Numerical simulation and analysis of lithium plasma during low-pressure DC arc discharge

Alkali metal DC arc discharge has the characteristics of easy ionization,low power consumption,high plasma temperature and ionization degree,etc,which can be applied in aerospace vehicles in various ways.In this paper,we calculate the physical property parameters of lithium vapor,one of the major alkali metals,and analyze the discharge characteristics of lithium plasma with the magnetohydrodynamic(MHD)model.The discharge effects between constant current and voltage sources are also compared.It is shown that the lithium plasma of DC arc discharge has relatively high temperature and current density.The peak temperature can reach tens of thousands of K,and the current density reaches 6 x 107 A m 2.Under the same rated power,the plasma parameters of the constant voltage source discharge are much higher than those of the constant current source discharge,which can be used as the preferred discharge mode for aerospace applications.

Optimization of the Gas Generator in Composite Power System with Tip-Jet Rotor

The key and bottleneck of research on the tip-jet rotor compound helicopter lies in the power system. Computational Fluid Dynamics (CFD) was used to numerically simulate the gas generator and rotor inner passage of the tip-jet rotor composite power system, studying the effects of intake mode, inner cavity structure, propellant components, and injection amount on the characteristics of the composite power system. The results show that when a single high-temperature exhaust gas enters, the gas generator outlet fluid is uneven and asymmetric;when two-way high-temperature exhaust gas enters, the outlet temperature of the gas generator with a tilted inlet is more uniform than that with a vertical inlet;adding an inner cavity improves the temperature and velocity distribution of the gas generator's internal flow field;increasing the energy of the propellant is beneficial for improving the available moment.

NONLINEAR INVERSE SIMULATION FOR THE MANEUVERING FLIGHT OF COAXIAL ROTOR HELICOPTERS

The maneuvering flight governing equations for coaxial rotor helicopters are established. By introducing induced velocity interference factor analysis, the coaxial rotor aerodynamic interference can be taken into account. With the combination of coaxial rotor helicopter control features and nonlinear inverse solution technique, the governing equations for maneuvering flight can be solved so as to determine helicopter control input, control force and moment, and helicopter body attitudes which are needed for performing the defined maneuver. Finally, as an example of this methods engineering application, the calculated results with level turn, lateral jink maneuvers are presented and simply analyzed.

Numerical Simulation of Aerodynamic Characteristics of Helicopter Rotor with Tip Slots

Effects of tip slots on the aerodynamic characteristics of helicopter rotor were investigated numerically by solving three-dimensional Navier-Stokes equations based on unstructured overset grids algorithm.Improved delayed detached eddy simulation (IDDES) based on the Spalart-Allmaras turbulence model and adaptive grid refinement technique were employed.Several slots in the rotor blade tip were designed on the base of Caradonna-Tung rotor to study the effect of tip slots.Numerical results show that tip slots are able to introduce the airflow from the leading edge and turn it in the spanwise direction to be ejected out of the face at the rotor blade tip,which can reduce the strength of the rotor blade tip vortex and accelerate the dissipation process.Although tip slots may lead to the decrease of airfoils' lift coefficient at the root of the rotor blade,it can increase the lift coefficient of airfoils at the rotor blade tip,so the lift of the rotor with tip slots is almost the same as that of the rotor without tip slots.In addition,tip slots can also reduce the intensity of the tip shock wave,which is beneficial to reduce the wave drag of the rotor.

Parameter Modeling and Kinematical Simulation for Rotor and Stator of Screw Pump

The research object used in the dissertation was screw pump, which was widely applied in engineering field. The analysis of end face profile formation was completed on its main working components, i.e., rotor and stator. With the purpose of finding optimal parameters to improve the efficiency of screw pump design, the key technologies involved in the parametric modeling of rotor and stator were analyzed. The three-dimensional (3D) design software SolidWorks was used for the secondary development and parametric modeling of rotor and stator. After that the simulation models of different kinds of screw pumps were established based on the cycloid type, variation coefficient, and screw head number. Finally the COSMOSMotion was used to analyze the motion characteristics on the equidistant line of rotor, including velocity and acceleration. This design and modeling method has been used in screw pump enterprises for design and development, laying the foundation for finite element analysis and further optimization of screw pump.

High-Order Discontinuous Galerkin Method for Hovering Rotor Simulations Based on a Rotating Reference Frame

An implicit higher ? order discontinuous Galerkin(DG) spatial discretization for the compressible Euler equations in a rotating frame of reference is presented and applied to a rotor in hover using hexahedral grids. Instead of auxiliary methods like grid adaptation,higher ? order simulations(fourth ? and fifth ? order accuracy) are adopted.Rigorous numerical experiments are carefully designed,conducted and analyzed. The results show generally excellent consistence with references and vigorously demonstrate the higher?order DG method's better performance in loading distribution computations and tip vortex capturing, with much fewer degrees of freedom(DoF). Detailed investigations on the outer boundary conditions for hovering rotors are presented as well. A simple but effective speed smooth procedure is developed specially for the DG method. Further results reveal that the rarely used pressure restriction for outlet speed has a considerable advantage over the extensively adopted vertical speed restriction.

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.

Numerical Simulation of the Wake Generated by a Helicopter Rotor in Icing Conditions

The wake generated by the rotor of a helicopter can exert a strong interference effect on the fuselage and the horizontal/vertical tail.The occurrence of icing on the rotor can obviously make this interplay more complex.In the present study,numerical simulation is used to analyze the rotor wake in icing conditions.In order to validate the overall mathematical/numerical method,the results are compared with similar data relating to other tests;then,different simulations are conducted considering helicopter forward flight velocities of 0,10,20,50,and 80 knots and various conditions in terms of air temperature(atmospheric temperature degrading from−12°C to−20°C or from−20°C to−26°C).The results indicate that the rotor aerodynamic performance(i.e.,the lift-to-drag ratio distribution of the rotor disc)drops significantly once the rotor undergoes ice accretion.More importantly,the icing exerts a different influence of the wake dynamics depending on the atmospheric conditions.Interestingly,the rime-ice firstly occurs on the inner portion of rotor blades and then diffuses outward along the blade radial direction with the decrease in atmospheric temperature.

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.

无人机系列化旋翼气动噪声特性对比研究

旋翼的气动噪声是各类旋翼无人机噪声的主要来源,为降低无人机整体噪声和提升其声隐身性能,文中针对某无人机的系列化等径旋翼开展定转速气动噪声特性的对比研究.分别建立各旋翼气动噪声特性预测大涡模拟计算模型,将获取的各旋翼表面压力脉动信息作为声学求解输入,基于FW-H方程计算了等距(3R)和不同方位的旋翼远场噪声特性并进行了试验验证,5个型号旋翼等距处总声压级仿真与试验结果误差不大于4.3%,气动噪声呈现明显的偶极子特性,气动噪声径向声压级明显高于轴向值,且不同旋翼的气动噪声声压级与旋翼转矩具有正相关关系,与旋翼升力间关系则不明显.

基于Simulation X的永磁外转子矿井提升机控制策略研究

针对传统矿井提升机存在机械效率低、传动系统复杂、设备维护成本较高等问题,本文提出了永磁外转子矿井提升机,将电动机内置于卷筒,省去了电动机、减速器和联轴器等部件,实现了电能到机械能的直接转换,大大提高了机械效率,简化了传动系统,降低了设备的维护成本。但电能直接驱动滚筒导致系统易受外部干扰,从而出现速度波动和转矩脉动,本文建立了永磁外转子矿井提升机数学模型,并研究常见的控制策略,利用Simulation X软件仿真研究永磁外转子提升机控制策略。结果表明,滑模控制算法改善了永磁外转子矿井提升机的启动特性,鲁棒性更好,抵抗外部干扰的能力更强,验证了控制策略的优势和效果。

大流量农业灌溉泵转子动力学特性研究

灌溉是保障农业稳定发展的手段,随着现代农业的发展,对灌溉水泵的需求日益增加。大流量灌溉泵因其独特的工作环境和要求,它的叶片通常具有扭曲度大和宽等特点。作为转子系统中重要的部分,叶轮及转子部件的变形与强度对灌溉泵整个系统的安全性能和效率都有很大影响。以大流量灌溉泵为研究对象,使用Ansys-Workbench软件对其大流量区进行有限元研究,对转子部件分别进行变形与强度分析和模态分析。结果表明,在流量为500 m^(3)/h时,叶片受最大等效应力为23.83 MPa,此时出现叶片最大形变值为0.341 mm,最大变形区域都出现在叶片边缘处。大流量工况下,对比不同流量工况的各阶固有频率,在各阶振型中流量大小与转子系统的固有频率没有显著关系,但不同材料明显地影响大流量灌溉泵的转子的固有频率。

工况参数对混输转子泵排出性能影响

混输转子泵是气液固三相混输工艺的关键设备,输送介质成分复杂,内部流动机理尚不明确。因此,基于动网格技术和Mixture多相流模型对混输转子泵内部进行数值模拟,分析了混输转子泵在不同工况参数下的性能变化规律。结果表明:气相与固相占比对混输泵性能影响不明显;转速对混输转子泵性能影响明显,转速增加,容积效率显著上升,流量脉动略微降低;随着压差的增加,出口流量降低,容积效率显著下降,流量脉动大幅上升;而在3个工况参数交互作用下,混输转子泵的性能波动明显,混输转子泵在低含气、高含砂、低转速、高压差工况时表现较差。研究结果对混输转子泵的深入研究和广泛应用提供了有价值的参考。

核主泵口环密封动力学特性数值研究

为了研究口环密封对核主泵转子动力学特性的影响,本文以“华龙一号”核主泵密封口环为研究对象,应用转子动力学理论,建立小扰动模型下的涡动转子动力学方程,基于CFD准稳态方法,对密封间隙域内部流场进行数值模拟,探究转速、压差及口环结构对转子动力学特性以其稳定性的影响。结果表明:转速和压差越大,涡动比对密封力的影响效果越显著,刚度系数、阻尼系数的绝对值呈增大趋势,转速对交叉刚度系数和交叉阻尼系数影响显著,平面密封和迷宫密封交叉刚度系数分别增加了6.92倍和4.13倍,交叉阻尼系数分别增加了15.4倍和6.25倍;压差对直接刚度系数影响明显,平面密封与迷宫密封直接刚度系数分别增加了6.2倍和9.1倍。同时迷宫密封对应的涡动系数Ω_(f)小于平面密封,稳定性优于平面密封结构。

含呼吸裂纹的多盘双转子系统振动特性探究

由于材料、工作环境等因素影响,以航空发动机为代表的旋转机械在工作过程中可能会产生裂纹故障,常见的裂纹类型为呼吸裂纹。为分析该故障对轴系振动特性的影响,基于某型双转子涡扇航空发动机,建立了包含风扇和多个轮盘在内的双转子—支承动力学数值仿真模型,使用Newmark-β法分别对不同裂纹相对深度和不同转速下的系统工况进行了数值仿真求解。结果发现:随着裂纹逐渐加深,转子高频分量愈加明显,系统稳定性下降;随着转速升高,系统出现了2X,3X分量,工频分量在一阶临界转速前后先增大后减小,轴心轨迹由不规则形状逐渐转变为圆形。

涡轮叶片装配智能优化算法

涡轮组件装配是发动机制造过程的重要组成部分,在装配过程中为保证涡轮叶片装配完成后的转子不平衡量符合设计标准,需对叶片进行分组试装等步骤,装配效率因此受到影响。为解决此问题,提出一种基于改进模拟退火算法的叶片装配序列优化方法。建立由轮盘自身不平衡量与叶片不平衡量相结合的数学模型,采用多邻域搜索机制,改进退火机制,增加升温、记忆模块等方法来改进算法,通过实例验证了算法的有效性,并与蝴蝶算法,天鹰算法,原始模拟退火算法进行比较,有效地降低了涡轮转子不平衡量。结果表明,改进的模拟退火算法能够有效的减少叶片装配后的不平衡量。为使该算法能够更方便的服务于装配现场,基于MFC框架开发一款叶片装配软件,为解决叶片装配需进行多次拆装以及装配效率低的问题提供了一种有效的方案。

基于车用永磁同步电机转子结构的电磁噪声优化仿真分析

针对目标电机低速加速段中存在明显类似“口哨”的高频噪声的问题及电机量产降本原则,将48槽8极峰值功率62 kW的乘用车前驱动电机作为案例进行电磁方案设计。基于设计指标及存在问题设计了定子结构相同内置式转子拓扑结构不同的优化方案,推导计算了两电机方案气隙磁场幅值波形时空分布方程及电磁力表达式,建立了两电机方案有限元模型及电磁-结构声场耦合模型,仿真分析比较两电机气隙磁密及径向电磁力谐波含量。基于仿真结果得到优化方案,在不牺牲电磁性能的前提下削弱了低速段加速过程的0阶6f1径向电磁力,并使磁钢用量从1.474 kg降低到了1.371 kg,实现了降本目的。最后分别制作样机进行实验验证,结果表明优化方案明显削弱了低速段径向振动,降低了24倍频电磁噪声,与仿真结果相吻合。

直升机ACF智能旋翼压电叠堆输出特性仿真分析

压电叠堆是ACF智能旋翼中后缘襟翼的致动元件,其输出性能的好坏直接影响后缘襟翼的偏转效率。基于COMSOL Multiphysics有限元平台,对全电极和叉指电极两种构型的压电叠堆进行了参数化建模,对叠堆自由位移和阻塞力两种典型输出特性进行了仿真分析,并利用理论进行了校验。结果表明,基于参数化建模的压电叠堆有限元模型具有良好的准确性,其计算结果与理论模型计算结果基本保持一致;两种构型压电叠堆的输出特性随激励电压的变化都是趋于线性的;相同激励电压下,同横截面积的叉指电极型压电叠堆的自由位移小于全电极型,减小比例与各陶瓷层活性区面积的缩减比例一致,而两种构型叠堆的阻塞力大小相当,叉指电极的尺寸缩进不会使得阻塞力明显降低。

异步电动机转子串电阻分级起动过程的SIMULINK仿真

利用 MATLAB/SIMULINK软件构造了绕线式异步电动机转子串电阻起动的仿真模型 。

串列不等直径水平轴风力机气动性能研究

为研究上游风力机叶轮直径增大和轮毂高度抬升对下游风力机气动性能影响,采用计算流体力学方法对串列水平轴风力机三维流场进行模拟,以揭示上游风力机叶轮尺寸增大和轮毂高度抬升对下游风力机气动性能影响规律。研究结果表明:增大上游风力机叶轮直径,会削减下游临近机组输出功率,增加机组在低频,1倍、2倍、3倍轴频推力脉动,增大机组疲劳载荷;随着风力机间距的增加,增大叶轮直径对12D范围外机组输出功率影响可忽略不计,但机组疲劳载荷在低频和1倍轴频仍有明显的增大。抬高上游机组轮毂高度,机组较近时,可使下游风力机避开一部分尾流,显著提高下游风力机的输出功率,但也会使风力机叶轮在旋转一周过程中产生较大的叶片推力脉动;当风力机间距较远时,抬高塔架高度有利于尾流恢复,进而提高下游机组输出功率,降低机组疲劳载荷。