COMPUTATIONAL AND EXPERI-MENTAL STUDY ON TIP LEAKAGE VORTEX OF CIRCUMFERENTIAL SKEWED BLADES

In the steady operation condition, the experiments and the numerical simulations are used to investigate the tip leakage flow fields in three low pressure axial flow fans with three kinds of circumferential skewed rotors, including the radial rotor, the forward-skewed rotor and the back- ward-skewed rotor. The three-dimensional viscous flow fields of the fans are computed. In the experiments, the two-dimensional plane particle image velocimetry （PIV） system is used to measure the flow fields in the tip region of three different pitchwise positions of each fan. The results show that the computational results agree well with the experimental data in the flow field of the tip region of each fan. The tip leakage vortex core segments based on method of the eigenmode analysis can display clearly some characteristics of the tip leakage vortex, such as the origination position of tip leak- age vortex, the development of vortex strength, and so on. Compared with the radial rotor, the other two skewed rotors can increase the stability of the tip leakage vortex and the increment in the forward-skewed rotor is more than that in the backward-skewed one. Among the tip leakage vortices of the three rotors, the velocity of the vortex in the forward-skewed rotor is th6 highest in the circumferential direction and the lowest in the axial direction.

喷水推进泵空化诱导压力脉动特性的试验研究

为探讨喷水推进泵内空化流动结构演变对压力脉动特性的影响,本文结合高速摄像和压力脉动同步测量展开了试验研究。结果表明:随着空化条件加剧,叶顶出现了泄漏涡核空化、剪切层旋涡空化、叶顶吸力侧片状空化和云状空化等复杂空化流动结构;叶顶低压区随着空化区域增大而增大;在泄漏流夹带下空化云不断翻滚,增加了空化云的不稳定性;空化云尺度随空化条件加剧而增大。大尺度空化云会导致强烈的压力脉动。空化区边缘的空泡破碎会带来压力冲击成份。压力脉动主频是叶频,次主频是二倍叶频。主频和次主频幅值在片状空化时小幅增长,在云状空化时大幅增大。垂直空化涡发展会导致叶片前缘附近压力面压力和局部压差下降,这是泵性能断裂的重要原因。

Examination on behavior of tip leakage flow in a three-stage gas-liquid two-phase flow pump

Tip leakage flow(TLF)trajectory in a pump with gas entrainment is investigated via visualization experiments and numerical simulations.Starting position of tip leakage vortex(TLV)is determined accurately by numerical simulation.Under high liquid flow rate(Q_(l))and high inlet gas volume fraction(IGVF)conditions,TLF flows from suction surface to pressure surface near the leading edge of blade,and the direction of TLF gradually changes along the chord which flows from pressure surface to suction surface near the tailing edge.The angle between TLF and blade mean camberline increases progressively as either Q_(l)or IGVF decreases,and starting position of TLV moves towards leading edge direction.As Q_(l)or IGVF decreases,value of vorticity increases and high vorticity region moves towards leading edge.The entropy production rate at blade tip clearance is high,and entropy diffuses from pressure surface to suction surface due to jet flow in blade tip clearance.The greater the amount of accumulated gas there is,the greater the amount of entropy in the area.In addition,when gas is entrained in pump,there are many low frequency fluctuations generated in blade tip clearance.

悬臂方向对TLV空化抑制效果的影响及其机理

该文综合利用实验及数值模拟方法细致研究了悬臂式沟槽叶顶间隙泄漏涡(tip-leakage vortex, TLV)空化抑制器的悬臂凸出方向对抑制TLV空化效果的影响,并对其原因进行了深入讨论。研究表明:相比于原始水翼叶顶处的TLV空化,无论悬臂凸出方向指向水翼的吸力面还是压力面,悬臂式沟槽TLV空化抑制器在各个间隙大小下均能产生显著的抑制效果。相对而言,当所采用的悬臂凸出方向为压力面时,该装置对TLV空化的抑制效果更为显著,且可更有效地抑制TLV空化体积脉动。测量结果表明:悬臂凸出方向对水翼升、阻力系数影响均很小。数值结果则进一步表明:当采用悬臂凸出方向为指向压力面时,悬臂式沟槽TLV空化抑制器能更好地抑制流体从压力面流向吸力面,干扰TLV的生长,进而可以更加有效地抑制TLV空化的发展。

Effect of blade tip geometry on tip leakage vortex dynamics and cavitation pattern in axial-flow pump

A series of blade tip geometries, including original plain tip, rounded tip on the pressure side and diverging tip towards the suction side, were adopted to investigate the effect of blade geometry on tip leakage vortex dynamics and cavitation pattern in an axial-flow pump. On the basis of the computation, it clearly shows the flow structure in the clearance for different tip configurations by the detailed data of axial velocity and turbulent kinetic energy. The in-plain trajectory, in aspects of the angle between the blade suction side and vortex core and the initial point of tip leakage vortex, was presented using the maximum swirling strength method. The most striking feature is that the inception location of tip leakage vortex is delayed for chamfered tip due to the change of blade loading on suction side. Some significant non-dimensional parameters, such as pressure, swirling strength and turbulent kinetic energy, were used to depict the characteristics of tip vortex core. By the distribution of circumferential vorticity which dominates the vortical flows near the tip region, it is observed that the endwall detachment as the leakage flow meets the mainstream varies considerably for tested cases. The present study also indicates that the shear layer feeds the turbulence into tip leakage vortex core, but the way is different. For the chamfered tip, high turbulence level in vortex core is mainly from the tip clearance where large turbulent kinetic energy emerges, while it is almost from a layer extending from the suction side corner for rounded tip. At last, the visualized observations show that tip clearance cavitation is eliminated dramatically for rounded tip but more intensive for chamfered tip, which can be associated with the vortex structure in the clearance.

Relationship between the Flow Blockage of Tip Leakage Vortex and its Evolutionary Procedures inside the Rotor Passage of a Subsonic Axial Compressor

The near casing flow fields inside the rotor passage of a 1.5 stage axial compressor with different blade-loading levels and tip gap sizes were measured by using stereoscopic particle image velocimetry(SPIV). Based on a carefully defined blockage extracting method, the variations of blockage parameter inside the blade passage were analyzed. It was found that the variation of blockage parameter appeared as a non-monotonic behavior inside the blade passage in most cases. This non-monotonic behavior became much more remarkable as the blade loading increases or mass flow rate decreases.The variations of the blockage parameter inside the blade passage had close relation to the evolutionary procedures of the tip leakage vortex(TLV). The destabilization of the TLV caused a rapid increasing of the blockage parameter. After the TLV lost the features of a concentrated streamwise vortex,the blockage parameter usually got a peak value. And then, because of the intense turbulent mixing between the TLV low momentum flow and its surrounding flows, the flow deficit inside the TLV recovered.

EXPERIMENTAL INVESTIGATION OF TIP CLEARANCE FLOW FOR AN AXIAL FLOW FAN ROTOR

The flow field in the tip region of an axial ventilation fan is investigated with a particle image velocimeter （PIV） system at the design condition. Flow fields with three different tip clearances are surveyed on three different circumferential planes, respectively. The phase-locked average method is used to investigate the generation and the development of a tip leakage vortex. The result from PIV system is compared with that from a particle dynamics anemometer（PDA） system. Both data are in good agreement and the structure of the tip leakage vortex for the rotor is illustrated. The characteristic of a leakage vortex is described in both velocity vectors and vortical contours. The unsteadiness of the leakage vortex and the position of the vortex are surveyed in detail, which interprets the discrepancy between the numerical simulation and PDA experimental results to a certain extent. The center loci of tip leakage vortex at different times and the mean center loci of the leakage vortex are displayed particularly. Finally, the trajectories of the tip leakage vortex by the experimental measurement are compared with predictions from the existing models for high speed and high-pressure compressors and turbines when appropriately interpreted. A good agreement is obtained.

Flow Fields with Tip Leakage Vortex in a Small Axial Cooling Fan

In order to improve the fan characteristics, especially efficiency and noise level of a small axial cooling fan with a large tip clearance, the internal flow measurements with tip leakage vortex were carried out at fan rotor outlet us- ing an I-type hot-wire probe. The probe was set toward two directions, parallel and normal to the meridional plane of test fan, and the two directional velocity components were measured. From the result of fan test it was found that the test fan didn＇t have the unstable characteristic with a positive gradient on its pressure - flow-rate curve. From the results of velocity measurement it was observed that the tip leakage vortex exited at maximum efficiency flow-rate and large flow-rate conditions. However, at small flow-rate conditions the tip leakage vortex was not observed and it was found that the flow field were enlarged toward radial outwards

Numerical Simulation of Tip Leakage Vortex Effect on Hydrogen-Combustion Flow around 3D Turbine Blade

In these years, a lot of environmental problems such as air pollution and exhaustion of fossil fuels have been discussed intensively. In our laboratory, a hydrogen-fueled propulsion system has been researched as an alternative to conventional systems. A hydrogen-fueled propulsion system is expected to have higher power, lighter weight and lower emissions. However, for the practical use, there exist many problems that must be overcome. Considering these backgrounds, jet engines with hydrogen-fueled combustion within a turbine blade passage have been studied. Although some studies have been made on injecting and burning hydrogen fuel from a stator surface, little is known about the interaction between a tip leakage vortex near the suction side of a rotor tip and hydrogen-fueled combustion. The purpose of this study is to clarify the influence of the tip leakage vortex on the characteristics of the 3-dimensional flow field with hydrogen-fueled combustion within a turbine blade passage. Reynolds-averaged compressible Navier-Stokes equations are solved with incorporating a k-ε turbulence and a reduced chemical mechanism models. Using the computational results, the 3-dimensional turbulent flow field with chemical reactions is numerically visualized, and the three-dimensional turbulent flow fields with hydrogen combustion and the structure of the tip leakage vortex are investigated.

Large eddy simulation of tip leakage cavitating flow focusing on cavitation-vortex interaction with Cartesian cut-cell mesh method

In the present paper, flow configurations of cavitating flow around a straight NACA0009 foil with a gap between the foil tip and sidewall are investigated numerically by large eddy simulation（LES） coupled with Zwart-Gerber-Belamri（ZGB） cavitation model. A Cartesian cut-cell method is used for mesh generation, which is of good orthogonality and high quality. A good agreement is obtained between simulation and experiment. Two influencing factors on vorticity distributions, the interaction between different vortices and the occurrence of cavitation, are discussed in detail based on the numerical results. A series of ？-shaped loops are observed during the development of the induced vortex, which is a result of the instability of vortex pair. This finding may provide a new viewpoint to control the evolution of tip-leakage vortex（TLV） cavitation. Moreover, it is found that the dilatation term plays a much more important role in the evolution of TLV cavitation compared with that in sheet cavitation.

Performance Improvement of a Centrifugal Compressor for the Fuel Cell Vehicle by Tip Leakage Vortex Control

Heightened interests have been laid at the preliminary design and optimization of the centrifugal compressor for the fuel cell vehicle.The centrifugal compressor for fuel cell vehicle is driven by a high-speed motor;however,the limit of the motor speed makes the flow passage of the impeller long and narrow,which leads to a serious tip leakage loss.Serious tip leakage loss deteriorates the compressor performance.In this paper,3-D numerical simulations were carried out with the aim of investigating the tip leakage loss in a prototype centrifugal compressor for a 100 kW fuel cell stack.The results revealed that the mixing loss caused by the interaction between the tip leakage vortex and the downstream tip leakage flow contributed to the major part of the tip leakage loss.The path of the tip leakage vortex almost followed the streamwise direction,while the downstream tip leakage flow exhibited strong circumferential momentum,which referred to the fact that they were nearly orthogonal.Therefore,a flow control approach,which was realized by enhancing the blade loading around the leading edge of blade tips in this paper,was proposed to decrease the interaction angle between the tip leakage vortex and the downstream tip leakage flow and then mitigate mixing loss by changing the flow direction of the tip leakage vortex.The results showed a smaller interaction angle was achieved in the optimized impeller compared with the baseline one.Meanwhile,the efficiency was also improved by 1.30%at design condition and the maximum efficiency improvement could be up to 10%at large mass flow condition of 92000 r/min.Being manufactured and tested,the optimized compressor was proved to achieve an isentropic efficiency of 75.84%at design condition.

Modal Analysis and Vortex Trajectory Description for Tip Leakage Flow of a Transonic Turbine Cascade

Tip leakage vortex(TLV),which develops from the clearance between the turbine blade and casing,has been studied for decades.Nevertheless,some associated phenomena,such as its unsteady behaviors,are still not well understood.In the present work,an unsteady simulation of a transonic turbine cascade was conducted by using a validated unsteady Reynolds averaged Navier-Stokes(URANS)technique with the k-ωshear stress transport(SST)turbulence model.Typical three-dimensional vortical topology in the tip region of this transonic turbine blade was depicted based on the vortex and shock wave identification.Afterwards,quantitative descriptions of TLV transient parameters,including core position,radius,intensity,wandering motion amplitude and their statistical analysis were also provided via an ellipse fitting method.Combined with the turbulent parameters in the tip region,it is recognized that the breakdown of TLV does not occur upstream of the trailing edge,and the TLV wandering,especially the spanwise motion is a dominant unsteady feature as migrating downstream.To mathematically extract underlying flow features of tip leakage flow(TLF),two data-driven modal analysis techniques,namely proper orthogonal decomposition(POD)and dynamic mode decomposition(DMD),are presented to complement one another to reveal underlying flow feature.Observation of modes distribution allowed qualitative identification of shockwaves,vortical cluster and corresponding transient interaction.Results of POD show that the dominant unsteady structures in the tip region exhibit various morphology with moving downstream.In the front part near the leading edge,the oscillation of separation bubble and bifurcation of passage vortex paly a dominant role;while in the middle part of the tip region,the corresponding factors are the wandering of TLV and unsteady interaction between shock waves and TLF/TLV.In the vicinity of the trailing edge,the instability induced by the mixing of large-scale vortices serves as the main factor in the context of flow unsteadiness.Both the POD and DMD methods can decompose the dominant frequency of TLV evolution and its harmonic frequencies;however,the DMD method presents a superiority in segregating the high-frequency components and their corresponding unsteady structures.

Effect of Tip-Blade Cutting on the Performance of Large Scale Axial Fan

The effect of tip-blade cutting on the performance of a large scale axial fan was investigated using computational fluid dynamics(CFD)methods.Experiments verified the numerical simulations.The original fan was compared with the one with tip-cutting in terms of dimensionless characteristic and aerodynamic performance in tip region under the conditions of the maximum efficiency point and near-stall point.The results showed that double leakage flow occurred in tip clearance at maximum efficiency point and spillage of leakage flow from leading edge occurred in tip-blade region at near-stall point for the both two fans;and that tip-cutting with 6% of blade height could reduce the intensity of tip-leakage vortex and increase flow capacity in tip blade region,and hold the stall margin almost the same as the original fan.The maximum efficiency of the fan with tip-cutting was improved by1%,and the ability of total pressure rising was obviously greater than the original fan.

Numerical Simulation of Active Control on Tip Leakage Flow in Axial Turbine

In an effort to reduce the blade tip clearance leakage in turbine designs, this article aims to numerically investigate the effects of active jet-flow injected from the blade tip platform upon the blade tip clearance flow. A CFD code integrated with dense-correction-based 3D Reynolds-averaged Navier-Stokes equations together with the well-proven Reynolds stress model (RSM) is adopted. The variation of specific heat is taken into consideration. The effects of jet-flow on the tip clearance flow are simulated ...

基于Omega涡识别理论的自适应空化流动模型

液体火箭发动机涡轮泵内存在多种空化类型,其发生机理有所不同,现有数值计算方法通常采用同一套模型预测所有类型空化,导致预测精度不足。为提高复杂空化流动的计算精度,提出了自适应空化流动模型。基于先进的Omega涡识别理论和ZGB空化模型建立了相变系数自适应调整方法,以涡轮泵内两种典型空化(附着空化和泄漏涡空化)为对象,利用翼型实验对模型进行了验证。首先对比了几种涡识别方法的差异,发现Omega方法对阈值不敏感且物理意义明确,适合作为相变系数的取值依据;分析了相变系数对附着空化和泄漏涡空化的影响规律及两种典型空化的形成机理。结果表明:自适应模型相比ZGB模型,对泄漏涡空化的预测精度在大间隙下提升了约181%,小间隙提升了约27%,对附着空化的预测更接近实验结果;附着空化是吸力面脱落涡形成的原因,间隙泄漏流场的涡带和剪切层空化是由间隙泄漏涡和分离涡共同作用形成的。

半开式离心叶轮叶顶泄漏诱发流道流动堵塞特性研究

为探究半开式离心叶轮叶顶泄漏量诱发的流道中流动堵塞作用,采用大涡模拟对流场进行精确计算,基于流动堵塞预估模型对叶顶间隙0.5、1.0和1.5 mm的3种半开式离心叶轮在不同流量工况下的流动堵塞特性进行研究,发现在叶轮流道内存在流动堵塞峰值,且在3种叶顶间隙下均在截面2处,在经过截面2之后流动堵塞发生大幅度的减小,并在后面4个截面发生小幅度的波动;通过对不同叶顶间隙、不同流量工况下在叶轮尾缘处相对流动堵塞作用的分析,发现尾缘处的流动堵塞在不同叶顶间隙下,随流量的变化具有相同的趋势,相对流动堵塞均在1.0Q_(d)时达到最小值,在0.6Q_(d)时出现峰值;然而流动堵塞在相同流量下与叶顶间隙的关系不是单一的线性关系,且存在一个最优叶顶间隙在设计工况点达到最小的流动堵塞情况;同时通过对泄漏涡发展情况的观察,发现泄漏涡的破碎和位移会增大叶片尾缘处的流动堵塞;通过对叶片静压差的分析,发现运行流量对叶片载荷的影响不大,然而叶顶间隙的改变会大大影响叶片载荷,同时对叶片尾缘处的流动堵塞造成影响。

离心叶轮失速涡结构演化与耦合特征研究

为深入解析离心压气机旋转失速的涡流耦合演化机理,基于Eckardt离心叶轮全通道非定常数值模拟数据,利用涡系识别法和傅里叶频谱分析等方法研究了失速工况下叶轮中关键涡流结构的空间分布特征及非定常演化规律,发现失速流场同时存在两类涡流结构:叶片前缘龙卷风涡和叶顶泄漏涡,两类流动结构交替演化、相互作用,形成了以63%叶轮转速周向传播的失速团,促使离心叶轮失速。具体体现为:叶顶泄漏涡形成并发展,裹挟、牵引叶片前缘分离涡从叶顶开始剥离,直至完全从叶片吸力面脱落。脱落后的分离涡沿周向运动,受到叶片阻挡产生溢流,该溢流流体在叶片压力面与吸力面横向压差的作用下演变为龙卷风涡,该龙卷风涡在周向运动过程中被叶片“截断”为两段而后向下游扩散并逐渐耗散消失。之后新的叶顶泄漏涡又逐渐兴起,形成下一个涡流演化周期。两种涡结构此消彼长、周而复始,共同构成了失速演化特征。

间隙宽度对轴流泵叶顶间隙涡流影响的数值分析

针对轴流泵不同间隙宽度下间隙涡流特性问题,采用数值模拟方法研究了某轴流泵3种叶顶间隙宽度(0.15、0.45、1.20 mm)下的间隙泄漏涡流特性。结果表明,相同流量下,当间隙宽度从0.15 mm增大到1.20 mm时,间隙分离涡区增大,同一平面位置的涡心强度增大。不同叶顶间隙宽度下,叶顶间隙区域的湍动能分布趋势相似,即从叶顶间隙入口处开始沿径向先增大后减小直到轮缘,在分离涡形成附近湍动能达最大值。此外,沿泄漏涡轨迹泄漏涡涡心涡量减小,压力增大,表明前缘附近容易产生空化。对于极小的间隙(0.15 mm),主流大部分流动不能通过间隙,叶顶分离涡仅发生在叶片压力侧转角;对于1.20 mm的间隙,高湍动能叶顶分离涡发生在间隙区,分离涡与剪切层连接从叶片脱离,然后缠绕在涡核外侧,最终被泄漏涡夹带。在间隙附近存在不同的涡量层可将湍流注入泄漏涡。研究成果可为轴流泵的水利优化设计提供参考。

泵喷推进器梢涡空化计算方法

在泵喷推进器梢涡流动数值计算中,转子梢部涡系对转子梢部附近网格质量要求极高,为了准确计算转子梢涡空化,本文首先完成梢涡空化观测试验,并根据空化试验条件布置数值计算,分析常用多通道周期性结构网格在计算准确性上的不足,进而在其基础上,结合梢涡流动特点,提出一种在转子域中进行局部网格重构的方法。通过数值计算结果与空泡观测试验结果对比显示,本文所提出的计算方法既能够满足梢涡空化计算对局部网格质量的超高要求,又能以较少的网格量准确预测梢涡空化。

Numerical Analysis of the Tip Leakage Flow Field in a Transonic Axial Compressor with Circumferential Casing Treatment

This paper reports on numerical investigations aimed at understanding the influence of circumferential casing grooves on the tip leakage flow and its resulting vortical structures.The results and conclusions are based on steady state 3D numerical simulations of the well-known transonic axial compressor NASA Rotor 37 near stall operating conditions.The calculations carried out on the casing treatment configuration reveal an important modification of the vortex topology at the rotor tip clearance.Circumferential grooves limit the expansion of the tip leakage vortex in the direction perpendicular to the blade chord,but generate a set of secondary tip leakage vortices due to the interaction with the leakage mass flow.Finally,a deeper investigation of the tip leakage flow is proposed.