.32%,涡轮时均总总效率ηtt为82.26%;可转导叶的尾缘泄漏涡使第1级动叶（R1）流动产生强非定常性;可转导叶的尾缘泄漏涡和R1泄漏涡、壁面涡是造成第2级静叶（S2）流动非定常性的主要因素。     

Numerical investigation of the unsteady tip leakage flow and rotating stall inception in a transonic compressor

<正>It is well known that tip leakage flow has a strong effect on the compressor performance and stability. This paper reports on a numerical investigation of detailed flow structures in an isolated transonic compressor rotor-NASA Rotor 37 at near stall and stalled conditions aimed at improving understanding of changes in 3D tip leakage flow structures with rotating stall inception.Steady and unsteady 3D Navier-Stokes analyses were conducted to investigate flow structures in the same rotor.For steady analysis,the predicted results agree well with the experimental data for the estimation of compressor rotor global performance.For unsteady flow analysis, the unsteady flow nature caused by the breakdown of the tip leakage vortex in blade tip region in the transonic compressor rotor at near stall condition has been captured with a single blade passage.On the other hand, the time-accurate unsteady computations of multi-blade passage at near stall condition indicate that the unsteady breakdown of the tip leakage vortex triggered the short length-scale-spike type rotating stall inception at blade tip region.It was the forward spillage of the tip leakage flow at blade leading edge resulting in the spike stall inception. As the mass flow ratio is decreased,the rotating stall cell was further developed in the blade passage.     

Numerical investigations on the steady and unsteady leakage flow and heat transfer characteristics of rotor blade squealer tip

The steady and unsteady leakage flow and heat transfer characteristics of the rotor blade squealer tip were conducted by solving Reynolds-Averaged Navier-Stokes(RANS) equations with k-ω turbulence model.The first stage of GE-E3 engine with squealer tip in the rotor was adopted to perform this work.The tip clearance was set to be 1% of the rotor blade height and the groove depth was specified as 2% of the span.The results showed that there were two vortexes in the tip gap which determined the local heat transfer characteristics.In the steady flow field,the high heat transfer coefficient existed at several positions.In the unsteady case,the flow field in the squealer tip was mainly influenced by the upstream wake and the interaction of the blades potential fields.These unsteady effects induced the periodic variation of the leakage flow and the vortexes,which resulted in the fluctuation of the heat transfer coefficient.The largest fluctuation of the heat transfer coefficient on the surface of the groove bottom exceeded 16% of the averaged value on the surface of the squealer tip.     

Influence of tip clearance on performance of a contra-rotating fan

Influences of tip clearance on the tip flow and associated loss mechanism in a contra-rotating axial flow fan has been studied in the paper, based on three dimensional numerical results. The results with different tip clearance are compared in terms of stage efficiency, relative total pressure loss coefficient, flow angle. It is found that the efficiency of the contra-rotating fan changes almost linearly with increment of the tip clearance, however, efficiency of the rear rotor is observed to decrease more dramatically than that of the forward rotor given same tip clearance variation. The analysis on the flow structure indicates that the tip region flow field is qualitatively similar in both rotors. However, with the same clearance value, the leakage flow in the rear rotor is effected by a tip leakage vortex of greater intensity caused by relative loading levels and the inter rotor interaction.     

零间隙压气机失稳机理的全通道数值模拟研究

为了探究零间隙压气机流动失稳机理,采用全通道非定常数值模拟方法研究了一台零间隙斜流压气 机转子的失稳机理,数值模拟过程中在转子出口施加了随时间动态变化的背压模拟压气机转子节流,非定常 数值计算结果表明零间隙斜流压气机转子仍然表现为典型突尖流动失稳特征。通过详细地分析斜流压气机 转子节流过程中不同阀系数对应的压气机内部流场结构,结果表明:尽管零间隙斜流压气机无叶顶泄漏特 征,但随着对压气机节流,转子叶片尾缘率先出现流动分离,进一步节流,尾缘流动分离表现为一方面在周向 范围加剧,另一方面分离点逐渐向上游移动,造成通道严重堵塞,最终引发相邻叶片通道尾缘回流和叶片前 缘流动溢出进而诱发叶片通道内部出现径向涡结构,从而形成压气机突尖失速先兆。