涡流发生器对潮流能水轮机叶片流动分离特性影响研究

当来流速度过大或在大攻角来流工况下,潮流能水轮机叶片边界层会发生流动分离,导致获能效率降低,甚至会使叶片发生失速破坏。针对上述问题,该文将涡流发生器（VGs）理论与水轮机叶片设计相结合,开展VGs对潮流能水轮机叶片流动分离现象的抑制机理研究。以NACA63418翼型设计的潮流能水轮机叶片为研究对象,分别建立带和不带VGs的叶片三维模型,应用CFD方法研究VGs对潮流能水轮机叶片的流动分离特性影响。结果表明：水轮机叶片流动分离主要发生在吸力侧表面叶根部分,随着流速的增大会沿叶根向叶尖径向扩展;VGs能有效减小水轮机叶片吸力侧表面分离区域,抑制流动分离现象发生;在该研究中,安装VGs后水轮机叶片整体获能性能提升明显,获能系数增加0.5%~5.0%,且能增加潮流能水轮机运行稳定性。     

混合型前缘掠对离心压气机气动性能的影响

对带有叶片前缘混合掠的跨音速离心压气机流场进行了数值模拟研究.结果表明:叶片前缘混合前掠能够有效提高压气机流通能力,拓展失速裕度,推迟压气机失稳,使压气机工作裕度得到明显提升,而叶片前缘混合后掠则减少失速裕度,使压气机工作裕度下降,易发生失稳;叶片前缘混合前掠可以有效减弱叶轮通道内部激波强度,而前缘混合后掠会使通道内激波强度增强,造成一定的激波损失;虽然二者均可以改善通道下游分流叶片两侧低能流团的分布情况,但叶片前缘混合前掠改善作用更好;叶片前缘混合掠对压气机内部二次流的影响主要集中在叶片前缘附近,对叶轮出口附近二次流影响不大.通过对不同前缘混合掠结果对比分析,叶片前缘混合前掠在提高压气机流通能力、工作裕度以及改善内部气流流动情况具有明显的优势.     

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.     

对跨音速转子附面层发展控制研究

采用数值方法模拟了低雷诺数条件下NASA Rotor 37跨音速压气机转子内部流场。结果表明,附面层径向涡是该压气机转子流动失稳的一个很重要的原因。通过在该压气机转子叶片吸力面叶顶附近处进行抽吸,发现可以很好地抑制附面层径向涡的发展,压气机转子的稳定工作范围明显扩大。此外,还比较了不同的抽吸量对压气机性能的影响。     

分流叶片前缘掠 对跨音速离心压气机气动性能的影响

对不同分流叶片前缘掠角(-20°~20°)的跨音速离心压气机流场进行了数值模拟研究,结果表明:分流叶片掠几乎不改变压气机的堵塞流量,前掠有扩展压气机工作范围、增加失速裕度的趋势,同时使性能提高,分流叶片前掠10°性能最佳,在最高效率点效率提高0.77%,压比提升0.91%;与原压气机相比,后掠性能有所下降。分流叶片掠对主叶片的影响集中在其叶片中部,对前端低能流体的径向迁移改善效果不明显;前掠使主叶片中部压差减小,减弱了通道中横向的压力梯度,减小间隙泄漏损失,后掠使泄漏损失增加;分流叶片掠对主叶片吸力面的斜激波影响甚微,对通道中部及其两侧的低能流体作用较明显,前掠抑制了压力面侧低能流团的发展,更好地改善了通道中部的分离流动,后掠使低能流团向分流叶片前积聚,流动损失增加。     

叶片前缘不同后掠角对离心压气机气动性能的影响

采用全三维气动设计技术,设计了4种具有掠角叶片和带翼型叶片扩压器的涡轮增压跨音速离心压气机,并采用数值模拟手段研究了叶片前缘不同后掠角对压气机内部工质流动的影响。研究结果表明:主叶片前缘不同后掠角会使压气机堵塞流量(堵塞工况下的工质流量)增加,提高压气机流通能力,同时,可以有效改善通道内低能流团的分布;但由于主叶片轴向弦长缩短,会造成喘振裕度的减少,以及主叶片前缘脱体激波角增大和槽道激波的增强;对截面二次流分析结果表明:叶片前缘的后掠角对二次流的影响主要表现在叶轮进口附近,对出口影响不大。对比不同前缘后掠角压气机内部流动情况发现,掠角越小,叶片叶顶负荷越小,叶片表面压差也越小,流动越稳定;掠角越大,虽然叶轮通道上游产生的激波越强烈,但是可以明显改善通道下游气流流动情况。     

不同湍流模型对水平轴风力机三维粘性气流特性的影响

对某水平轴风力机叶片附近的三维湍流流场进行了数值模拟,其中在7、15、25m/s 3种不同工况下分别采用S-A、Standard k-ε、RNG k-ε和SST k-ω4种湍流模型。计算结果表明:随着来流速度的逐渐增大,叶片吸力面的分离流沿叶根向叶尖方向逐渐发展,且由于三维旋转效应使得展向流动逐渐增强。和相关实验结果比较,选择不同的湍流模型对数值模拟结果有明显影响,其中RNG k-ε和SST k-ω两种模型可以获得较好的压力分布计算精度。综合考虑压力分布、功率系数和推力系数在不同工况下与实验结果的比较,选择SST k-ω湍流模型较适合模拟该水平轴风力机周围复杂的三维湍流流动。     

超音速叶型关键几何参数敏感性分析

为了分析超音速叶型关键几何参数的敏感性,以NASA Rotor67跨音速压气机转子为研究对象,采用准二维的数值方法,研究弯度、最大厚度位置等叶型关键几何参数的变化对跨音速压气机转子顶部叶栅激波结构及流场性能的影响。结果表明,与最大厚度位置相比,叶型弯度的影响更为显著;以安装角表征叶型弯度,在63°~65°范围内存在最优值使总压比达到最大。     

基于LES的压气机叶栅通道非定常流动结构研究

为了进一步理解压气机叶栅通道内的非定常流动结构,采用大涡模拟(LES)方法研究了来流附面层厚度和稠度变化对叶栅通道内涡系结构及总压损失系数的影响。研究表明：来流附面层增厚将导致端壁处流体的轴向动能降低,使得马蹄涡压力面分支更早地流向相邻叶片吸力面;来流附面层越厚,通道涡在叶栅尾缘沿展向抬升的高度越高,角区分离的范围也越大;叶栅的总压损失随附面层增厚而增加,附面层损失增加显著,二次流损失有所增大;稠度较低时叶栅吸力面表面存在分离,会对通道涡及角区分离产生影响;稠度增大,横向压力梯度减小,叶栅流道的速度分布更均匀,通道涡的强度和尺度减小,角区分离的范围减小;稠度增大使叶表不再分离时,总压损失显著降低,但稠度继续增大会使气流与叶片表面的摩擦损失增加。     

带小翼肋条的涡轮叶尖泄漏流场的数值模拟

对叶尖吸力面带小翼肋条的某一轴流转子叶尖间隙泄漏流场进行了数值研究,分析了在不同肋条宽度下泄漏流场细节,并对涡轮效率进行了计算.结果表明:涡轮叶尖单吸力边小翼肋条总体上减小叶尖表面压差,使得吸力面后半部分泄漏流速度减小,从而减小泄漏流动损失,但会增大通道内流动损失,使涡轮转子效率下降;小翼肋条宽度有一个最佳值,小间隙下增大肋条宽度使得涡轮转子效率降低,大间隙下增大肋条宽度却使得涡轮转子效率提高;吸力边小翼肋条改变了叶尖吸力边附近的流场,对压力边附近泄漏流动结构影响不大.     

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.     

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。     

Effects of a kind of non-smooth blade on the unsteady flow field at the exit of an axial fan

An experimental investigation of effects of a kind of streamwise-grooved blade on the unsteady flow field at an exit of an axial-flow fan was performed. The flow field at 25% chord downstream from the trailing edge at hub was measured using a fast-response five-hole pressure probe at different mass-flow conditions. The unsteady flow of the grooved blades was compared with that of the smooth blades. The measurement results indicate that： （1） the grooved blades restrain the velocity fluctuation and the pressure fluctuation by modulating the blade boundary layers, which contributes to the flow loss reduction in the hub region and in the rotor wake region at the design condition; （2） the stream-wise grooves play an important role in restraining the radial migration in the blade boundary layer and abating the tip flow mixing, which contributes to the flow loss reduction in the tip region at the design condition; （3） at the near stall condition, the grooved surface can not reduce the flow loss, even increase the loss nearby when the separation happens in the blade boundary layer.     

System identification modeling and unstable behavior of the dynamics of flows within the tip region of an axial compressor blade passage

In recent years, the correlation coefficient of pressure data from the same blade passage in an axial compressor unit has been used to characterize the state of flow in the blade passage. In addition, the correlation coefficient has been successfully used as an indicator for active control action using air injection. In this work, the correlation coefficient approach is extended to incorporate system identification algorithms in order to extract a mathematical model of the dynamics of the flows within a blade passage. The dynamics analyzed in this research focus on the flow streams and pressure along the rotor blades as well as on the unsteady tip leakage flow from the rotor tip gaps. The system identification results are used to construct a root locus plot for different flow coefficients, starting far away from stall to near stall conditions. As the compressor moves closer to stall, the poles of the identified models move towards the imaginary axis of the complex plane, indicating an impending instability. System frequency data is captured using the proposed correlation based system identification approach. Additionally, an oscillatory tip leakage flow is observed at a flow coefficient away from stall and how this oscillation changes as the compressor approaches stall is an interesting result of this research. Comparative research is analyzed to determine why the oscillatory flow behavior occurs at a specific sensor location within the tip region of the rotor blade.     

Effects of suction side squealer tip on the performance of a low-speed axial compressor

This paper presents the investigation of the effects of suction side squealer tip on the performance of an axial compressor.The experiment is carried out in a single-stage large-scale low-speed compressor.The investigated tip geometries include flat tip as the baseline and suction side squealer tip.The tip clearance of the baseline is 0.5% of the blade span.The static pressure rise characteristic curves of both the rotor and the stage are measured.The flow field at the exit of the rotor is measured by a 5-hole probe under design and off-design conditions.The static pressure on the endwall of the rotor passage is also obtained.The results show that the pressure rise characteristic curves obtained by measuring the pressure on the end wall are almost unchanged by using the suction side squealer tip.The measuring results of the 5-hole probe show the static pressure and the total pressure in tip region is slightly greater than that of the flat tip at the design condition at the exit of the rotor.It also leads to greater av-eraged static pressure rise and total pressure.At the near stall condition,the averaged static pressure and total pressure is lower than the baseline which is related to the redistribution of the blade load caused by the suction side squealer tip.     

Numerical study on the influence mechanism of inlet distortion on the stall margin in a transonic axial rotor

A numerical study is conducted to investigate the influence of inlet flow condition on tip leakage flow (TLF) and stall margin in a transonic axial rotor.A commercial software package FLUENT,is used in the simulation.The rotor investigated in this paper is ND_TAC rotor,which is the rotor of one-stage transonic compressor in the University of Notre Dame.Three varied inlet flow conditions are simulated.The inlet boundary condition with hub distortion provides higher axial velocity for the incoming flow near tip region than that for the clean inflow,while the incoming main flow possesses lower axial velocity near the tip region at tip distortion inlet boundary condition.Among the total pressure ratio curves for the three inlet flow conditions,it is found that the hub dis-torted inlet boundary condition improves the stall margin,while the tip distorted inlet boundary condition dete-riorates compressor stability.The axial location of interface between tip leakage flow (TLF) and incoming main flow (MF) in the tip gap and the axial momentum ratio of TLF to MF are further examined.It is demonstrated that the axial momentum balance is the mechanism for interface movement.The hub distorted inflow could de-crease the axial momentum ratio,suppress the movement of the interface between TLF and MF towards blade leading edge plane and thus enhance compressor stability.     

Smart control of a horizontal axis wind turbine using dielectric barrier discharge plasma actuators

Rotating stall around a small-scale horizontal axis wind turbine was experimentally studied to characterize and assess smart rotor control by plasma actuators. Phase-locked Particle Image Velocimetry was used to map the flow over the rotor blade suction surface at numerous radial stations at a range of tip-speed-ratios. Flow separation occurred from the inboard of the blade and spread radially outwards as the tip-speed-ratio reduced. Plasma actuators placed along the span that produced a chord-wise body force had very little effect on the flow separation, even when operated in pulsed forcing mode. In contrast, plasma actuators along the blade chord that produced a body force into the radial directions (plasma vortex generators) successfully mitigated rotating stall. Torque due to aerodynamic drag was reduced by up to 22% at the lowest tip-speed-ratio of 3.7, suppressing stall over the outboard 50% of the blade. This was due to quasi-two-dimensional flow reattachment in the outboard region, and shifting of a fully stalled zone towards the hub in the inboard region because the plasma-induced body force counteracted the Coriolis-induced radial flow. This can significantly increase the turbine power output in unfavourable wind conditions and during start-up.     

The Interactions of Turbine Hot Streak and Leakage Flow from the Inter-Platform Gap

ABSTRACT

The paper presents the effects of the leakage flow from the inter-platform gap on the migration of hot streak in a first stage turbine by three-dimensional unsteady Reynolds-Averaged Navier-Stokes simulations. Five circumferential positions of the hot streak are considered. The comparisons between the results with/without slot leakage show significant differences. The leakage changes the hot streak in the vane passage significantly and it protects the vane suction surface trailing from the hot gas. The leakage also changes the secondary flow and results in forming a new couple of vortices in the vane passage. In general, rotor passage, the hot gas usually gathers in the rotor hub and the pressure surface. In the present study, the leakage coolant from upstream slot is entrained to the unsteady rotor secondary flows and transported toward the rotor hub and pressure surface effectively. The cooling effect is related to the relative circumferential positions between the hot streaks and slot. When the hot streak is positioned at the slot suction side, the time-averaged temperature reduction on the blade leading edge can be more than twice of that for the hot streak at the slot pressure side.     

Effects of a Kind of Non-smooth Blade on the Performance of an Axial Fan

This paper presents an experimental investigation of effects of a kind of streamwise-grooved blade on theperformance of an axial-flow fan.The flow field at 25% chord downstream from the trailing edge at hub wasmeasured using a 5-hole pressure probe at different mass-flow conditions.The fan performance of the grooveblades was compared with that of the smooth blades.The measurement results indicate that:(1)the non-smoothblades increase mass flow of the fan at the same throttle conditions except a near stall condition;(2)thenon-smooth blades reduce the relative total pressure loss in the rotor passage and increase the fan's total pressurerise at the test mass-flow conditions except the near stall condition;(3)Negative benefits are obtained at a nearstall condition when the smooth blades are replaced by the non-smooth ones.The fan mass flow decreases 0.9%while the total-pressure rise decreases 2.4% at the near stall condition.     

高压涡轮动叶前缘新型几何特征对流场结构影响研究

本文提出一种前缘前伸内凹且根部叶片略厚的新型动叶片设计方法,旨在通过这种新型叶片控制前缘马蹄涡的生成和发展,通过根部叶片较厚到中间区域叶片厚度略低的三维设计和积叠方法,实现动叶片的弯叶片效果。论文以某高压涡轮叶片为研究对象,从能量损失系数、型面压力分布、旋涡沿流向变化对比分析了新型叶片与原型叶片对流场结构的影响。研究表明叶型前缘新的几何特征使马蹄涡得到控制,流场内流动得到改善。