Blade Wrap Angle Impact on Centrifugal Pump Performance:Entropy Generation and Fluid-Structure Interaction Analysis

The centrifugal pump is a prevalent power equipment widely used in different engineering patterns,and the impeller blade wrap angle significantly impacts its performance.A numerical investigation was conducted to analyze the influence of the blade wrap angle on flow characteristics and energy distribution of a centrifugal pump evaluated as a low specific speed with a value of 69.This study investigates six impellermodels that possess varying blade wrap angles(95°,105°,115°,125°,135°,and 145°)that were created while maintaining the same volute and other geometrical characteristics.The investigation of energy loss was conducted to evaluate the values of total and entropy generation rates(TEG,EGR).The fluid-structure interaction was considered numerically using the software tools ANSYS Fluent and ANSYSWorkbench.The elastic structural dynamic equation was used to estimate the structural response,while the shear stress transport k–ωturbulence model was utilized for the fluid domain modeling.The findings suggest that the blade wrap angle has a significant influence on the efficiency of the pump.The impeller featuring a blade wrap angle of 145°exhibits higher efficiency,with a notable increase of 3.76%relative to the original model.Variations in the blade wrap angle impact the energy loss,shaft power,and pump head.The model with a 145°angle exhibited a maximum equivalent stress of 14.8MPa and a total deformation of 0.084 mm.The results provide valuable insights into the intricate flow mechanism of the centrifugal pump,particularly when considering various blade wrap angles.

Analysis of the Influence of the Blade Deformation on Wind Turbine Output Power in the Framework of a Bidirectional Fluid-Structure Interaction Model

The blades of large-scale wind turbines can obviously deform during operation,and such a deformation can affect the wind turbine’s output power to a certain extent.In order to shed some light on this phenomenon,for which limited information is available in the literature,a bidirectional fluid-structure interaction(FSI)numerical model is employed in this work.In particular,a 5 MW large-scale wind turbine designed by the National Renewable Energy Laboratory(NREL)of the United States is considered as a testbed.The research results show that blades’deformation can increase the wind turbine’s output power by 135 kW at rated working conditions.Compared with the outcomes of the simulations conducted using the model with no blade deformation,the results obtained with the FSI model are closer to the experimental data.It is concluded that the bidirectional FSI model can replicate the working conditions of wind turbines with great fidelity,thereby providing an effective method for wind turbine design and optimization.

Study of modeling unsteady blade row interaction in a transonic compressor stage part 2:influence of deterministic correlations on time-averaged flow prediction

The average-passage equation system （APES） provides a rigorous mathematical framework for account- ing for the unsteady blade row interaction through multistage compressors in steady state environment by introducing de- terministic correlations （DC） that need to be modeled to close the equation system. The primary purpose of this study was to provide insight into the DC characteristics and the in- fluence of DC on the time-averaged flow field of the APES. In Part 2 of this two-part paper, the influence of DC on the time-averaged flow field was systematically studied; Several time-averaging computations boundary conditions and DC were conducted with various for the downstream stator in a transonic compressor stage, by employing the CFD solver developed in Part 1 of this two-part paper. These results were compared with the time-averaged unsteady flow field and the steady one. The study indicat;d that the circumferential- averaged DC can take into account major part of the unsteady effects on spanwise redistribution of flow fields in compres- sors. Furthermore, it demonstrated that both deterministic stresses and deterministic enthalpy fluxes are necessary to reproduce the time-averaged flow field.

Study of modeling unsteady blade row interaction in a transonic compressor stage part 1:code development and deterministic correlation analysis

The average-passage equation system （APES） provides a rigorous mathematical framework for account- ing for the unsteady blade row interaction through multi- stage compressors in steady state environment by introduc- ing deterministic correlations （DC） that need to be modeled to close the equation system. The primary purpose of this study is to provide insight into the DC characteristics and the influence of DC on the time-averaged flow field of the APES. In Part 1 of this two-part paper, firstly a 3D viscous unsteady and time-averaging flow CFD solver is developed to investi- gate the APES technique. Then steady and unsteady simu- lations are conducted in a transonic compressor stage. The results from both simulations are compared to highlight the significance of the unsteady interactions. Furthermore, the distribution characteristics of DC are studied and the DC at the rotor/stator interface are compared with their spatial cor- relations （SC）. Lastly, steady and time-averaging （employing APES with DC） simulations for the downstream stator alone are conducted employing DC derived from the unsteady re- suits. The results from steady and time-averaging simula- tions are compared with the time-averaged unsteady results. The comparisons demonstrate that the simulation employing APES with DC can reproduce the time-averaged field and the 3D viscous time-averaging flow solver is validated.

On the Wake Flow Interaction between Model Turbines with Varying Streamwise Distance

Wind tunnel measurements using particle image velocimetry have been performed around two perforated discs, with varying streamwise distance, in order to simulate the wake interaction between wind turbines. The static pressure footprint (p-f) on ground level associated with the wake behind the disc and wake velocity data for both the streamwise and wall-normal velocity components with the corresponding turbulence intensities are reported. The p-f method shows that the size of the wake regions, behind the wind turbine models, initially drop when a second disc is placed just downstream of the first one. From a mutual distance (Δ χ) of about five disc diameters (5D), both wake footprints increase as the mutual distance is increased, and for very large mutual distances, approximately Δ χ/ D > 15, the footprint of the downstream disc has recovered and is about the same as for a single disc. At last we conclude that despite very different inlet conditions to the discs, with about 50% of reduced velocity on the centre line upstream of the second disc and an increase of the maximum streamwise fluctuations by 90%, the mean velocities in the wake are proven to scale with the hub height velocity.

Investigation into the Interaction of Centrifugal Compressor Impeller and Vaneless Diffuser

Centrifugal compressors with parallel-wall and contracting wall vaneless diffuser are designed by using centrifugal compressor computer-aided integrated design system. The internal flow fields of the compressor are calculated by solving three-dimensional Navier-Stokes equation. Four aspects are investigated and calculation results show that the total efficiencies and total pressure ratios of the compressor with contracting wall vandess diffuser is higher than that of the compressor with parallel-wall. The jet and wake don＇t mix rapidly inside vandess diffuser. The outlet blade lean angle doesn＇t affect the compressor performance. The greater the mass flow rate through impeller, the more uneven the velocity distribution at impeller outlet is.

Numerical Study on Flow Around Modern Ship Hulls with Rudder-Propeller Interactions

Reducing the fuel consumption of ships presents both economic and environmental gains. Although in the past decades,extensive studies were carried out on the flow around ship hull, it is still difficult to calculate the flow around the hull while considering propeller interaction. In this paper, the viscous flow around modern ship hulls is computed considering propeller action. In this analysis, the numerical investigation of flow around the ship is combined with propeller theory to simulate the hull-propeller interaction. Various longitudinal positions of the rudder are also analyzed to determine the effect of rudder position on propeller efficiency. First, a numerical study was performed around a bare hull using Shipflow computational fluid dynamics(CFD) code to determine free-surface wave elevation and resistance components.A zonal approach was applied to successively incorporate Bpotential flow solver^ in the region outside the boundary layer and wake, Bboundary layer solver^ in the thin boundary layer region near the ship hull, and BNavier-Stokes solver^in the wake region. Propeller open water characteristics were determined using an open-source MATLAB code Open Prop, which is based on the lifting line theory, for the moderately loaded propeller. The obtained open water test results were specified in the flow module of Shipflow for self-propulsion tests. The velocity field behind the ship was recalculated into an effective wake and given to the propeller code that calculates the propeller load. Once the load was known, it was transferred to the Reynolds-averaged Navier-Stokes(RANS) solver to simulate the propeller action. The interaction between the hull and propeller with different rudder positions was then predicted to improve the propulsive efficiency.

极端运行阵风下风电叶片动力学响应特性流固耦合分析

基于CFD及有限单元法,利用ANSYS Workbench平台的Fluent与Transient Structural模块,对NREL 5 MW风电机组复合材料叶片在极端运行阵风下的气动特性及结构力学特性进行研究。结果表明:风轮气动载荷受极端运行阵风的影响较大,极端运行阵风作用下,风力机转矩及轴向推力等随风速的变化出现较大幅值的响应且响应峰值较阵风峰值均有所提前;叶片位移随风速的变化在峰值风速的前后出现大小两个峰值;在风速达到峰值时,与均匀来流阶段相比,叶片表面应力整体增幅较大。

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.

叶片旋向对风力机尾流特性影响的试验研究

采用一种简单、有效的方法来改善风力机尾流效应,提升下游风力机功率。进行叶片旋向对风力机尾流特性的试验研究,利用低频粒子图像测速(PIV)系统对NACA4415翼型的叶片进行扰流流场测试并采集风力机的尾流数据。当2台串列排布的风力机旋向不同时,首先在下游风力机前1D(D为风轮直径)处,叶尖涡涡核位置向中央尾迹区偏移,而外部主流区的流体在叶尖涡诱导区的输运和卷吸作用下持续进入中央尾迹区并与之掺混使得轴向速度恢复得更佳;进而分析下游风力机后1D的流场数据,结果显示:虽然下游风力机叶尖涡几何结构被“打碎”,但涡核能量却未降低;最后探讨影响风力机功率特性的因素,下游风力机入流角的增大促使下游风力机捕获更多风能,在风轮间距为2D时,逆向旋转的功率比比同向旋转时高4.70%,且功率比随间距增加其增幅逐渐减小。

涡流恢复导叶对螺旋桨气动和声学性能影响研究

为了对比安装涡流恢复导叶与单排螺旋桨气动性能和气动噪声的差异,采用数值模拟的方法研究了安装六种不同间距涡流恢复导叶和单排螺旋桨的气动力及气动噪声。研究结果表明:在起飞状态,级间距Δx=0.27的工况下,安装涡流恢复导叶使得推力系数增加6.4%,效率增加6.7%。随着间距的增大,前级叶片的桨尖涡、尾迹涡等涡系结构在通过后级叶片时破碎并向下游传播,且强度逐渐减小。噪声强度随着级间距的增加而逐渐减小,最大级间距涡流恢复导叶的噪声与最小级间距涡流恢复导叶噪声相比降低5.7 dB,噪声下降幅度随级间距的增加逐渐减缓,存在级间距最优位置使得推力增加最大,噪声强度适中。

台风风速下风力机风轮流固耦合动力响应特性研究

将改进的流固耦合方法用于不同风速下风力机的载荷和响应特性研究,其准确性得到NREL数据和风力机叶片模态振动实验的验证。与传统的流固耦合方法相比,该方法减少了动网格使用数量、避免负体积网格,提高了计算稳定性,将计算时间缩短约50%。仿真结果表明,将风速由25 m/s提升至35 m/s,叶片的推力和扭矩载荷的波动振幅分别增加了6.8倍和9.8倍。同时,在叶片吸力面发现存在结构屈曲,这与台风现场叶片断裂位置接近,可能是风力机叶片结构在台风环境下的强度薄弱点,同时,在叶片吸力面发现存在结构屈曲,这与台风现场叶片断裂位置接近,是可能的风力机叶片结构在台风环境下的强度薄弱点。

基于故障物理的风力机叶片可靠性仿真分析方法

提出一种基于故障物理的风力机叶片可靠性仿真分析方法,通过绘制任务剖面和载荷剖面图,将叶片材料、结构、环境条件和使用方式等参数加载到数值计算模型中,进行瞬态热力学、振动应力和多应力耦合分析。结果表明,最大应力和热集中主要发生在叶片根部,变形主要发生在叶片中部到叶尖这段区间。从故障原因和机理出发研究叶片的故障规律,运用FMECA(故障模式、影响和危害性分析)处理收集到的故障信息。将定性评价指标予以定量化,以此建立叶片危害性矩阵和FMECA表格,在失效模式下对高危性故障数据进行可靠性评估,为工程实际提供必要的理论支持。该方法相较于传统基于手册的可靠性分析方法精度更高,与研制、生产、维修和管理并行,通过不断更新迭代,以保证产品可靠性要求的实现,为风力机叶片的可靠性分析提供了新的思路和实施方法。

脉冲信号的奇异性分布熵特征分析

为了对低信噪比复杂环境下脉冲信号的奇异性差异进行有效的分析和标定,提出了一种基于模极大值理论的奇异性分布熵特征分析模型。首先对脉冲信号进行归一化并进行小波变换,计算各尺度下模极大值及其特定分布,可以体现具有奇异性差异的模极大值曲线族。为定量描述这种差异性,用熵值表达构成模极大值曲线族的模极大值点分布,并构建能有效分析脉冲信号奇异性差异的奇异性分布熵特征模型。该模型能对低噪比下信号的奇异性差异进行刻画。实验结果表明,在信噪比为-6 dB的环境下对典型的直升机脉冲信号(桨/涡干扰信号和高速脉冲信号)进行分析,能够得到89.25%和87.63%的正确率。

不同风速对单桩式海上风电机组塔筒动态特性的影响

基于ANSYS有限元软件对NREL 5 MW单桩式海上风电机组塔筒系统进行三维实体建模,在考虑土构耦合与叶轮旋转作用下,模拟分析不同风速对塔筒结构动态响应特性的影响。选取机组切入风速3 m/s与切出风速25 m/s区间内6种平均风速及与之对应的叶轮转速作为模拟工况,分析结果表明:随着风速和叶轮转速的增加,塔筒结构的模态频率逐渐增大,前两阶模态频率变化最为明显;塔筒位移量峰值增大,但增幅减小,位移量呈非线性增长趋势;塔筒等效应力值随之增大,但变化趋势与位移量不同,大致为线性增长;塔筒疲劳寿命急剧下降,但都远超实际工作时长,疲劳损伤与安全系数危险值主要分布在塔筒底部与单桩处,与最大等效应力分布位置吻合。

不完整实例引导的航空发动机叶片实例分割

当前基于深度学习的实例检测方法在进行发动机叶片分割时,由于缺少带标注的发动机叶片数据,导致无法充分训练网络模型,仅得到次优的分割结果。为了提升航空发动机叶片实例分割精度,提出了不完整实例引导的航空发动机叶片实例分割方法,通过结合已有的实例分割方法和交互式分割方法,可得到较好的发动机叶片分割结果。首先,使用少量标注数据训练实例分割网络,得到发动机叶片的初步分割结果;其次,将检测到的单个叶片分为前景和背景两部分,通过选择前景种子点和背景种子点,利用交互式分割方法的思想,产生完整的单个叶片的分割结果;依次处理完所有的叶片后,将结果合并得到最终的发动机叶片实例分割结果。使用72张图像训练基于稀疏实例激活图的实时实例分割方法(SparseInst)产生初始的实例分割结果,在56张图像上进行测试。所提方法的全类平均准确率(mAP)比SparseInst的全类平均准确率高5.1个百分点;且它的mAP结果均优于当前流行的实例分割方法MASK R-CNN(MASK Region based Convolutional Neural Network)、YOLACT(You Only Look At CoefficienTs)、BMASKRCNN(Boundary-preserving MASK R-CNN)。

Astrocytic calcium waves:unveiling their roles in sleep and arousal modulation

Neuron-astrocyte interactions are vital for the brain’s connectome.Understanding astrocyte activities is crucial for comprehending the complex neural network,particularly the population-level functions of neurons in different cortical states and associated behaviors in mammals.Studies on animal sleep and wakefulness have revealed distinct cortical synchrony patterns between neurons.Astrocytes,outnumbering neurons by nearly fivefold,support and regulate neuronal and synaptic function.Recent research on astrocyte activation during cortical state transitions has emphasized the influence of norepinephrine as a neurotransmitter and calcium waves as key components of ion channel signaling.This summary focuses on a few recent studies investigating astrocyte-neuron interactions in mouse models during sleep,wakefulness,and arousal levels,exploring the involvement of noradrenaline signaling,ion channels,and glutamatergic signaling in different cortical states.These findings highlight the significant impact of astrocytes on large-scale neuronal networks,influencing brain activity and responsiveness.Targeting astrocytic signaling pathways shows promise for treating sleep disorders and arousal dysregulation.More research is needed to understand astrocytic calcium signaling in different brain regions and its implications for dysregulated brain states,requiring future human studies to comprehensively investigate neuron-astrocyte interactions and pave the way for therapeutic interventions in sleep-and arousal-related disorders.

复合载荷作用下H型垂直轴风力机叶片结构多目标优化

为改善气动力、离心力和重力等复合载荷作用下的H型垂直轴风力机叶片的结构性能,提出一种多目标优化方法。以质量和最大应力最小为目标,最大变形为约束建立优化模型。通过流固耦合(Fluid-Structure-Interaction,FSI)方法,实现叶片表面压力的实时准确提取,建立复合载荷作用下的叶片有限元模型;基于最优空间填充(Optimal Space-Filling,OSF)方法和Kriging模型建立各变量对应力、质量和变形的响应面模型,进行灵敏度和变化趋势分析;最后采用多目标遗传算法(Multi-Objective Genetic Algorithm,MOGA)获得各变量的最优解,并进行结果验证。结果表明,优化后叶片质量减少了14.7%,各方位角下的最大应力减幅最大为7.8%,最大变形减幅最大为16.7%。研究结果可为复合载荷作用下叶片的结构优化设计提供参考。

直升机小速度前飞状态下的振动机理研究

针对直升机在小速度前飞状态下振动偏大问题展开机理研究。采用自由尾迹模型计算小速度前飞状态下的旋翼桨涡干扰气动特征;推导了桨叶4自由度桨叶挥舞动力学结构有限元模型,以进行模态分析和结构参数影响分析;采用预定气动载荷法,建立桨叶挥舞动力学模型,分析桨叶结构动响应/载荷特征。研究结果表明,小速度状态下,气动载荷中桨涡干扰所致的频率为五倍旋翼转速的谐波成分是其振动问题的“外部”气动力源头;旋翼展向上根部大分布质量引起的惯性载荷是其振动问题的“内部”根源;两者的综合作用使得通过频率的旋翼动载荷高于基准旋翼,引起机体的异常振动。

Static aeroelasticity analysis of a rotor blade using a Gauss-Seidel fluid-structure interaction method

The present study introduces a Gauss-Seidel fluid-structure interaction(FSI)method including the flow solver,structural statics solver and a fast data transfer technique,for the research of structural deformation and flow field variation of rotor blades under the combined influence of steady aerodynamic and centrifugal forces.The FSI method is illustrated and validated by the static aeroelasticity analysis of a transonic compressor rotor blade,NASA Rotor 37.An improved local interpolation with data reduction(LIWDR)algorithm is introduced for fast data transfer on the fluid-solid interface of blade.The results of FSI calculation of NASA Rotor 37 show that when compared with the radial basis function(RBF)based interpolation algorithm,LIWDR meets the interpolation accuracy requirements,while the calculation cost can be greatly improved.The data transmission time is only about 1%of that of RBF.Moreover,the iteration step of steady flow computation within one single FSI has little impact on the converged aerodynamic and structural results.The aerodynamic load-caused deformation accounts for nearly 50%of the total.The effects of blade deformation on the variations of aerodynamic performance are given,demonstrating that when static aeroelasticity is taken into account,the choke mass flow rate increases and the peak adiabatic efficiency slightly decreases.The impact mechanisms on performance variations are presented in detail.