Tip Clearance Flows in Turbine Cascades

This article describes the effects of some factors on the tip clearance flow in axial linear turbine cascades. The measurements of the total pressure loss coefficient are made at the cascade outlets by using a five-hole probe at exit Mach numbers of 0.10, 0.14 and 0.19. At each exit Mach number, experiments are performed at the tip clearance heights of 1.0%, 1.5%, 2.0%, 2.5% and 3.0% of the blade height. The effects of the non-uniform tip clearance height of each blade in the pitchwise direction are also studied. The results show that at a given tip clearance height, generally, total pressure loss rises with exit Mach numbers proportionally. At a fixed exit Mach number, the total pressure loss augments nearly proportionally as the tip clearance height increases. The increased tip clearance heights in the tip regions of two adjacent blades are to be blame for the larger clearance loss of the center blade. Compared to the effects of the tip clearance height, the effects of the exit Mach number and the pitchwise variation of the tip clearance height on the cascade total pressure loss are so less significant to be omitted.

EFFECT OF TIP CLEARANCE ON PERFORMANCE AND FLOW FIELD OF SMALL SIZED HIGH SPEED CENTRIFUGAL FAN

A centrifugal fan with the high speed and compact dimensions is studied numerically and experimentally. The centrifugal fan consists of a shrouded impeller rotating at 34 000 r/min with a small tip clearance 0.7 mm to the fixed outer casing. Computational models with/without the tip clearance are built and the κ-ω shear stress transport （SST） turbulence model and the unstructured mesh are applied to the numerical simulation for unsteady solutions. The overall performance is measured on a standard experimental bench and the major flow feature of each component inside the centrifugal fan is numerically investigated. In the presence of the tip clearance due to the difference of static pressure between leading and trailing edges of the clearance, i. e. , leading and trailing edges of the impeller, a strong return flow exists inside the clearance passage and re-circulates the main stream inside the impeller passage, and produces the strong flow interaction, thus changing the flow field and influencing the overall performance.

Influence of Tip Clearance on Unsteady Flow in Automobile Engine Pump

The automobile engine pump is an important part of the automobile cooling system,and has a direct influence on the engine performance.Based on the SST k-ωturbulence model,unsteady numerical simulation for an automobile engine pump with different tip clearances was carried out by Fluent.To study the flow field characteristics and pressure fluctuation,the characteristics of secondary flow distribution in volute are also analyzed.The result shows that the pressure fluctuation characteristics of the flow field show obvious periodic variation at different levels of tip clearances.The peak value of pressure fluctuation at each monitoring point is dependent on the blade frequency.At the same time,with the increase of the tip clearance,the pressure fluctuation in the blade and volute is gradually increased,while the pressure fluctuation at the tip is reduced clearance.The pressure gradient in the pump also varies periodically with the rotation of the impeller.With the increase of the tip clearance,the pressure of the impeller,volute and tip clearance is gradually decreased.There are secondary flow vortexes inside the impeller,volute outlet and volute section.With the increase of tip clearance,the vortex intensity in the impeller channel is weakened,and the vortex strength at the volute outlet is intensified.On the cross section of the volute,the morphology of most vortexes has insignificant changes,but the vortex intensity decreased.

Experimental study on fluid flow in arciform clearance

The system damping and dynamic characteristics can be further improved by properly increasing the damping coefficient ζ h. For a special hydraulic damping structure, an arciform damping clearance often used in FCS, a mathematical model has been established for fluid flow using the theory of laminar flow in the clearance of parallel plates. Analytical calculations are made for fluid flow in the arciform clearance and relational expression is deduced for flow rate along the arciform cleaance height, pressure difference, maximum arciform clearance height, the flow rate for the fluid flow in arciform clearance as well, and its simplified formula is obtained by using the theory of hydrodynamics and the curve-fitting method. This paper consists of two sections:the first section focuses on the theoretical analysis by using the simplified mathematical model and the second section mainly describes experimental analysis. The simplified formula is corrected with experimental results by considerig various boundary conditions of the damping clearance. Experimental results show that this study of arciform damping clearance is reliable and practical.

TOPOLOGY AND VORTEX STRUCTURES OF A CURVING TURBINE CASCADE WITH TIP CLEARANCE (Ⅱ)- TOPOLOGICAL FLOW PATTERN AND VORTEX STRUCTURE IN THE TRANSVERSE SECTION OF A BLADE CASCADE

By means of ink trace visualization of the flows in conventional straight, positively curved and negatively curved cascades with tip clearance, and measurement of the aerodynamic parameters in transverse section, and by appling topology theory, the topological structures and vortex structure in the transverse section of a blade cascade were analyzed. Compared with conventional straight cascade, blade positive curving eliminates the separation line of the upper passage vortex, and leads the secondary vortex to change from close separation to open separation, while blade negative curving effects merely the positions of singular points and the intensities and scales of vortex.

The Tip Leakage Flow Structure of an Axial Fan with Tip Clearance

Experiment and numerical simulation technique are used to investigate the tip leakage flow in an axial fan with tip clearance at the design condition. The flow field in the tip region of fan is measured using a PDA (Particle Dynamics Analysis) system. The flow is surveyed across the whole passage at fifteen axial locations (from the 100% axial chord in front of the leading edge to the 100% axial chord behind the trailing edge), mainly focusing on the outer 90% blade span. Both experiment measurement and numerical simulation indicates the leakage flow originated from the tip clearance along the chord rolls up into three dimensional spiral structure to form leakage flow vortex. The interaction of leakage flow and main flow will produce the low velocity zone, and block the flow. The leakage flow almost occupies the most part of flow passage behind the trailing edge.

Numerical Analysis of Nozzle Clearance's Effect on Turbine Performance

Variable nozzle turbine （VNT） has become a popular variable geometry turbine （VGT） technology for the diesel engine application. Nozzle clearance, which can＇t be avoided on the hub and shroud side of the VNT turbine due to the pivoting stators, can lead to turbine performance deterioration. However, its mechanism is still not clear. In this paper, numerical investigation, which is validated by experiment, is carried out to study the mechanism of the nozzle clearance＇s effect on the turbine performance. Firstly, performance of the mixed flow turbine with fixed nozzle clearances tested on flow bench. Performance of the tested turbine with the same nozzle clearance is numerically simulated. The numerical result agrees well with the test data, which proves correct of the numerical method. Then the turbine performance with different nozzle clearances is numerically analyzed. The research showed that with nozzle clearance, flow loss in the nozzle increases at first and it reaches the maximum value when the clearance ratio is 5%. Flow at the exit of the nozzle becomes less uniform with nozzle clearance. The negative incidence angle of the rotor also increases with nozzle clearance and leads to more incidence angle loss in the rotor. The low energy fluid formed in the nozzle due to the nozzle clearance migrates from hub to shroud side in the rotor, which is another main reason for the rotor＇s performance degradation. The present research exposed the mechanism of the dramatically decrease of the turbine performance with nozzle clearance： （a） The loss associated with the nozzle leakage increases with the nozzle clearance; （b） The flow loss grows up quickly in the rotor due to the incidence angle loss and migration of the low energy fluid from hub to shroud side.

Topology and Vortex Structures of Turbine Cascade with Different Tip Clearances

This paper uses the topology theory to analyze the surface flowspectrums of straight, positively curved and negatively curvedcascades with relative tip clearances of 0.023 and 0.036, findsapparent differences of topology and vortex structures in the bladetip and the suction side wall corner of single type of cascade withthis two clearances, and studies the mechanism of the differenceformation as well as their effects o the energy loss.

Effect of tongue clearance on hydraulic performance of double support vortex pump

In order to study influence of tongue clearance on the hydraulic performance of double support vortex pump,three dimensional flow model with symmetric variable size tongue clearance was established by changing section parameter of tongue clearance,and applied to numerically simulate the steady inner flow in a vortex pump based on fixed working conditions and impeller through ANSYS FLUENT.The numerical results show the influence of tongue channel with two sections(non-uniform and uniform sections)on flow field characteristics in vortex pump.Firstly,the variation of tongue channel section changes the vortex structure distribution in circumferential flow channel.Specifically the spiral forward vortex structure in the circumferential direction shifts to large radius side with increasing tongue width.Secondly,the circumferential velocity gradient and axial pressure gradient both diminish with the increase of the tongue section,and the inlet/outlet pressure difference and velocity distribution also reduce with increasing tongue channel section.Finally,for vortex pump with non-uniform section of tongue channel,the head diminishes and the efficiency remains constant approximately with the increase of the tongue width,while the head and the efficiency both diminish for uniform section of tongue channel.

Calculation of the Energy Loss for Tip Leakage Flow in Turbines

A commercial N-S solver has been employed for simulation and investigation ofthe unsteady flow field inside the tip clearance of a turbine rotor. The main objective of thispaper is to introduce a new method of energy loss calculation for the flow field in tip clearanceregion of a turbine rotor blade. This method can be easily used in all kinds of flow fields. Regionsof high viscous effects have been found to be located near the shroud rather than the blade tip. Itis shown that the time-averaged loss of energy in tip leakage flow is dissimilar for differentrotor blades. This result is a helpful hint that can be taken by blade designers to designnon-uniform rotor blades with different geometric and aerodynamic loads to minimize the energy loss.

An Experimental Study on Dynamics Features of Three Side-by-Side Flexible Risers Undergoing Vortex-Induced Vibrations in A Uniform Flow

A vortex-induced vibration(VIV)experiment on three side-by-side risers subjected to a uniform flow was carried out in a combined wave-current flume.The dynamic features of interference effect on three side-by-side risers were investigated by varying fluid velocity and inter-riser spacing.The distributions of dimensionless displacement,dominant frequency,and displacement trajectory of the model risers were measured using mode decomposition and wavelet transform techniques.The coupled interference of inter-riser fluid to adjacent risers at different spacings was disclosed by introducing the"interference ratio"concept.The results show that at spacings smaller than 6.0 D,the three model risers display appreciable deviations in their displacement responses in cross-flow or in-line direction,attributable to the strong proximity disturbance and wake interference between the risers.When the spacing is increased to 8.0 D,wake interference still makes great difference to the dynamic response of the risers in both directions.As reduced velocity increases,the three risers show higher agreement with an isolated riser in overall dominant vibration frequency in CF direction than that in IL direction at all spacings and the side risers,although symmetrically placed,do not vibrate symmetrically,as a result of the steady deflection of clearance flow within the riser group.Interference effect results in a remarkable unsteady mode competition within the risers;quantitation of the interference levels for the three risers at different spacings with interference ratio revealed that under low flow velocities and large spacing ratios,clearance flow constitutes a non-neglectable interferer for three side-by-side risers.

间隙密封被动活塞式气体流量标准装置量值溯源方法

间隙密封被动活塞式气体流量标准装置具有操作简单、测量效率高、无水银密封、易于携带和具有自动温压补偿功能等优点,在气体微小流量测量中广泛使用。被动活塞的上下往复运动对测量管路内的压力会产生波动,直接用流量测量法对间隙密封被动活塞式气体流量标准装置进行量值溯源还存在一些困难。针对这一情况,提出了一种利用几何测量法对间隙密封被动活塞式气体流量标准装置进行量值溯源的新方法,对几何测量溯源法进行了不确定度评估,并与国外相关机构进行了比对验证。结果表明,利用几何测量法对间隙密封被动活塞式气体流量标准装置进行溯源的方法是可行的。

压气机内部旋转不稳定的研究综述

旋转不稳定是压气机工作在高负荷近失速工况时的一种常见现象。研究旋转不稳定在降低压气机工作噪声、减小流致振动以及保障航空发动机稳定工作等方面具有重要意义。首先对旋转不稳定现象进行了回顾,详细讨论了旋转不稳定的特征。其次,重点调研了旋转不稳定的起源和机理,将旋转不稳定产生的原因归纳为叶尖泄漏流、涡脱落以及流动剪切等类别。此外,回顾了模拟旋转不稳定的数值方法,讨论了多种流动控制手段对旋转不稳定的作用效果。最后,对旋转不稳定的研究现状进行了总结,对未来的研究趋势进行了展望。

叶顶间隙对低比转数小流量泵性能的影响

为建立叶顶间隙对低比转速小流量泵性能的影响关系,采用数值计算的方法,以叶顶间隙宽s和叶轮出口宽b的比值(s/b)表征间隙大小,对不同间隙下泵的性能展开对比分析。分析发现,随着间隙的增加,泵的扬程和效率均逐渐降低,最大和最小间隙下的扬程和效率差分别达15.4%,5.5%。当间隙较小即s/b<0.2时,扬程曲线在小流量工况会出现不稳定的“驼峰”现象,在s/b>0.3后,设计工况附近效率的降幅显著增大。从流动特性来看,随着叶顶间隙的增大,间隙泄漏流对叶轮内主流区影响加剧,会诱导严重的二次流和旋涡的产生,同时间隙内不稳定流动也会产生能量损失,造成扬程和效率下降。为低比转数小流量泵的设计与优化提供借鉴意义。

叶顶间隙对螺旋混流式喷水推进泵内流及推进特性的影响

喷水推进泵是舰船泵喷推进系统的核心部件,喷水推进泵在工作过程中,叶顶间隙处所产生的泄漏流会严重影响混流泵的工作性能。为了探讨叶轮叶顶间隙对喷水推进泵推进特性的影响,本文定义了叶顶间隙系数τ,设计了六种不同叶顶间隙系数模型并使用Ansys进行仿真分析,最终得到叶顶间隙对于喷水推进泵内流以及推进特性的影响规律。结果表明:随着叶顶间隙系数的增大,叶顶间隙处泄漏流逐渐增加,泄漏涡影响范围变大,轴向推力随着叶顶间隙系数的增大呈负指数下降,叶顶间隙处泄漏量随指数上升,喷水推进泵内流损失增加,推进效率持续减小,并且在大流量工况下叶顶间隙对喷水推进泵推进特性影响最大,在设计的六套模型中,叶顶间隙系数为0.08,叶顶间隙为0.16mm时效率最高。通过本文的研究可以发现,叶顶间隙对于喷水推进泵内流以及推进特性影响较大,在设计时应尽量减小叶顶间隙。

叶顶间隙对蜗壳式混流泵流动特性影响研究

采用计算流体力学(CFD)数值模拟技术,研究了蜗壳式混流泵在不同叶顶间隙下的水力性能及内部流动特性。通过对流场、涡流和压力分布的分析,揭示了叶顶间隙变化对泵装置扬程、效率及运行稳定性的影响。结果表明,随着间隙尺寸的增大,混流泵的整体效率逐渐下降,且对大流量工况的影响尤为显著。同时,叶顶间隙的增大会导致叶轮区域泄漏涡的增强,影响泵的运行稳定性。

压气机叶顶间隙流动与控制研究进展

压缩空气储能被视为最具发展潜力的物理储能技术,作为其核心部件,压气机的性能表现在较大程度上决定着储能系统的经济性和效率。叶顶间隙流动因其复杂的三维流动特性,对压气机内部流场结构变化存在重要作用,是影响整机性能的关键因素。文章依照叶顶结构特点分类总结了带冠、无冠轴流压气机和开式/半开式、闭式离心压气机叶顶间隙流动产生的机理,根据压气机流动特性,进一步综述国内外压气机叶顶间隙流动的研究进展,形成以下结论:对于无冠轴流压气机,非定常叶顶间隙流动与失速、叶片噪声及振动问题密切相关,需扩充研究成果以优化叶顶设计;带冠轴流压气机缺乏实验和数据支撑,流动控制手段单一,可尝试跨领域应用控制技术;离心压气机叶顶间隙流动研究仍需探索变间隙特性和周向不均匀性对流动结构的影响,并提升应对流场变化的能力。未来研究可着重于高精度数值模拟方法的应用推广、跨领域控制技术的尝试和复合结构的探索。

基于Doehlert Matrix的全贯流泵装置定转子进出流间隙优化设计

全贯流泵是一种新型的机电-水泵一体式贯流泵,然而其在运行时存在定转子间隙回流,扰乱了叶轮内的流场分布,导致泵装置产生能量损失、压力波动和噪声等问题,影响泵站的正常运行。通过数值模拟和模型试验研究全贯流泵装置定转子间隙流的水力特性,结合Doehlert Matrix设计-响应面优化法对其定转子进、出流间隙结构进行优化设计,揭示全贯流泵装置定转子进、出流间隙结构对泵装置性能的影响机理,并得到最终优化的折角式定转子进、出流间隙结构方案为:外侧延伸段长度t1为4.921r,外侧收缩段长度x1为0.624r,内侧延伸段长度t2为3.655r,内侧收缩段长度x2为1.6r(r为定转子间隙宽度),使得全贯流泵装置扬程和效率分别提升约10.3%和5.2%。

跨音速流动中涡轮动叶叶顶的气膜冷却特性分析

为了掌握跨音速流动中涡轮动叶叶顶气膜冷却特性,采用压敏漆测试技术来研究叶顶间隙高度和质量流量比对叶顶气膜冷却特性的影响规律。研究结果表明:在小质量流量比条件下,增加叶顶间隙高度能够有效改善叶顶中弦区域的气膜覆盖,然而当质量流量较大时,叶顶间隙高度变化对叶顶中弦区域的气膜冷却效率分布影响并不明显;在小叶顶间隙高度条件下,随着质量流量比增加,叶顶中弦区域冷气覆盖效果逐渐变差,在大叶顶间隙高度条件下,仅当质量流量比从0.1%+0.05%增加到0.14%+0.07%时,叶顶中弦区域的冷气覆盖效果才有所改善。

泵喷推进器间隙流场尺度效应数值研究

由于泵喷推进器转子与导管之间有间隙的存在,内流场特性较复杂.为了探究尺度效应对泵喷推进器间隙流场的影响,采用非定常雷诺平均Navier-Stokes(URANS)方程和SST k-ω湍流模型,利用全结构化网格对计算域进行离散处理,滑移网格用于处理转子和其他部件之间的相对运动.首先通过网格不确定分析来验证本文数值方法的可行性,数值计算结果与模型试验数据进行了比较,两者吻合良好;然后对3种尺度泵喷推进器模型的敞水性能进行了数值计算,从涡量场和压力场的角度进行了分析.结果表明,全进速系数下,实尺度模型的效率会提高;实尺度模型的叶梢泄漏涡(TLV)涡量溃灭提前,涡量强度更低,并且TLV涡核中心压力系数更小,间隙间的脉动压力幅值更低.