Intrinsic physical relationships between rotor modal shapes and instantaneous vibrational energy flow transmission characteristics:Theoretical and numerical analysis and application

The modal vibration of the rotor is the main cause of excessive vibration of the aeroengine overall structure.To attenuate the vibration of the rotor under different modal shapes from the perspective of energy control,the intrinsic physical relationships between rotor modal shapes and instantaneous vibrational energy flow transmission characteristics is derived from the general equation of motion base on the structural intensity method.A dual-rotor-support-casing coupling model subjected to the rotor unbalanced forces is established by the finite element method in this paper.The transmission,conversion and balance relationships of the vibrational energy flow for the rotors in the first-order bending modal shape,the conical whirling modal shape and the translational modal shape are analyzed,respectively.The results show that the vibrational energy flow transmitted to the structure can be converted into the strain energy,the kinetic energy and the energy dissipated by the damping of the structure.The vibrational energy flow transmission characteristics of rotors with different modal shapes are quite different.Especially for the first-order bending modal shape,the vibrational energy flow and the strain energy are transmitted and converted to each other in the middle part of the rotor shaft,resulting in large deformation at this part.To attenuate this harmful vibration,the influences of grooving on the shaft on the first-order bending vibration are studied from the perspective of transmission control of vibrational energy flow.This study can provide theoretical references and guidance for the vibration attenuation of the rotors in different modal shapes from a more essential perspective.

Application of Improved Hybrid Interface Substructural Component Modal Synthesis Method in Vibration Characteristics of Mistuned Blisk

The large and complex structures are divided into hundreds of thousands or millions degrees of freedom（DOF） when they are calculated which will spend a lot of time and the efficiency will be extremely low. The classical component modal synthesis method （CMSM） are used extensively, but for many structures in the engineering of high-rise buildings, aerospace systemic engineerings, marine oil platforms etc, a large amount of calculation is still needed. An improved hybrid interface substructural component modal synthesis method（HISCMSM） is proposed. The parametric model of the mistuned blisk is built by the improved HISCMSM. The double coordinating conditions of the displacement and the force are introduced to ensure the computational accuracy. Compared with the overall structure finite element model method（FEMM）, the computational time is shortened by23.86%–31.56%and the modal deviation is 0.002%–0.157% which meets the requirement of the computational accuracy. It is faster 4.46%–10.57% than the classical HISCMSM. So the improved HISCMSM is better than the classical HISCMSM and the overall structure FEMM. Meanwhile, the frequency and the modal shape are researched, considering the factors including rotational speed, gas temperature and geometry size. The strong localization phenomenon of the modal shape’s the maximum displacement and the maximum stress is observed in the second frequency band and it is the most sensitive in the frequency veering. But the localization phenomenon is relatively weak in 1st and the 3d frequency band. The localization of the modal shape is more serious under the condition of the geometric dimensioning mistuned. An improved HISCMSM is proposed, the computational efficiency of the mistuned blisk can be increased observably by this method.

Experimental and FEM Modal Analysis of a Deployable-Retractable Wing

The aim of this paper is to conduct experimental modal analysis and numerical simulation to verify the structural characteristics of a deployable-retractable wing for aircraft and spacecraft. A modal impact test was conducted in order to determine the free vibration characteristics. Natural frequencies and vibration mode shapes were obtained via measurement in LMS Test. Lab. The frequency response functions were identified and computed by force and acceleration signals, and then mode shapes of this morphing wing structure were subsequently identified by PolyMAX modal parameter estimation method. FEM modal analysis was also implemented and its numerical results convincingly presented the mode shape and natural frequency characteristics were in good agreement with those obtained from experimental modal analysis. Experimental study in this paper focuses on the transverse response of morphing wing as its moveable part is deploying or retreating. Vibration response to different rotation speeds have been collected, managed and analyzed through the use of comparison methodology with each other. Evident phenomena have been discovered including the resonance on which most analysis is focused because of its potential use to generate large amplitude vibration of specific frequency or to avoid such resonant frequencies from a wide spectrum of response. Manufactured deployable-retractable wings are studied in stage of experimental modal analysis, in which some nonlinear vibration resulted should be particularly noted because such wing structure displays a low resonant frequency which is always optimal to be avoided for structural safety and stability.

Extraction of real modes and physical matrices from modal testing

A technique to extract real modes from the identified complex modes is presented in this paper, which enables the normalized real mode shapes, modal masses, and full or reduced mass and stiffness matrices to be obtained. The theoretical derivation of the method is provided in detail. An 11-DOF vibration system is used to validate the algorithm, and to analyze the effects of the number of modes utilized and measurement DOFs on the extraction results. Finally, the method is used to extract real modes from both experimental modal analysis and operational modal analysis.

Two-Dimensional Modal Curvature for Damage Detection in Plates

Mode shape has become a hotspot of vibration-based damage detection in plates.Two-dimensional(2D)modal curvature(MC2D),derived from mode shapes,is a prevailing physical quantity used to indicate damage.Unfortunately,the physical mechanism of MC2 Dfor characterizing damage in plates has not been clarified to date.In contrast,one-dimensional(1D)modal curvature(MC1D)has explicit physical mechanism to portray damage in beams.Unresolved physical mechanism of MC2 Dseverely hampers its applications for damage identification in plates.To address this deficiency,the clarification mechanism of MC2 Dis investigated to identify damage.With the clarified mechanism,numerical and experimental cases are used to demonstrate the effectiveness of MC2 Din detecting damage in plates.

用于轮胎振动分析的壳模型优化研究

虽然现有壳模型在0~500 Hz频带内精度高,适合用于轮胎结构振动分析,但由于模型中耦合了胎侧二维壳模型,导致胎冠振动模态难以分离,且模型自由度和所需输入参数增加。本文对该壳模型进行改进:在保持胎冠壳模型不变的基础上,应用轮胎环模型和板模型中对胎侧的近似方法,采用弹性基底代替胎侧二维壳模型,简化了原模型的边界条件并缩减了输入参数个数;针对改进后的壳模型建立了求解方法,实现了胎冠模态频率和振型的求解。并通过与实验数据的对比,验证了改进后的壳模型及其求解方法的正确性。

Radiation from finite cylindrical shell with irregular-shaped acoustic enclosure

In practical situations, large machinery is usually placed in an underwater vessel and changes the acoustic enclosure shape into an irregular one. The existence of machinery causes the difficulties in expressing sound transmission and radiation analytically. In this study, the sound radiation of a cylindrical shell excited by an internal acoustic source is modeled and analyzed. The cylindrical shell contains a machine modeled as a rectangular object, which is attached to a shell with a spring-mass system. The acoustic field of the cavity is computed by the integro-modal approach. The effect of object size on the coupling between acoustic mode and structural mode is investigated. The relationship between object volume and sound radiation is also studied. Numerical results show that the existence of objects inside vessels leads to a more effective coupling between the structure and acoustic enclosure than the existence of no objects in a regular-shaped cavity（i.e. empty vessel）.

深水钻井隔水管横向振动振型分析

为了分析深水钻井隔水管的横向振动固有频率和振型,综合考虑深水隔水管受到的顶部张紧力、海洋环境载荷、钻井平台漂移等作用力,借助微元法建立受力分析模型。根据连续梁理论和隔水管单元的动力学微分方程,确定其无阻尼自然振动基本方程,并进一步剖析建立隔水管横向振动固有频率微分方程和模态振型基本方程,然后进行数值求解。使用控制变量法逐步分析隔水管长度、张力比、自身材质对隔水管固有频率的影响和变化规律。通过MATLAB软件表现出不同阶数的振动振型,结果表明:控制张力比、合理选择隔水管类型能够有效提高固有频率,避免与波流力形成共振,进而保证深水钻井作业安全。此外,隔水管的振型并不是标准正弦曲线,振型会受时间的影响不断变化。

细长桁架臂卸载反弹动应力分布规律及试验

为研究细长桁架臂在卸载冲击下的动态响应变化规律,提出了基于等效梁振型函数的桁架臂动应力分布计算模型。根据等效梁振型函数,探讨了卸载后桁架臂动应力分布假设,分析了影响桁架臂卸载反弹动响应的相关参数。以装备细长桁架臂的动臂塔机为对象,建立了桁架臂精细化有限元模型和起重机刚柔耦合模型,通过仿真辨识了应力分布模型的关键参数。实施了动臂塔机系列载荷卸载冲击试验,桁架臂上主弦杆的动应力试验值与理论计算结果误差小于7%,表明动应力分布理论模型与实际相符。通过理论模型预测了极限工况下桁架臂上主弦杆动应力分布状态,发现在最大载荷卸载条件下起重臂动应力峰值超过结构承载极限,为卸载条件下起重机关键结构的优化设计提供依据。

基于形貌优化的车身地板振动性能优化分析

通过计算获得某皮卡车身悬置到地板的振动传递函数,对比参考车型地板振动曲线和设定目标线,发现地板响应点的峰值超出目标范围。采用模态贡献量分析确定最大贡献量模态频率,模态分析查找问题区域,确认地板存在与峰值频率一致的局部模态。采用形貌优化对车身地板加强筋重新优化设计,提升车身地板刚度降低地板振动响应幅值。对实车车身进行地板振动传递函数测试,对比测试和仿真的地板振动传递函数曲线,验证了计算结果的准确性。

基于谐响应分析的冲击式水轮机转轮共振预测

冲击式水轮机水斗的疲劳断裂与转轮的周期性振动密切相关。以六喷嘴冲击式水轮机模型机组转轮为研究对象,采用基于模态叠加的谐响应分析法,获取转轮在实际工作载荷激励下的形变与应力响应并评估薄弱部位,结合坎贝尔图确定共振转速。结果表明,在实际运行工况下转轮三阶模态振型最易被激发,最大形变值为21.50mm,位于水斗尖端;七阶与八阶频率下被施加最大简谐载荷的水斗等效应力值较大,从根部向水斗尖端缺口处递减,最大应力值出现在分水刃根部,发生明显的应力集中;坎贝尔图显示易发生谐共振的转速为587r/min、660r/min、785r/min,在实际运行中应进一步测试与避免。

核电工程异形水箱流固耦合分布式参数模型与效用研究

在流固耦合动力分析领域,传统的Housner模型在工程设计中发挥重要作用。但其理论推导仅适用于规则水箱,采用集中质量总体模型描述液体晃动的整体效应,难以有效模拟异形水箱储液结构的局部精细响应,亟须建立适用于不规则水体晃荡的分布式附加质量模型。基于势流理论推导了一种模态综合法模型,实现了分布质量与储液器壁激振加速度的解耦。该模型能够有效剥离分布式的脉冲质量与对流质量;同时,实体网格的振型分析适用于任意形状水体的动力分析。通过算例的形式将该模型与精细声学-结构耦合(Acoustic-Structural coupling,CAS)模拟法进行了比较,验证了模型的精确性与可靠性。最后,基于本文的模型研究了核电异形的安全水箱在不同水位和减晃格栅分布下的动力响应规律,并检验了其在工程中的适用性。

基于NSGA-Ⅱ传感位置优化的曲面重构及误差补偿方法

通过优化光纤布拉格光栅形状传感技术中传感点位置和补偿重构结果来提高薄层合金板三维形状重构精度。通过ANSYS workbench建立合金板仿真模型,提取应变和位移模态振型,根据模态置信准则、转换矩阵稳定性和模态振型相似性分别设计了三个目标函数,采用快速和精英机制的多目标遗传算法优化传感器位置。将镍钛合金板弯曲成不同曲率半径的弧形,利用光纤布拉格光栅中心波长漂移量和线性插值算法计算得出不同形状下的结构应变,重构合金板形状,均方根误差和最大误差相较于单目标优化算法分别减小30%和15%。利用粒子群优化径向基函数神经网络算法拟合误差与位移的关系实现误差补偿,均方根误差和最大误差比无补偿时分别减小了90%和70%,最大相对百分比误差仅为5%,提高了三维形状重构算法精度。

基于跨模型模态应变能变化的结构损伤识别两阶段法

为提高结构损伤识别精度,采用跨模型模态应变能变化(Cross-model Modal Strain Energy Changes,CMSEC)代替传统的模态应变能变化(Modal Strain Energy Changes, MSEC)建立先定位后定量的结构损伤识别两阶段法.与传统模态应变能(Modal Strain Energy, MSE)计算时仅利用结构损伤后的振型不同,跨模型模态应变能(CMSE)的计算同时利用结构损伤前后的振型.先利用CMSEC构建CMSECI (Cross-model Modal Strain Energy Index)损伤指标来确定损伤位置,筛选出疑似损伤构件后,再利用CMSEC建立定量识别损伤程度的灵敏度方程.采用基于奇异值截断的迭代法求解该方程,以避免迭代过程中可能出现的病态方程问题.根据公式构成可以定性判断CMSEC比MSEC更难被噪声干扰.某简支梁算例表明,本文方法在损伤定位和损伤定量两个阶段均比传统方法具有更高的识别精度.为了深入考察本文方法的优越性,采用蒙特卡洛法从宏观的相对误差上界和具体的相对误差分布这两个视角解释了本文方法优于传统方法的原因.

氦气轮机转子动力学特性优化设计

基于ANSYS软件对某一型号的氦气轮机柔性转子进行了转子动力学特性的计算分析与优化设计。首先对转子的初始模型进行了临界转速计算,并识别影响转子固有频率的关键部位,通过加强其弯曲刚度,初步提高了转子的临界转速。进一步将转子分段并用柔性膜盘联轴器连接,计算得到氦气轮机转子的临界转速大幅提高,使其在设计转速下可视为刚性轴,保证了氦气轮机转子的转子动力学安全。

基于扣件弹条固有频率的扣压力检测与试验验证

[目的]扣件弹条的扣压力不足,会诱发周围扣件松脱,加剧轮轨之间的动力响应,影响轨道部件的使用寿命。相对于弹条缺失和断裂,弹条松脱较难通过常规的工人巡检发现,需要研究扣件弹条扣压力的检测方法。[方法]以高速铁路的WJ-7型扣件弹条为例,建立了扣件系统的精细化模型,分析了扣件弹条在不同扣压力状态下的模态特征,得到扣件弹条扣压力与固有频率的对应关系,进而提出通过测试弹条模态频率来推算扣压力的快速无损检测方法。选取我国某国家重点实验室轨道试验基地的高铁线路作为试验现场,对该检测方法进行试验验证。[结果及结论]不同扣压力状态下,弹条第1阶模态振型特征均表现为弹条两侧肢产生垂向振动和扭转;弹条第1阶固有频率仿真值与实测值差值比例绝对值的最大值为3.24%,可以认为该试验方法具有有效性。

基于振型曲率的夹芯波纹板脱焊损伤分析方法研究

针对夹芯波纹板在生产和服役过程中的漏焊、脱焊损伤提出了基于动态响应参数的损伤识别方法。首先基于有限元理论对波纹板不同大小、不同位置的损伤进行数值分析,然后基于数值分析所得损伤前后振动特性参数,使用中心差分法求取结构模态振型曲率,根据求得的损伤前后模态振型曲率,分别用差分法、曲面光滑算法和二维连续小波变换建立损伤识别指标,从而确定损伤的位置和数量。最后通过数值分析和实验数据处理,验证了损伤分析方法的有效性和可靠性。计算结果表明:基于模态振型曲率建立损伤识别指标的差分法、曲面光滑算法以及二维连续小波变换均可以检测到损伤的位置和数量,但曲面光滑算法和二维连续小波变换相较于差分法不需要结构损伤前的原始数据,更适用于工程实际问题。

基于高分辨率模态柔度矩阵桥梁损伤识别的少量传感器方法

为了降低监测系统成本和提高桥梁损伤识别精度,本文利用少量传感器获得高分辨率模态振型.在考虑路面粗糙度的情况下,基于柔度变化率进行损伤识别.在不同路面粗糙度水平下,对移动车辆荷载作用下桥梁上所测位移响应进行特征正交分解,再将得到的主成分矩阵中高频动力分量信息过滤,获得高分辨率的模态振型.利用少量传感器方法得到的高分辨率模态振型计算柔度变化率,将其作为桥梁损伤定位的指标.为了验证该方法的有效性,对一简支梁进行模拟和试验.结果显示,该方法在考虑不同粗糙度水平情况下,利用少量传感器得到高分辨率模态振型的柔度变化率能准确定位损伤.

基于模因理论-AHP的川东土家族文化主题民宿设计研究

为传承和创新川东土家族文化,提升当地民宿品质,采用模因理论和AHP(Analytic Hierarchy Process)层次分析法,梳理文化特征,提取并筛选文化因子,基于形状文法对文化因子进行转译,生成新图形;提出了“引形赋新,装饰应用、形随物变,造型应用、旧形新构,组合应用”等转译应用思路,并应用于民宿空间的界面分割、天花造型、门窗装饰,以及软硬装装饰等具体设计实践中。旨在为传承土家族文化,提升民宿品质,促进当地旅游经济发展作为参考。

某型航空导叶作动筒振动性能仿真分析

针对航空导叶作动筒在复杂工况下的损坏问题,为在设计阶段预测产品可能出现的损坏,获取导叶作动筒标准载荷下的易损位置,利用有限元仿真建模方法建立了该型作动筒的模态分析、谐响应分析、随机振动分析与疲劳分析仿真模型。通过对数正弦扫频试验验证了模态分析仿真模型的准确性,获得了振型、固有频率与功率谱载荷下的应力响应等信息。考虑作动筒活塞的轴向伺服工作影响,在标准功率谱上叠加伺服工作正弦载荷模拟了该工况。建立随机振动情况下的疲劳寿命分析仿真模型,活塞与活塞密封圈的疲劳寿命结果在可接受范围内,为该航空作动筒结构优化设计提供了依据。