Hybrid URANS/LES Method of Flow Fields in Axial-flow Compressor Rotor Rotor

Accurate and efficient prediction of the aerodynamic performance and flow details of axial-flow com-pressors is of great engineering application value for the aerodynamic design and flow control of axial-flow compres-sors.In this work,a delayed detached eddy simulation method is developed and applied to numerically simulate the tur-bulent channel flow and the aerodynamic performance of NASA Rotor 35.Several acceleration techniques including parallel implementation are also used to speed up the iteration convergence.The mean velocity distribution and Reyn-olds stress distribution in the boundary layer of turbulent channel flow and the aerodynamic performance curve of NASA Rotor 35 are predicted.The good agreement between the present delayed detached eddy simulation results and the available direct numerical simulation results or experimental data confirms the effectiveness of the developed meth-od in the accurate and efficient prediction of complex flow in turbomachinery.

Numerical Investigation of the Unsteady Flow in a Transonic Compressor with Curved Rotors

The unsteady 3D flow fields in a single-stage transonic compressor under designed conditions are simulated numerically to investigate the effects of the curved rotors on the stage performance and the aerodynamic interaction between the blade rows. The results show that, compared to the compressor with unurved rotors, the compressor under scrutiny acquires remarkable increases in efficiency with significantly reduced amplitudes of the time-dependent fluctuation. The amplitude of the pressure fluctuation around the stator leading edge decreases at both endwalls, but increases at the mid-span in the curved rotors. The pressure fluctuation near the stator leading edge, therefore, becomes more uniform in the radial direction of this compressor. Except for the leading edge area, the pressure fluctuatinn amplitude declines remarkably in the tip region of stator surface downstream of the curved rotor, but hardly changes in the middle and at the hub.

Combined Free Wake /CFD Methodology for Predicting Transonic Rotor Flow in Hover

A new combined wake /CFD methodology is used to include realistic wake effects in CFD solutions for the rotor flow in hover. The analytical method for predicting the hovering rotor wake is described to investigate the motion of the helical tip vortex. Beginning with the generalized wake model, a Semi Empirical Correction for the vortex core effect on the rotor wake is made. Then on the condition of circulation and wake geometry convergence, the free wake calculation is carried out. Finally, Euler equations are solved for transonic rotor flow employing Jameson’s finite volume explicit Runge Kutta time stepping scheme. The results are compared with the respective references and experimental data.

Flow Field Characteristics of the Rotor Cage in Turbo Air Classifiers

The turbo air classifier is widely used powder classification equipment in a variety of fields. The flow field characteristics of the turbo air classifier are important basis for the improvement of the turbo air classifier＇s structural design. The flow field characteristics of the rotor cage in turbo air classifiers were investigated trader different operating conditions by laser Doppler velocimeter（LDV）, and a measure diminishing the axial velocity is proposed. The investigation results show that the tangential velocity of the air flow inside the rotor cage is different from the rotary speed of the rotor cage on the same measurement point due to the influences of both the negative pressure at the exit and the rotation of the rotor cage. The tangential velocity of the air flow likewise decreases as the radius decreases in the case of the rotor cage＇s low rotary speed. In contrast, the tangential velocity of the air flow increases as the radius decreases in the case of the rotor cage＇s high rotary speed. Meanwhile, the vortex inside the rotor cage is found to occur near the pressure side of the blade when the rotor cage＇s rotary speed is less than the tangential velocity of air flow. On the contrary, the vortex is found to occur near the blade suction side once the rotor cage＇s rotary speed is higher than the tangential velocity of air flow. Inside the rotor cage, the axial velocity could not be disregarded and is largely determined by the distances between the measurement point and the exit.

The 3D Modeling of Blades of Multiphase Flow Helico-Axial Pump's Rotor Based on Solidworks

The structure of multiphase flow helico-axial pump＇s rotor and how to model the rotor, especially the blades of the rotor, based on the Solidworks software. More important, the principle of the blade design is mainly introduced. Under the guide of the principle, the 3D coordinates of the blade data points can be got by matlab programming. In the paper, the design step and the modeling step are particularly described through a concrete example.

Experimental investigation on flow characteristics in circular tube inserted with rotor-assembled strand using PIV

Rotor-assembled strand works as a typical tube insert to achieve heat transfer augmentation and scale inhibition in a heat exchanger.In this work, the PIV experiment regarding the flow fields in a circular tube inserted with rotor-assembled strand was conducted and the flow characteristics on transverse section and longitudinal section were analyzed.The results showed that swirling flow was produced in the tube inserted with rotors and it was particularly strong within the swing diameter of the rotor on the section that contains the rotor;the average turbulence intensity and the radial velocity were improved notably; the velocity vectors on the longitudinal section remained along the direction of a straight line; both the swirling flow and average turbulence intensity were higher for the rotor with three blades than for the rotor with two blades except that the radial velocity was approximate, but they were all reduced by enlarging the lead of the rotor.Characterization of the flow patterns in a circular tube contributes to understanding the heat transfer efficiency and scale inhibition performance of the rotor-assembled strand and provides guidance for its application.

INVESTIGATION OF INFLUENCE OF DYNAMIC INFLOW ON ROTOR FLAP/LAG STABILITY

A method taking dynamic inflow into account is developed to analyse the rotor flap/lag stability and coupled rotor/body stability in hover. The method is verified bystability experiments. The influence of dynamic inflow on rotor flap/lag stability is investigated in different conditions. The inflow mode is identified by a new way. The workdone by inflow on other degrees of freedom is investigated to give a physical explanation ofthe effect of dynamic inflow.

Design and Analysis of a Dual Rotor Turbine with a Shroud Using Flow Simulations

This paper describes the flow simulation of a dual rotor, three-bladed wind turbine module with a shroud to determine its performance. The parameters that were evaluated are the effects of adding a second rotor, wind speed, distance between the two rotors, the size of the front rotor and the shroud. The results were obtained by using the Solid Works 2015 flow simulation program. Also, the benefits and cost issues for wind generating systems are illustrated.

Rotor performance enhancement by alternating current dielectric barrier discharge plasma actuation

An experimental system was established to explore the plasma flow control effect for helicopter rotors in hover mode.With the plasma actuator applied at the leading edge of the rotor blades,alternating current dielectric barrier discharge(AC-DBD) plasma actuation was generated by a sinusoidal AC high-voltage generator.By direct force measurement,the influence of actuation parameters on the aerodynamic performance of the rotor was investigated at a tip Reynolds number of 1.7 × 105.AC-DBD actuation can delay the blade stall to more than 3° with a 20%increase of about in the thrust coefficient at the post-stall pitch.At a constant motor power driving the rotor,AC-DBD actuation could reduce the rotor’s torque at the stalled pitch and increase the rotational speed of the rotor.Also,AC-DBD actuation could maintain a relatively high hover efficiency of the rotor at large collective pitches.In a wide range of actuation parameters,AC-DBD plasma actuation could improve the rotor’s aerodynamic performance at large blade pitches.High-speed photography of the tuft motion on the blade’s upper surface showed that AC-DBD plasma actuation could promote the reattachment of the blade’s separation flow.

轴流式水轮发电机组不对中-碰摩耦合故障振动特性分析

针对轴流式水轮发电机组因联轴器偏角不对中引起的碰摩转子-转轮系统振动问题,基于修正的LuGre摩擦模型,该研究推导了联轴器不对中故障下转轮叶片碰摩力表达式。在此基础上,搭建了综合考虑不平衡磁拉力等外激励作用下系统动力学模型。采用数值方法研究了不对中角度对系统振动特性的影响,并结合Floquet理论分析了以转速为控制变量的系统周期解稳定性。结果表明,不对中的存在增大了系统发生失稳可能性,显著改变了系统动态特性。此外,不对中角度对转子与转轮振动响应的影响具有较大差异,随着不对中角度的增加,转轮振动变化明显且碰摩程度较为恶劣。该研究结果可为轴流式水轮发电机组安全运行及稳定性分析提供有益借鉴。

Aerodynamic Coupling Analysis of Counter⁃rotating Propfan and Inlet Flow Field

Taking a propfan engine as the research object,the CFD method was used for 3D modeling and unsteady slip flow for numerical calculation.The propfan rotation domain and the nacelle outside flow domain were meshed by using the partition splicing grid technology.Used the Reynolds⁃averaged of N⁃S equation,the Reynolds stress term uses the RNG turbulence model;and based on the slip grid method,numerical calculation of the flow field with different Mach numbers,front and rear blade angles and engine state were carried out;and the change law of propeller fan characteristics and the influence of slip flow on the inlet flow field were analyzed.The blade angle was the key parameter of the propeller fan characteristic conditions.When the blade angle increases from 41°to 50°,the thrust coefficient increases by 31.2%,and the power coefficient increases by 33.4%;in the climbing state of the propeller fan,the maximum total pressure distortion at the inlet port of 6.8%;the cross section is less affected by the slip flow of the propfan;and the pressure distribution is relatively uniform,but the area of the flow channel is small.The research results can provide a solution for the matching of the counter⁃rotating propeller fan and the engine and the arrangement of the air inlet measuring rake.

基于半解析涡环模型的农用单旋翼直升机流场快速计算

农业航空领域中,定量获取风场(流场)速度分布对单旋翼直升机辅助授粉作业、农药施用效率提升具有重要意义。基于此提出一种半解析理论方法能够快速完整计算单旋翼流场速度。以涡环模型为基础,将农用直升机旋转桨盘下的尾涡系等效为涡环连续叠加所形成的圆柱涡面,再由涡环速度诱导公式半解析计算直升机旋翼空间各点速度。理论模型与仿真和文献试验数据比较,结果表明:涡环模型简单快速,普通计算机(CPU 2 GHz,内存2 GB)上2.8 s完成计算;悬停时与计算流体力学仿真结果下洗速度径向平均误差小于1.9 m/s,平均相对误差小于39.1%,轴向平均误差小于2.26 m/s,平均相对误差小于54.6%;悬停时,诱速从中央往桨尖递增;前飞时,平飞速度越大诱速越小;流场主要影响因素依次为前飞速度、旋翼半径、飞机总重、空气密度。为定量计算农用直升机旋翼风场、辅助授粉作业和田间施药喷头布置提供一种快速方法和参考。

气隙取气斜流式通风汽轮发电机转子的温度场研究

为了研究气隙取气斜流式通风汽轮发电机转子的温度场的分布特点,本文依据传热学基本理论,建立了三维全域的转子耦合计算模型,利用有限体积法对模型中的控制方程进行数值计算与分析。首先分别对转子槽内铜排、匝间绝缘、转子铁芯进行整体温度场的分析,研究其温度分布的异同点,然后对比了各风区中心截面的温度,最后研究铜排沿轴向和周向的温度分布特点,分析了温度分布趋势的产生原因。结果表明:转子温度场沿轴向呈波浪形分布,转子中心截面、磁极中心线及其垂直线高度对称,最高温度出现在靠近汽端和励端的出风区;槽内越靠下的铜排,温度峰谷差越小,温度不均的程度越小;在周向上,靠近大齿铜排的温度比其余铜排温度略低。本文的结论可为气隙取气斜流式通风汽轮发电机的深度调峰运行和转子结构优化提供参考。

基于流固耦合的压气机转子叶片非同步振动分析

压气机转子叶片非同步振动是近年来发现的一类新气动弹性问题,表现为叶片振动频率与转频不同步且具有锁频现象,严重影响航空发动机的可靠性和运行安全,目前对其产生机理并不完全清楚.为了深入研究压气机内不稳定流动与叶片非同步振动之间的耦合机制,基于时间推进的方法建立了多级压气机转子叶片全环的双向流固耦合模型,数值研究了刚性叶片与非同步振动柔性叶片的非定常流场、气流激励频率和结构响应特征,揭示了压气机转子叶片非同步振动的流固耦合机制.结果表明:近失速工况下,转子叶尖吸力面径向分离涡的周期性脱落及再附过程是导致叶尖压力剧烈波动的主要原因,其3倍谐波激励频率与转子一阶弯曲固有频率接近,提供了叶片非同步振动的初始气流激励源.叶片非同步振动发生时,位移响应表现为等幅值的极限环特征,振动以一阶弯曲模态主导,径向分离涡产生的非整数倍气流激励频率及其谐波频率最终锁定为叶片一阶弯曲固有频率,非同步振动的运动胁迫使得相邻通道叶尖流场周向趋于一致.研究成果及对叶片非同步振动流固耦合机制的认识可为压气机内部不稳定流动诱发的叶片振动失效分析提供有益参考.

黏温黏压下径向柱塞泵滑靴副温度分布与泄漏量分析

针对高压大排量径向柱塞泵滑靴副摩擦失效和泄漏问题,以XDP1000型径向柱塞泵为例,对滑靴副温度分布与泄漏量进行了流场仿真和数值计算。首先,根据滑靴柱塞组件运动学特性分析,求解了滑靴偏转角变化规律,并通过建立滑靴副不同通道流量计算公式的方式,建立了滑靴副静压支承特性方程;然后,建立了滑靴副泄漏功率损失和摩擦功率损失模型,求解了滑靴副最佳油膜厚度,并分析了最佳油膜厚度的变化规律;最后,在考虑了油液黏温黏压特性的基础上,通过流场数值计算的方式,研究了滑靴副温度分布与泄漏量随径向柱塞泵工况参数的变化规律。研究结果表明:额定工况下,滑靴副最佳油膜厚度值约为14μm,滑靴副最佳油膜厚度值随着转子转角的增大而增大,随着工作压力和温度的增大而减小;滑靴运动方向侧油膜温度较另一侧高13 K,滑靴副温度值基本不受工作压力的影响,而随着转速的增大而升高;滑靴副阻尼孔泄漏量较滑靴边界泄漏量大0.02 kg/s,而且泄漏量随着压力、转速和油液温度的增大而增大。该研究结论可为高压大排量径向柱塞泵滑靴副设计及优化提供参考。

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%。

罗茨真空泵新型偏心渐开线型不对称转子的构建与性能研究

罗茨转子作为罗茨真空泵的重要组成部件,对罗茨真空泵性能影响极大。为了解决传统渐开线型转子在渐开线与圆弧连接处存在不光滑连接点,导致泄漏加剧,运行效率下降的问题,文章采用偏心渐开线与齿顶、齿根圆弧平滑相连,提出了一种偏心渐开线型不对称转子。建立了偏心渐开线型不对称转子的几何模型,分析了转子的几何参数对面积利用率等性能的影响。结果表明:随着圆心角增大及节圆半径减小,所提出的偏心渐开线型不对称转子的面积利用率提高;与传统渐开线型转子相比,所提出的偏心渐开线型不对称转子每转排量提升了17.2%,出口流量脉动降低9.8%,出口压力脉动降低7.9%。研究内容对罗茨真空泵的发展具有重要的意义。

不同转子轴向间隙下双螺旋轴流泵的内部流动特性

通过改变两螺旋转子之间的轴向间隙(1、5、10 mm),研究双螺旋轴流泵在不同转子轴向间隙下的内部流动特性。基于CFD模拟平台,采用浸入实体法,运用N-S方程和标准k-ε湍流模型,对不同轴向间隙和不同工况下的瞬态特性进行数值模拟,得到双螺旋泵在不同转子间隙下各过流部件在运转过程中的瞬态流动特性。结果表明:转子间隙为1 mm时泵的扬程最高,增大转子间隙(5和10 mm)泵的扬程依次减小;1 mm间隙下泵的升压性能最好,但流体在刚进入转子域出现了明显的负压现象,间隙增大后转子内抗堵塞能力增强,负压现象得到改善;双螺旋轴流泵的主要泄漏区域在转子啮合区,随着转子轴向间隙的增大,啮合区的速度增大,出现较明显的泄漏;双螺旋泵的扬程与流量成反比,随着设计流量的增大,3种间隙泵的扬程均逐渐减小。

Savonius型转轮三角阵列减流性能研究

为了助力海洋牧场减流防护工程,研究Savonius型转轮阵列减流性能。作者建立Savonius型转轮三角阵列尾流场数值模型,并通过水池实验验证准确性,基于可靠数值模型探究转轮阵列尾涡减流机理,研究三角阵列结构参数LX、LY,以及动力参数TSR、初始流速、旋向对整体减流性能的影响规律。结果表明,下游转轮产生的涡流呈现非对称分布,并且产生更多涡流的转轮拥有更好的减流效果。另外,LX为3D和LY为2D时减流性能最佳。最后对比发现,在叶尖速比为0.9~1.1减流效果更好;初始流速大小不影响减流效果;下游转子对称分布时,随着上游转子改变旋转方向,减流效果出现明显差异。

燃气轮机透平转静盘腔内流动与传热研究进展

转静系盘腔是燃气轮机二次空气系统中的重要组成部分,盘腔内流动和传热特性对整机安全稳定运行十分重要。随着燃气透平进口温度的不断提升,对透平冷却设计的要求不断提高,透平盘腔流动换热特性研究也越来越受关注。研究人员从流动与换热两个方面对转静系盘腔进行实验测量和数值模拟研究,形成相对比较成熟的研究体系。总结近年来燃气透平转静盘腔流动传热及冷却的相关研究进展,根据结构的不同分别对中心进气和预旋进气转静系盘腔及转静系盘腔的轮缘密封进行介绍,分析3种不同盘腔结构内部流动型态,介绍了预旋系统结构和轮缘密封结构对盘腔内流动传热特性影响的相关实验与数值研究现状。最后,基于当前研究热点和发展趋势,总结并展望了转静系盘腔未来研究的发展方向。