涡流空气分级机圆弧形叶片转笼的设计

涡流空气分级机分级粒径主要受转笼转速与入口风速匹配关系的影响。入口风速一定时,转笼转速越高,分级粒径越小,但这会造成流场速度分布不均匀,而降低分级精度。利用Fluent软件对具有直叶片转笼结构的涡流空气分级机进行建模和数值模拟,分析转笼内流场特性,针对其流场不均匀及转笼入口冲角大等现象,对转笼叶片的形状及安装角进行改进,提出一种圆弧形叶片转笼的设计方法。通过数值模拟及物料试验对改进结果进行验证,数值模拟结果表明:圆弧形叶片转笼入口冲角减小,流道内流场更加均匀,分级粒径减小。碳酸钙分级试验结果与数值模拟结果吻合:设计工况即入口风速为12 m/s,转笼转速为1 200 r/min时,采用设计的圆弧形叶片转笼在保持分级精度不变的情况下,分级粒径减小了11.5%。     

Empirical study of classification process for two-stage turbo air classifier in series

The suitable process parameters for a two-stage turbo air classifier are important for obtaining the ultrafine powder that has a narrow particle-size distribution, however little has been published internationally on the classification process for the two-stage turbo air classifier in series. The influence of the process parameters of a two-stage turbo air classifier in series on classification performance is empirically studied by using aluminum oxide powders as the experimental material. The experimental results show the following: 1) When the rotor cage rotary speed of the first-stage classifier is increased from 2 300 r/min to 2 500 r/min with a constant rotor cage rotary speed of the second-stage classifier, classification precision is increased from 0.64 to 0.67. However, in this case, the final ultrafine powder yield is decreased from 79% to 74%, which means the classification precision and the final ultrafine powder yield can be regulated through adjusting the rotor cage rotary speed of the first-stage classifier. 2) When the rotor cage rotary speed of the second-stage classifier is increased from 2 500 r/min to 3 100 r/min with a constant rotor cage rotary speed of the first-stage classifier, the cut size is decreased from 13.16 μm to 8.76 μm, which means the cut size of the ultrafine powder can be regulated through adjusting the rotor cage rotary speed of the second-stage classifier. 3) When the feeding speed is increased from 35 kg/h to 50 kg/h, the "fish-hook" effect is strengthened, which makes the ultrafine powder yield decrease. 4) To weaken the "fish-hook" effect, the equalization of the two-stage wind speeds or the combination of a high first-stage wind speed with a low second-stage wind speed should be selected. This empirical study provides a criterion of process parameter configurations for a two-stage or multi-stage classifier in series, which offers a theoretical basis for practical production.     

Experimental Study of the Flow Field Inside a Whirling Annular Seal

The flow field inside a whirling annular seal has been measured using a 3-D Laser Doppler Anemometer (LDA) system. The seal investigated has a clearance of 1.27 mm, a length of 37.3 mm and is mounted on a drive shaft with a 50 percent eccentricity ratio. This results in the rotor whirling at the same speed as the shaft rotation (whirl ratio = 1.0). The seal is operated at a Reynolds number of 12000 and a Taylor number of 6300 (3600 rpm). The 3-D LDA system is equipped with a rotary encoding system which is used to produce phase averaged measurements of the entire mean velocity vector field and Reynolds stress tensor field from 0.13 mm upstream to 0.13 mm downstream of the seal. The mean velocity field reveals a highly three-dimensional flow field with large radial velocities near the inlet of the seal as well as a recirculation zone on the rotor surface. The location of maximum mean axial velocity migrates from the pressure side of the rotor at the inlet to the stiction side at the exit. Turbulence production is a maximum near the seal inlet as indicated by the rapid increase of the turbulence kinetic energy (κ). However, turbulence production and dissipation attain equilibrium fairly quickly with K remaining relatively constant over the last half of the seal.     

叶根倒角对跨音轴流压气机气动性能的影响*

为了获得叶根倒角对跨音轴流压气机气动特性影响规律,研究充分考虑了加工工艺及气动影响两方面,用倒角半径及最小角度两个参数确定倒角几何。研究基于Rotor37分析倒角参数对叶片几何的影响,并从整体性能及内部流场细节两方面对转子气动特性变化进行详细分析,获得了倒角参数变化对气动性能的影响规律。研究结果表明,相对于最小角度,倒角半径是影响转子性能的主要因素;倒角的存在不仅使得叶片根部马蹄涡的分布发生改变,且影响了出口通道涡的强度和尺度。此外倒角存在改变了叶根处的压力分布,使得前缘来流附面层有所增厚,导致根部的做功能力及转子性能下降。     

Aerodynamic performance analysis of partial admission dual row control stage at different working conditions

Aerodynamic performance of partial admission dual row control stage at the rated and off-designed operating conditions was numerically investigated using three-dimensional Reynolds-averaged Navier-Stokes (RANS) and k -ε turbulence model. The full scale computational model includes the four nozzle boxes, full first and second row rotor blade, as well as two admission guided vanes with consideration of the rotor tip clearance and stator diaphragm gland. The numerical results of the mass flow rate, power output and aerodynamic efficiency of the dual row control stage at the rated and off-designed conditions are well in agreement with the experimental data. The obtained results at rated condition show that the blocking segmental arc of guided vane increased the exit pressure of the upstream nozzle, which reduced the mass flow rate and changed the aerodynamic performance of the nozzle. The circumferential non-uniformity of aerodynamic parameters and partial admission losses increases with the decrease in the admission degree for the computed three operating conditions. The analysis of axial steam velocity shows that the trailing shedding vortex and the complex flow vortex in flow passages have a significant impact on the magnitude and direction of the axial steam velocity. Furthermore, the partial admission degree changed the proportions of the power output of two rotor blade rows. The lower partial admission degree leads to a larger proportion of the power output of the first rotating blade row. The detailed flow pattern in the partial admissions dual row control stage at different operating conditions is also illustrated.     

3D Particle image velocimetry test of inner flow in a double blade pump impeller

The double blade pump is widely used in sewage treatment industry,however,the research on the internal flow characteristics of the double blade pump with particle image velocimetry(PIV) technology is very little at present.To reveal inner flow characteristics in double blade pump impeller under off-design and design conditions,inner flows in a double blade pump impeller,whose specific speed is 111,are measured under the five off-design conditions and design condition by using 3D PIV test technology.In order to ensure the accuracy of the 3D PIV test,the external trigger synchronization system which makes use of fiber optic and equivalent calibration method are applied.The 3D PIV relative velocity synthesis procedure is compiled by using Visual C++ 2005.Then absolute velocity distribution and relative velocity distribution in the double blade pump impeller are obtained.Test results show that vortex exists in each condition,but the location,size and velocity of vortex core are different.Average absolute velocity value of impeller outlet increases at first,then decreases,and then increases again with increase of flow rate.Again average relative velocity values under 0.4,0.8,and 1.2 design condition are higher than that under 1.0 design condition,while under 0.6 and 1.4 design condition it is lower.Under low flow rate conditions,radial vectors of absolute velocities at impeller outlet and blade inlet near the pump shaft decrease with increase of flow rate,while that of relative velocities at the suction side near the pump shaft decreases.Radial vectors of absolute velocities and relative velocities change slightly under the two large flow rate conditions.The research results can be applied to instruct the hydraulic optimization design of double blade pumps.     

稳态偏航状态的风力机风轮气动力研究

根据水平轴风力机的特征参数建立了偏航致动盘的涡流柱面模型,用稳态偏航状态下的叶素动量理论计算出周向诱导流动因数。以Pitt-Peters模型为收敛条件,考虑了风轮的偏航角参数,建立计算水平轴风力机轴向诱导流动因数的计算模型,并用C++语言在VC环境下进行仿真计算,解决了气动设计和性能计算的关键问题,并通过实例验证了仿真过程的可行性。     

Average Velocity Measurements in Six Automotive Torque Converters Part II: Turbine Measurements

The internal flow fields of two automotive Plexiglas torque converter turbines with three different pumps were examined. A laser velocimeter was utilized to measure the velocity flow field at the turbine inlet and mid-planes in the six different geometry combinations; the stator was the same for all combinations. The turbine geometries differed only by the inlet blade angle, while the pump geometries differed only by the exit blade angle. The torque converter was operated at three different turbine/pump rotational speed ratios: 0.065 (near stall), 0.600, and 0.800 (near coupling point). For all geometries at the inlet plane the flow is fairly uniform in the blade-to-blade direction at all speed ratios. Velocities are most uniform in the core-to-shell direction at high speed ratios, but high velocities move near the shell at lower speed ratios. At the mid-plane, at low speed ratios the velocities are significantly higher near the pressure surface but as the speed ratio increases, the gradient decreases. At low speed ratios velocities are higher near the shell but this distribution becomes uniform at higher speed ratios. In general the flow became more uniform as the speed ratio increased. Variations in the pump exit blade angle had effects on both inlet and mid-plane velocity distributions and are documented. Variations in turbine inlet blade angle altered the inlet and mid-plane flow fields, but less so than the pump variations. A clockwise circulatory secondary flow pattern at the turbine inlet plane was observed for all geometries and, conversely, counter-clockwise circulatory secondary flow patterns at the mid-plane were recorded. Resulting vorticities were found to depend on geometries and speed ratios. The turbine leading edge incidence angles were found to strongly depend on the speed ratio, ranging from positive to negative, as well as pump and turbine blade angles.     

Measuring the total pressure in the relative motion of the flux behind a compressor rotor

A nontraditional method is proposed for measuring the total pressure behind the compressor rotor in relative motion of the gas flux. The operation of a rotary probe is considered. The flow pattern at the exit from the rotor’s blade channel is determined.     

Behavior of rotating stall cell in a high specific-speed diagonal flow fan

An experimental investigation was carried out to clarify unsteady flow fields with rotating stall cell, especially behavior of stall cell, in a high specific-speed diagonal flow fan. As its specific-speed is very high for a diagonal flow fan, its pressure-flow rate curve tends to indicate unstable characteristics caused by rotating stall similar to axial flow fan. Although for an axial flow fan many researchers have investigated such the flow field, for a diagonal flow fan little study has been done. In this study, velocity fields at rotor inlet in a high specific-speed diagonal flow fan were measured by use of a single slant hot-wire probe. These data were processed by using the ““Double Phase-Locked Averaging“ (DPLA) technique, i. e. phases of both the rotor blade and the stall cell were taken into account. The behaviors of stall cell at rotor inlet were visualized for the meridional, tangential and radial velocity.     

高压涡轮动叶吸力面气膜冷却特性研究

为了研究某航空发动机高压涡轮动叶吸力面的气膜冷却特性,通过数值模拟的方法,采用SST k-ω湍流模型,分析了高压涡轮动叶在静止和旋转条件下,吸力面气膜冷却效率的影响规律。结果表明:在静止条件下,相同主流湍流度时吹风比对吸力面气膜冷却效率影响显著,冷却效率随着吹风比的增大而减小;在小吹风比下,气膜冷却效率随着主流湍流度的增大而减小;在大吹风比下,气膜冷却效率随着主流湍流度的增大而增大。在相同湍流度和转速下,随着吹风比的增大,气膜向高半径偏转程度减小;在相同湍流度和吹风比下,随着转速的增大,气膜沿流向上的气膜覆盖面积减弱。优化结构的扇形气膜孔对叶片吸力面具有更好的冷却效果。     

旋流泵内液固两相流场的CFD-PBM耦合计算

为获得旋流泵内更为符合物理真实的液固两相流动特征,在传统欧拉(Euler)双流体模型基础上加载群体平衡模型(PBM),以考虑实际存在的颗粒聚并、破碎等动力学行为,与CFD耦合计算了不同流量、颗粒粒径及浓度下的液固两相流场,分析了颗粒存在对泵外特性的影响规律。计算结果表明:从进口到出口,叶片背面附近颗粒粒径明显增大;在叶轮出口位置,同一半径上,从叶片工作面到背面附近存在粒径梯度;在外缘部,沿轴向形成粒径梯度。与Euler模型计算结果对比发现:加载PBM模型后,颗粒总体浓度分布特征存在差异;同一轴截面上,颗粒浓度在中心部的分布基本相同,而在中间和外缘部位置出现差异。PBM模型计算得到的泵扬程、效率曲线更接近于实验值,证明基于CFD-PBM耦合计算的预测精度更符合实际。     

Limit vibration and pressure-pulsation cycles of the flow in the case of turbocharger rotor blade flutter

In this paper, the feasibility of limiting the flutter amplitudes of the axial turbocharger rotor blades by stabilizing the rotor speed is based on a study of experimentally confirmed required conditions. Two composite tasks are analyzed, the role of the contributions of structural damping and pressure pulsations in the air flow to the stability of the turbocharger blades’ vibrations and the parametric conditions for limiting the blade’s flutter amplitude at a stabilized rotor speed. It is shown that the blade’s flutter amplitude can be stabilized by increasing the quadratic damping of the acoustic diametral mode of the pressure pulsations in the air flow.     

基于FLUENT的后混合磨料水射流喷嘴内流场的数值模拟

以后混合磨料水射流喷嘴为研究对象,基于多相流动的欧拉模型,应用FLUENT流体分析软件对几种典型后混合磨料喷嘴的内流场进行数值模拟和仿真,得到压力分布、速度分布、湍流能量分布.结果表明:喷嘴内由于涡旋的形成损耗了部分能量,使得射流出口速度和动能明显降低;存在一个最优圆柱长度使得磨料出口速度达到最大值,其长度为喷嘴出口直径的23～37倍时,磨料得到最高的出口速度;喷嘴内流体紊动能的分布主要集中在喷嘴近壁区和几何形状变化较大的区域.     

航空燃油离心泵内流特性分析

针对航空发动机燃油离心泵内流特性研究,采用雷诺平均方法和滑移网格技术,在多工况下进行数值模拟,得到了内部流场细节和压力流量曲线。结果表明:由于流体绕过叶根时加速,可能出现局部低压区并导致气蚀;随着流量的增大,叶轮中相对速度增大,根据速度合成法可知,叶轮边缘出流速度随之减小,最终导致泵内静压降低;随着转速的提高,泵内速度和静压增大,且叶根附近出现局部高流速低压区并逐渐扩张,此区域也是局部低压区。根据压力流量曲线可知,随着流量的增大,泵输出的压力降低;随转速的提高,泵输出的压力升高;在低转速条件下,大流量运行无法实现。     

Experimental and computational studies on flow behavior around counter rotating blades in a double-spindle deck

Experimental and computational studies were performed to determine the effects of different blade designs on a flow pattern inside a double-spindle counter rotating mower deck. In the experimental study, two different blade models were tested by measuring air velocities using a forward-scatter LDV system. The velocity measurements were taken at several different azimuth and axial sections inside the deck. The measured velocity distributions clarified the air flow pattern caused by the rotating blades and demonstrated the effects of deck and blade designs. A high-speed video camera and a sound level meter were used for flow visualization and noise level measurement. In the computational works, two-dimensional blade shapes at several arbitrary radial sections have been selected for flow computations around the blade model. For three-dimensional computation applied a non-inertia coordinate system, a flow field around the entire three-dimensional blade shape is used to evaluate flow patterns in order to take radial flow interactions into account. The computational results were compared with the experimental results.     

Effect of cooling flow on thermal performance of a gas foil bearing floating on a hot rotor

This paper presents the measurements of the thermal behavior of a gas foil bearing (GFB) floating on a hot rotor in a tangential air injection cooling scheme. The cooling air was tangentially injected against rotor spinning into the inlet mixing zone of the test GFB. The hollow rotor was heated by a cartridge heater. The GFB temperatures were measured at intervals of 30 deg along the circumference of the axial center except for at 45 deg, where the cooling flow is injected. The rotor temperatures were measured near the GFB side ends using an infrared thermometer, which was calibrated with a thermocouple. Load cells measure the static load and bearing torque. The baseline rotor temperature was measured without GFB over the axial length at rotor speeds up to 15 krpm and for increasing heater temperatures up to 400 °C. The results showed relatively uniform rotor temperatures at the test journal GFB section, and severe heat convections on the rotor surfaces. The GFB and rotor temperatures were measured under a static load of 80 N for increasing heater temperatures of 100 °C, 200 °C, 300 °C and 400 °C and with increasing cooling flow rates of 100 liter/min, 150 liter/min, and 200 liter/min. The circumferential GFB temperatures showed the maximum temperatures at the loaded zone and the minimum temperatures in the unloaded zone. The increasing cooling flow effectively reduced both the rotor and GFB temperatures, showing a dramatic decrease with the smallest amount of cooling flow. GFB friction torque was measured for two test cases for the static load of 80 N at a rotor speed of 10 krpm: 1) A lift-off and touch-down operating cycle for increasing heater temperatures without the cooling flow, and 2) a continuous operation for the heater temperature of 400 °C with increasing cooling flows. In test case 1, the GFB friction torque decreased for higher heater temperatures due to a larger thermal expansion of the bearing housing than the rotor’s. In test case 2, the GFB friction torque decreased with increasing cooling flows due to strong cooling effects on the rotor temperature. The results imply that the tangential air injection increased the GFB clearance by directly cooling the rotor and effectively alleviating the rotor expansion; hence, the scheme is capable of an effective cooling for high temperature GFB applications, such as micro gas turbines.     

Numerical study on unsteadiness of tip clearance flow and performance prediction of axial compressor

Numerical calculations were performed to investigate unsteady features of tip clearance leakage flow in an axial compressor. The first stage rotor of a low speed axial compressor with a large tip clearance was examined. It was confirmed that the numerically calculated performance data were in good agreement with the experimentally measured performance data. Using frequency analysis, the flow characteristic near the casing induced by tip clearance leakage flow was found to be not associated with the rotating speed of the rotor. This characteristic is called rotating instability or self-induced unsteadiness. We found that the circumferential length scale of the rotating instability of the compressor was longer than a pitch of a blade passage; therefore, a multi-blade passage was adopted to study the flow structure more precisely. The flow characteristic was described by the frequency, the circumferential length, and the phase velocity, and was changed by operating points toward stall. The behavior of the flow was characterized by circumferentially traveling waves. Hence, the mechanism governing the development of the unsteady feature was further examined in terms of the rotating wave pattern of the pressure distribution. Furthermore, the unsteady feature of the tip clearance leakage flow affected the prediction of compressor performance by altering blockage, flow turning, and loss near the casing.     

旋风分离器排气管缩口半径优化的数值模拟

利用FLUENT中的RSM模型和DPM模型对不同排气管底口半径r的缩口式旋风分离器进行了内部流场的数值模拟。对结果的时均图进行分析,得到随着收缩半径r的减小,排气管入口面积在减小,轴向速度及切向速度均增加,速度的增加可使靠近中心的颗粒获得更大的离心力,因此被捕集的颗粒数增多。当半径r与排气管半径R比值为1~0.9时,分离效率提高不大,压降变化也较小,比值为0.8~0.5时,分离效率提高很多,同时能量损失也较大,在半径r逐渐减小的过程中,旋风分离器分离效率增加,压降增加。综合考虑,当r/R为0.6~0.5左右时,分离效率约为97%~98%,此时压降也较合理。     

Study on unsteady tip leakage vortex cavitation in an axial-flow pump using an improved filter-based model

The aim of the present investigation is to simulate and analyze the tip leakage flow structure and instantaneous evolution of tip vortex cavitation in a scaled axial-flow pump model. The improved filter-based turbulence model based on the density correction and a homogeneous cavitation model were used for implementing this work. The results show that when entering into the tip clearance, the backward flow separates from the blade tip near the pressure side, resulting in the generation of a corner vortex with high magnitude of turbulence kinetic energy. Then, at the exit of the tip clearance, the leakage jets would re-attach on the blade tip wall. Moreover, the maximum swirling strength method was employed in identifying the TLV core and a counter-rotating induced vortex near the end-wall successfully. The three-dimensional cavitation patterns and in-plain cavitation structures obtained by the improved numerical method agree well with the experimental results. At the sheet cavitation trailing edge in the tip region, the perpendicular cavitation cloud induced by TLV sheds and migrates toward the pressure side of the neighboring blade. During its migration, it breaks down abruptly and generates a large number of small-scale cavities, leading to severe degradation of the pump performance, which is similar with the phenomenon observed by Tan et al. [35].