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.     

Behavior of Vaneless Diffuser Stall in a Centrifugal Compressor

The rotating stall in a centrifugal compressor with a vaneless diffuser was investigated both experimentally and numerically with focus on the effect of the internal flow field within the impeller on the diffuser stall.Through numerical analysis,the boundary layer separation at the impeller outlet was found to play an important role in the expansion and rotation processes of the diffuser stall.In particular,the expanded boundary layer separation near the hub side at the outlet of the main blade(M.B.)suction surface passage was considered to be the main cause of the expansion and rotation processes.A longitudinal vortex existed at the throat of the M.B.passage,and the mass flow rate in the M.B.passage was significantly reduced by the blockage effect.In addition,the longitudinal vortex induced the rolling up flow near the hub side at the impeller exit.Thus,the boundary layer separation expanded.     

A similitude method and the corresponding blade design of a low-speed large-scale axial compressor rotor

A similitude method to model the tip clearance flow in a high-speed compressor with a low-speed model is presented in this paper. The first step of this method is the derivation of similarity criteria for tip clearance flow, on the basis of an inviscid model of tip clearance flow. The aerodynamic parameters needed for the model design are then obtained from a numerical simulation of the target high-speed compressor rotor. According to the aerodynamic and geometric parameters of the target compressor rotor, a large-scale low-speed rotor blade is designed with an inverse blade design program. In order to validate the similitude method, the features of tip clearance flow in the low-speed model compressor are compared with the ones in the high-speed compressor at both design and small flow rate points. It is found that not only the trajectory of the tip leakage vortex but also the interface between the tip leakage flow and the incoming main flow in the high-speed compressor match well with that of its low speed model. These results validate the effectiveness of the similitude method for the tip clearance flow proposed in this paper.     

Investigation on centrifugal impeller in an axial-radial combined compressor with inlet distortion

Assembling an axial rotor and a stator at centrifugal compressor upstream to build an axial-radial combined compressor could achieve high pressure ratio and efficiency by appropriate size augment.Then upstream potential flow and wake effect appear at centrifugal impeller inlet.In this paper,the axial-radial compressor is unsteadily simulated by three-dimensional Reynolds averaged Navier-Stokes equations with uniform and circumferential distorted total pressure inlet condition to investigate upstream effect on radial rotor.The results show that spanwise nonuniform total pressure distribution is generated and radial and circumferential combined distortion is formed at centrifugal rotor inlet.The upstream stator wake deflects to rotor rotation direction and decreases with blade span increases.Circumferential distortion causes different separated flow formations at different pitch positions.The tip leakage vortex is suppressed in centrifugal blade passages.Under distorted inlet condition,flow direction of centrifugal impeller leading edge upstream varies evidently near hub and shroud but varies slightly at mid-span.In addition,compressor stage inlet distortion produces remarkable effect on blade loading of centrifugal blade both along chordwise and pitchwise.     

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.     

Stall Behaviour in a Mixed-flow Compressor with Axial Slot Casing Treatment

Casing treatment is an effective technique in extending stall margin of axial and centrifugal compressor.However,its impacts on the stall behaviour of mixed-flow compressor are still not completely understood until now.To conquer this issue,unsteady full-annulus simulations were conducted to investigate the stall mechanism of a mixed-flow compressor with and without axial slot casing treatment(ASCT).The circumferential propagating speed of spike inception resolved by the numerical approach is 87.1%of the shaft speed,which is identical to the test data.The numerical results confirmed that the mixed-flow compressor fell into rotating stall via spike-type with and without ASCT.The flow structure of the spike inception was investigated at 50%design rotational speed.Instantaneous static pressure traces extracted upstream of the leading edge had shown a classic spiky wave.Furthermore,it was found that with and without ASCT,the mixed-flow compressor stalled through spike with the characteristic of tip leakage spillage at leading edge and tip leakage backflow from trailing edge,which is different from a fraction of the centrifugal compressor.The resultant phenomenon provides conoborating evidence for that unlike in axial-flow compressor,the addition of ASCT does not change the stall characteristics of the mixed-flow compressor.The flow structure that induced spike inception with ASCT is similar to the case with smooth casing.In the throttling process,tip leakage flow vortex had been involved in the formation of tornado vortices,with one end at the suction side,and the other end at the casing-side.The low-pressure region relevant to the downward spike is caused by leading-edge separation vortex or tornado vortex.The high-pressure region relevant to the upward spike is induced by blockage from the passage vortex.These results not only can provide guidance for the design of casing treatment in mixed-flow compressor,but also can pave the way for the stall waring in the highly-loaded compressors of next-generation aeroengines.     

Numerical investigation on the effects of re-organized shock waves on the flow separation for a highly-loaded transonic compressor cascade

This paper presents a detailed numerical investigation of the influence of re-organized shock waves on the flow separation for a highly-loaded transonic compressor cascade. The boundary layer suction (BLS) was used to control the location and strength of shock waves, with the aspirated slot locating at 49% chord, where is just downstream of the impingement point of shock wave at the leading edge. The numerical simulation is based on NUMECA, a commercial software, where the cell-centered control volume approach with third-order spatial accuracy is used to solve the 3-D Reynolds-averaged Navier-Stokes equations under the Cartesian coordinate system. Several conclusions can be made through the observation of the numerical results. (1) Multiple shock waves in cascade passage leaded the velocity deficits of boundary layer on suction surface downstream of shock wave, resulting in seriously separated flow on the suction side of blade, especially when the front shock wave is much stronger than the rest of the shocks. (2) BLS with small mass flow rate can not effectively improve the boundary layer. When the impingement point of oblique shock wave coming from cascade leading edge is bled to downstream of the passage shock wave by BLS, the boundary layer flow is greatly improved. However, if the BLS mass flow rate exceeds a critical value (1.2%), the boundary layer downstream of shock wave would separate from suction surface. (3) At the blade mid-span, the aerodynamic performance of compressor blade is improved as BLS mass flow rate increases. The optimum BLS is about 1.2%. Compared with the baseline case, the BLS with flow rate of 1.2% increases the total pressure recovery coefficient by 12%, and decreases diffusion factor by 18% and deviation angle to 7 ° while keeping the pressure rise constant. (4) The three dimensional flow structure of the compressor cascade ranged from 25% span to 75% span was improved greatly with the 1.2% BLS flow rate. However it could not control the development of the corner boundary layer effectively.     

Unsteady behavior and control of vortices in centrifugal compressor

Two examples of the use of vortex control to reduce noise and enhance the stable operating range of a centrifugal compressor are presented in this paper.In the case of high-flow operation of a centrifugal compressor with a vaned diffuser,a discrete frequency noise induced by interaction between the impeller-discharge flow and the diffuser vane,which appears most notably in the power spectra of the radiated noise,can be reduced using a tapered diffuser vane（TDV） without affecting the performance of the compressor.Twin longitudinal vortices produced by leakage flow passing through the tapered portion of the diffuser vane induce secondary flow in the direction of the blade surface and prevent flow separation from the leading edge of the diffuser.The use of a TDV can effectively reduce both the discrete frequency noise generated by the interaction between the impeller-discharge flow and the diffuser surface and the broadband turbulent noise component.In the case of low-flow operation,a leading-edge vortex（LEV） that forms on the shroud side of the suction surface near the leading edge of the diffuser increases significantly in size and blocks flow in the diffuser passage.The formation of an LEV may adversely affect the performance of the compressor and may cause the diffuser to stall.Using a one-side tapered diffuser vane to suppress the evolution of an LEV,the stable operating range of the compressor can be increased by more than 12 percent,and the pressure-rise characteristics of the compressor can be improved.The results of a supplementary examination of the structure and unsteady behavior of LEVs,conducted by means of detailed numerical simulations,are also presented.     

Numerical simulation on the effect of tip clearance size on unsteadiness in tip clearance flow

Unsteadiness of tip clearance flow with three different tip clearance sizes is numerically investigated in this paper. NASA Rotor 67 is chosen as the computational model. It is found that among all the simulated cases, the un- steadiness exists when the size of the tip clearance is equal to or larger than design tip clearance size. The relative total pressure coefficient contours indicate that region of influence by tip leakage flow augments with the increase of tip clearance size at a fixed mass flow rate. Root Mean Square contours of static pressure distribution in the rotor tip region are provided to illustrate that for design tip clearance （1.1% tip chord） the strongest fluctuating region is located on pressure side of blade near leading edge, while for the larger tip clearance （2.2% tip chord）, it is in the region of the interaction between the shock wave and the tip leakage flow.     

An improvement on the efficiency of a single rotor transonic compressor by reducing the shock wave strength on the blade suction surfaces

It is well known that increasing the rotational velocity is an effective way to increase the total pressure ratio. With increasing flow velocity especially under the condition of transonic flow in the supersonic region, where exist strong shock waves, the shock wave loss becomes main and important. Simultaneously, there occurs boundary layer separation due to the shock wave / boundary layer interaction. In the present paper the transonic compressor blades were studied and analyzed to find a proper and simple way to reduce the shock wave loss by optimizing the suction surface configuration or controlling the gradient of isentropic Mach number on the suction surface. A Navier-Stokes solver combined with a modified design algorithm was developed and used. The NASA single rotor for transonic flow compressor was served as a numerical example to show the effectiveness of this method. Two cases for both original and modified rotors were analyzed and compared.     

振荡作用下气液两相流的流动特性

为研究高强化活塞冷却油腔内气液两相流的振荡流动结构对其强化传热效果的影响,对矩形空腔内气液两相流的振荡流动过程进行了实验研究。结果表明:气液两相流在起振阶段和充分振荡阶段的振荡流动规律有着明显的区别,起振阶段两相流以"爬壁"运动为主,而充分振荡阶段两相流则以"绕壁"运动为主;振荡频率主要影响两相流中气泡的状态和湍流强度,而填充率则主要影响两相流的流动形态和运动规律,在起振阶段振荡频率和填充率对起振阶段时长和最大气泡尺度的变化都有显著影响,而在充分振荡阶段,振荡频率对于气泡尺度的影响要明显高于填充率。     

缸盖冷却水的单相流沸腾模型

针对缸盖水腔内的冷却水流动沸腾传热计算,本文介绍了两种单相流沸腾模型。模型认为流动沸腾总传热量等于泡核沸腾和单相对流传热之和,其中泡核沸腾传热计算采用修正后的容积沸腾传热计算公式。BDL模型在Chen模型的基础上作了改进,考虑了冷却水局部流动参数及饱和状态的影响,适用于局部流动传热计算。     

低流阻系数轴流式止回阀的内部流场分析

为了设计公称直径为DN200的低流阻系数轴流式止回阀,并准确分析其压力损失和流阻特性,在其原有的结构基础上,用汇源法设计止回阀的阀芯结构,得到结构优化后的轴流式止回阀。基于FLUENT(商用计算流体力学)软件提供的标准k-ε两方程湍流模型,对结构优化后的轴流式止回阀进行三维流道数值模拟,求解出不同工况下的压力云图和速度流线图,计算出优化后的止回阀流阻系数在0.272以下,小于优化前的0.4。最后,总结出进口压力、进口速度与流阻系数之间的关系。计算结果表明:在止回阀流道结构保持不变的情况下,影响止回阀流阻系数的主要因素是进口平均速度,随着进口流速的增大,止回阀的流阻系数呈逐渐减小的趋势;在进口速度保持不变的情况下,进口压力的变化对止回阀的流阻系数影响较小。     

轴流泵内部流场的数值模拟

为更深入研究轴流泵并了解其流道内流场特性,结合南水北调东线工程某泵站模型能量试验数据,采用计算流体动力学软件Fluent, 在多重参考系坐标下,运用基于壁面律的RNG κ〖KG-*6〗 ε的湍流模型对模型泵进行数值模拟。 计算采用交错网格的有限体积法求解三维不可压Navier Stokes方程, 进口压力值选为0。通过计算预测了泵的水力性能,并与模型试验结果进行了比较,结果显示设计工况下数值预测与试验数据值吻合较好,非设计工况下偏差较大。     

轴流泵内气液两相流动的数值模拟

为进一步揭示轴流泵的气液两相流动的一般规律,基于ANSYS软件对轴流泵的气液两相流动三维流场进行数值计算与分析,研究了叶轮及出口导叶的压力面和吸力面的静压分布及气泡体积分布情况。结果表明,叶轮流道内,同等气泡体积分数下,当气泡粒径增大时,压力面上的气泡会由叶片出口处向着靠近轮毂处减少;而吸力面上的气泡会由进、出口处向着叶片中部靠近轮毂处聚集。气泡粒径不变时,当气泡体积分数增大时,叶片压力面上的气泡会由进口及轮缘处向着出口靠近轮毂处聚集;而吸力面上的气泡会由进、出口处向着叶片中部靠近轮毂处聚集。导叶流道内,同等气泡体积分数下,当气泡粒径增大时,叶片压力面上的气泡会由出口及轮缘处向着进口靠近轮毂处聚集,出口靠近轮缘处气泡越来越少;而吸力面上的气泡会由叶片进、出口向着叶片中部慢慢扩散。气泡粒径不变时,当气泡体积分数增大时,压力面上的气泡会由进口靠近轮毂处向着出口靠近轮缘处扩散;而吸力面上的气泡会由叶片进、出口向着叶片中部扩散。     

缸盖冷却水的单相流沸腾模型

针对缸盖水腔内的冷却水流动沸腾传热计算,本文介绍了两种单相流沸腾模型.模型认为流动沸腾总传热量等于泡核沸腾和单相对流传热之和,其中泡核沸腾传热计算采用修正后的容积沸腾传热计算公式.BDL模型在Chen模型的基础上作了改进,考虑了冷却水局部流动参数及饱和状态的影响,适用于局部流动传热计算.     

模型试验中的阵发性不稳定流态及折冲流——李家峡水电站左底孔试验中的两个问题

本文证实李家峡水电站左底孔不存在阵发性不稳定流态问题,模型上的这种不良流态是模拟条件引起的。文章分析了与折冲流有关的因素,如压差、压力和流速梯度以及渥奇面参数,进而提出了修改方案,基本解决了该孔存在的折冲流问题。     

结构化小球填充床内小球层流流动的周期性特征

采用CFD(计算流体动力学)方法全尺寸介观尺度下研究结构化小球填充床内的小球流动特性。重点是成列排列的小球填充床内流体流动的周期性特征。结果表明,小球填充床内时流体流动具有周期性特征,当颗粒Re(雷诺数)小于28.88时,整个填充床内表现出很好的对称性。当Re继续增大时,入口效应对孔隙内的流速分布的影响逐渐增大,周期性特征不断衰减。当Re增大到204.7时,入口效应对孔隙速度的影响扩展到上游入口段的2~3个单元。数值计算的有效性通过实验结果进行了验证,数值预测的速度分布与实验结果是一致的。     

Two-Phase Flow Distribution to Tubes of Parallel Flow Air-Cooled Heat Exchangers

Abstract

This paper addresses two-phase flow distribution phenomena in multiple header–tube junctions used in heat exchangers. Because of phase separation, it is very difficult to obtain uniform two-phase flow distribution to the branch tubes. The flow distribution is strongly influenced by the header orientation (horizontal or vertical) and the number of branch tubes. Other factors that influence the flow distribution are the flow direction in the header (upflow or downflow), the header shape and tube end projection into the header, and the location and orientation of the inlet and exit connections. The source of maldistribution is the flow in the dividing headers. Work performed by the authors and others (including patents) are discussed. The possibilities for eliminating two-phase flow maldistribution are identified and discussed. This investigation shows that solutions, which provide uniform flow distribution, are very design-specific. Change of the geometry or operating parameters will require modification of the design.     

超声波流量计和电磁流量计各自特点及区别比较

通过对超声波流量计和电磁流量计概论、工作原理、分类和工作性能区别的比较,揭示了中国现阶段两种最常用流量计的特征和不同优势.