Numerical Investigations on Dynamic Stall Characteristics of a Finite Wing

The paper examines the dynamic stall characteristics of a finite wing with an aspect ratio of eight in order to explore the 3D effects on flow topology,aerodynamic characteristics,and pitching damping.Firstly,CFD methods are developed to calculate the aerodynamic characteristics of wings.The URANS equations are solved using a finite volume method,and the two-equation k-ωshear stress transport(SST)turbulence model is employed to account for viscosity effects.Secondly,the CFD methods are used to simulate the aerodynamic characteristics of both a static,rectangular wing and a pitching,tapered wing to verify their effectiveness and accuracy.The numerical results show good agreement with experimental data.Subsequently,the static and dynamic characteristics of the finite wing are computed and discussed.The results reveal significant 3D flow structures during both static and dynamic stalls,including wing tip vortices,arch vortices,Ω-type vortices,and ring vortices.These phenomena lead to differences in the aerodynamic characteristics of the finite wing compared with a 2D airfoil.Specifically,the finite wing has a smaller lift slope during attached-flow stages,higher stall angles,and more gradual stall behavior.Flow separation initially occurs in the middle spanwise section and gradually spreads to both ends.Regarding aerodynamic damping,the inboard sections mainly generate unstable loading.Furthermore,sections experiencing light stall have a higher tendency to produce negative damping compared with sections experiencing deep dynamic stall.

Numerical Investigation into the Transient Behavior of the Spike-Type Rotating Stall for a Transonic Compressor Rotor

In this paper,a numerical investigation into a spike-type rotating stall process is carried out considering a transonic compressor rotor(the NASA Rotor 37).Through solution of the Unsteady Reynolds-Averaged Navier-Stokes(URANS)equations,the evolution process from an initially circumferentially-symmetric near-stall flow field to a stable stall condition is simulated without adding any artificial disturbance.At the near-stall operating point,periodic fluctuations are present in the overall flow of the rotor.Moreover,the blockage region in the channel periodically shifts from middle span to the tip.This fluctuating condition does not directly lead to stall,while the full-annulus calculation eventually evolves to stall.Interestingly,a kind of“early disturbance”feature appears in the dynamic signals,which propagates forward ahead of the rotor.

The Spike-Type Solution of Second-Order Semilinear Differential Equation with Integral Boundary Conditions

A singularly perturbed second-order semilinear differential equation with integral boundary conditions is considered. By the method of boundary functions, the conditions under which there exists an internal transition layer for the original problem are established. The existence of spike-type solution is obtained by smoothly connecting the solutions of left and right associated problems, and the asymptotic expansion of the spike-type solution is also presented.

Experimental investigation of dynamic stall flow control using a microsecond-pulsed plasma actuator

To alleviate the performance deterioration caused by dynamic stall of a wind turbine airfoil,the flow control by a microsecond-pulsed dielectric barrier discharge(MP-DBD) actuator on the dynamic stall of a periodically pitching NACA0012 airfoil was investigated experimentally.Unsteady pressure measurements with high temporal accuracy were employed in this study,and the unsteady characteristics of the boundary layer were investigated by wavelet packet analysis and the moving root mean square method based on the acquired pressure.The experimental Mach number was 0.2,and the chord-based Reynolds number was 870 000.The dimensionless actuation frequencies F+ were chosen to be 0.5,1,2,and 3,respectively.For the light dynamic regime,the MP-DBD plasma actuator plays the role of suppressing flow separation from the trial edge and accelerating the flow reattachment due to the high-momentum freestream flow being entrained into the boundary layer.Meanwhile,actuation effects were promoted with the increasing dimensionless actuation frequency F+.The control effects of the deep dynamic stall were to delay the onset and reduce the strength of the dynamic stall vortex due to the accumulating vorticity near the leading edge being removed by the induced coherent vortex structures.The laminar fluctuation and Kelvin-Helmholtz(K-H) instabilities of transition and relaminarization were also mitigated by the MP-DBD actuation,and the alleviated K-H rolls led to the delay of the transition onset and earlier laminar reattachment,which improved the hysteresis effect of the dynamic stall.For the controlled cases of F+=2,and F+=3,the laminar fluctuation was replaced by relatively low frequency band disturbances corresponding to the harmonic responses of the MP-DBD actuation frequency.

机匣开槽控制喷水推进器不稳定流动的数值研究

针对喷水推进器小流量工况下的驼峰区不稳定流动,采用计算流体力学方法研究了其失稳特性。结果表明,随着流量的减少,推进泵的扬程和效率显著下降,扬程曲线在0.42Qd~0.8Qd范围内呈现出正斜率的驼峰特性,同时内部流场变得紊乱,并出现流动分离和回流等现象。为了改善这一不稳定流动,采用了机匣开槽技术进行流动控制,使驼峰现象得到明显改善。在最佳槽体结构参数下,深度失速工况点的扬程和效率分别比原模型提高了约147.6%和70.3%。机匣开槽一方面能够对进口来流进行整流,起到减少预旋和增大轴向进流速度的作用,另一方面可以抑制主流区漩涡的形成以及叶轮进口位置的低频压力脉动。

固定转捩对不同系列及厚度翼型气动性能的影响研究

为探究翼型表面污染对其气动性能的影响,基于SST k-ω模型对DU、NACA44XX系列的不同厚度翼型的气动性能进行数值模拟,确定两系列翼型的固定转捩敏感位置,分析固定转捩对两系列及不同厚度翼型气动参数、失速特性及内流特征的影响。结果表明:不同的气动外形会明显改变翼型的转捩敏感位置,但相对厚度的变化不会对其产生影响,DU和NACA44XX系列翼型吸力面和压力面上的转捩敏感位置分别位于1%c、5%c处及1%c、9%c处;NACA44XX翼型受固定转捩的影响相较于DU翼型更大,并随厚度的增大其影响更加显著;相对厚度增大导致固定转捩位置附近的高涡量区和整体涡团尺寸进一步增大,气动外形和相对厚度对固定转捩敏感度的影响主要体现在尾缘处的分离涡。

过失速重新定向机动过程气动特性建模

以过失速重新定向技术为基础的自翻转越肩飞行器与传统越肩发射飞行器相比,具有响应时间短、机动性能高、射程远等优势。本文针对飞行器过失速重新定向机动过程,基于CFD动态计算数据分析了该过程中的飞行器气动特性,通过改进微分方程模型成功描述了机动过程中的迟滞环效应,同时验证了最小二乘支持向量机方法在此建模问题中的适用性。本文的建模方法可以准确捕捉飞行器过失速重新定向机动过程中的非线性非定常气动特性,为飞行器过失速重新定向机动控制律设计提供模型基础。

边界层和压力滞后对翼型动态失速性能的影响

为优化动态失速模型经验常数,提升动态失速发生时翼型气动性能预测精度,该文基于B-L动态失速模型,结合内蒙古工业大学风能太阳能利用技术教育部重点实验室风洞实验数据,探究压力滞后及边界层滞后时间常数对翼型动态失速性能的影响。主要结论如下:压力滞后与边界层滞后时间常数对动态升力系数的影响较大且与平均攻角有关。当平均攻角相对较小且气流处于附着流动与分离流动之间时,适当减小时间常数可使动态失速模型计算结果更接近实验值;当平均攻角相对较大,气流处于分离流动与完全分离流动时,可适当增大时间常数值。压力滞后与边界层滞后时间常数对动态阻力系数的影响不显著。动态升力系数仅在攻角逐渐减小的完全分离流动过程中,随着边界层滞后时间常数的增大而减小。

多翼离心风机旋转失速阶段压力脉动分析

为了研究多翼离心风机在旋转失速阶段的压力脉动特性,以多翼离心风机为研究对象,利用Creo软件对其进行三维建模,并对模型进行网格划分,进行非定常数值计算.在叶轮出口不同周向、径向以及轴向位置设置监测点,分析旋转失速工况下风机内部压力脉动规律,计算结果表明:隔舌处监测点的压力系数最大,且随着流量的减小,压力脉动剧烈程度增大;叶轮出口受叶轮与蜗壳之间动静干涉影响,压力系数幅值最大,往蜗壳壁面径向移动,压力脉动程度减弱;压力脉动规律受轴向位置变化影响较小,旋转失速程度的变化会引起压力脉动的变化,旋转失速越强,压力脉动越剧烈,低频脉动范围越广,失速频率幅值越高.

基于拉格朗日功能平衡法的单轨吊失速保护器触发理论分析

通过假设分步法从机器人学的角度对单轨吊机车失速保护器触发装置进行运动学分析,并对点位进行了详细描述。采用拉格朗日功能平衡法对失速保护器触发机构中的滑动轴位移状况建立了完整的动力学数学模型,通过该模型可以描述在运动过程中的滑动轴位移与运行速度、各部件参数之间的关系。借助Adams软件构建虚拟样机模型进行动力学仿真分析,得出所需的速度-位移仿真结果图。分析结果表明,滑动轴的位移与运行速度有关,当运行速度到达所设定临界值2 m/s时,滑动轴能够伸出足够长度以满足失速保护工作要求,符合数学模型的预期计算。

矿用对旋风机旋转失速信号特征识别与提取

针对旋风机旋转失速信号特征的识别与提取,提出了一种参数优化的变分模态分解(VMD)方法。首先,为了消除人为选择VMD参数的影响,提出一种以平均包络熵为目标函数的蛙跳优化算法,对VMD算法的模态个数K和惩罚因子α进行优化选取,实现了参数K和α的合理自动选取;然后,通过模拟信号验证了参数优化后的VMD方法的有效性;最后,利用参数优化的VMD方法对风机失速信号进行处理和分析,研究风机失速的频谱特性,并与经验模态分解(EMD)结果进行对比分析。研究结果表明:与EMD方法相比,参数优化的VMD方法在处理模态混叠方面更具有优势,其处理效果明显优于EMD,分解得到的IMF分量个数也少于EMD,易区分特征频率;另外,以优化获取的参数组合处理风机的失速信号时,能够很好地揭示失速特征频率在失速发展过程中的变化规律,对应于频率分量的波动,从大尺度的频率波动转变为小尺度的频率波动。

不同叶顶弯曲对离心叶轮性能影响机理

面对现代发动机对离心叶轮性能需求不断提高的背景,叶顶弯曲具备有效改善离心叶轮气动特性的能力,本文通过数值模拟的方式对不同叶顶弯曲方向、弯曲形式、弯曲程度的压气机性能进行预测,基于仿真结果对不同流动状态下压气机内部流场进行分析,给出了叶顶弯曲压气机性能变化机理。结果显示:负弯叶轮有助于提升压气机峰值效率,提高压气机堵塞流量。正弯叶轮则在损失部分效率的情况下,使压气机失速裕度得到提升。弯曲叶轮主要通过改善叶顶前缘载荷,重构叶轮通道内静压分布,从而削弱激波强度、减少二次流损失、抑制低能涡发展,达到提升压气机性能的目的。本文研究结果可为离心压气机叶片改型设计提供参考。

受控制律影响的电传运输机飞行品质试飞技术

针对电传运输机控制律设计特点,该文分析保护功能、自动配平功能等飞控功能对飞行品质试飞科目的影响,梳理受影响的关键试飞科目,并根据影响情况,适应性提出受控制律影响的运输机失速特性、抖振边界、空中最小操纵速度、高速特性等科目改进的试飞方法,总结试飞过程中的问题和经验,突破受电传控制律影响的飞机飞行品质关键科目试飞技术,为后续电传运输机飞行品质试飞提供参考。

引气量对多级轴流压气机性能影响的数值研究

以NASA 74A压气机前3.5级为研究对象,利用源项法探究级间引气量变化对压气机总体性能和内部流动的影响。结果表明:引气量越大压气机总体特性变化越显著,10%引气量下压气机流量范围拓宽25.72%,相比于未引气的压气机最高效率点效率增加5.6%,压比增加2.76%,而引气后进口气流冲角减小以及叶背处流动分离减弱所带来的气体流通量的增加是效率提升的主要原因;引气使得压气机稳定裕度升高,当最佳引气量8%时其稳定裕度增大21.80%;引气提高了压气机进口流量,但两者变化量不完全一致,在最高效率点处引气,引气量与进口质量流量增加量基本相等,然而,当低于最高效率点流量时,小流量点的增加量大于引气量,而大流量点则相反,这决定了出口流量的增减,影响了压气机总压比;引气对于气流周向角度影响更大,对径向角度的影响主要集中于引气位置附近。

涡扇发动机高原起动供油调整规律研究及故障分析

以某型涡扇发动机高原起动试验为研究对象,通过建立关键事件方式建立起动调整策略分析方法,总结分析了高原起动特点及起动供油量的调整规律,并针对发动机起动过程中出现的几种典型的失速、热悬挂失败案例,分析获得了起动失败的原因。结果表明:高原冷态起动失败主要为起动机脱开后发动机失速为主;热态起动失败主要为低压转子阻力矩增大导致热悬挂为主;起动供油调整规律为起动第二阶段减小供油量,起动第三阶段增加供油量。并提出了提升高原起动成功率的建议,可为发动机高原使用提供参考。

附面层吸入条件下非轴对称静子对风扇流场影响数值研究

附面层吸入导致进气道与风扇气动交界面处产生严重的总压、旋流畸变,进而使得风扇效率、稳定性降低,是制约其应用的主要问题之一。为了提高风扇的抗畸变能力,本文对风扇静子进行了非轴对称设计和数值仿真计算。结果表明:相较于原型风扇,非轴对称静子效率提高0.31个百分点,失速裕度提高50.5%,风扇内部流场有明显改善,扩压因子减小,畸变区静叶叶尖吸力面角区分离范围显著降低,叶片通道通流能力上升。非轴对称静子改型方案通过改变畸变区静叶进口几何角与弦长,使静叶冲角基本不变,稠度增加,气流在吸力面上不易发生分离,从而使得角区分离范围减小,流动损失降低,风扇性能提升。

Flow Field Improvement by Bowed Stator Stages in a Compressor with Different Axial Gaps Under Near Stall Condition

The outlet flow fields of a low-speed repeating-stage compressor with bowed stator stages are measured with five-hole probe under the near stall condition when the rotor/stator axial gap varies. The performances of the straight stator stages are investigated and compared to those of the bowed stator stages. The results show that using bowed stator stages could alleviate the flow separation at both upper and low corners of the suction surface and the endwalls, and decrease the losses along the flow passage as well as the outlet flow angle. As the rotor/stator axial gap decreases, although the diffusion capacity of the compressor increases obviously, the outlet flow field in the straight stator stages deteriorates quickly. By contrast, little changes occur in the bowed stator stages, indicating that as the rotor/stator axial gap decreases, improved performance is achieved in the bowed stator stages.

基于深度算子神经网络的翼型失速颤振预测

失速颤振是弹性结构大幅俯仰振动与动态失速气动力耦合所发生的一种单自由度失稳现象,需有效预测其失稳分岔速度与失稳后的极限环振荡幅值.针对NACA0012翼型大幅俯仰运动气动力预测问题,发展了由嵌入门限循环单元或长短时记忆神经网络单元的分支网络(branch net)和主干网络(trunk net)组成的深度算子神经网络(deep operator network, DeepONet)结构.通过给定大幅俯仰运动下的动态失速CFD气动力数据对深度算子神经网络参数进行训练,建立了高精度动态失速气动力的数据驱动模型,并有效预测其他俯仰运动下的非定常气动力.更进一步,将基于深度算子神经网络的非定常气动力数据驱动模型与结构动力学方程耦合,采用数值积分方法预测失速颤振的失稳分岔速度和不同速度下的极限环振荡特性.结果表明,在动态失速气动力预测精度方面,与普通循环神经网络相比,深度算子神经网络通过引入主干网络结构,可考虑运动与气动力间的迟滞特性,气动力预测平均绝对误差降低2%,误差分散性更低;在失速颤振预测方面,极限环振荡幅值误差在2%以内,增加来流速度输入的深度算子神经网络模型预测误差显著小于固定速度输入的算子模型.

基于演化博弈的城市地摊经济常态化治理策略研究

地摊作为一种边缘化的商业经济模式,在为消费者提供实惠便利服务的同时,与城市精细化治理存在一定摩擦,多次经历放开又叫停的发展困境。以地摊经济发展融入城市治理为目标,为探讨相关利益主体间的互动机理,结合前景理论与动态奖惩机制构建“摊贩-地方政府-消费者”三方演化博弈模型,运用SD仿真剖析系统的动态演化过程。结果表明:初始策略选择并不影响最终演化结果;加大奖惩和降低成本等管理模式无法长期奏效;政府应针对性地进行精细化治理,提升增量收益,发展常态有效的管理模式。

预防双馈风机调频期间失速的功率轨迹预设策略

为解决双馈风机阶跃惯性控制过程中易导致频率二次跌落和分机失速的问题,在斜坡形阶跃惯性控制方法基础上考虑风机有效旋转动能,建立转速减速阶段增发功率、加速阶段降低功率与线性下降阶段时间的数学关系,计算风机有功功率线性下降阶段不引起风机失速的最大持续时间,对功率轨迹线性下降阶段时间加以约束,使风机具有与斜坡形阶跃惯性控制相同频率支撑效果,同时防止风机失速、减少二次频率跌落。利用EMTP-RV平台对不同扰动大小、渗透率、风速情形进行仿真,验证了所提方法的有效性。