转子轴承系统稳定性分析与识别方法

大规模的工业生产对透平机械的转子稳定性提出了更高的要求,对稳定性的评价及改善技术的需求极为迫切。采用电磁激振器进行正弦扫频试验,用最小二乘法在频域对转子轴承系统的频响函数进行估计来提高数据精度,并使用均值滤波抑制频响函数的高频噪声使得频响特性更加清晰。再利用变换矩阵,将实数域的传统多输入多输出频响函数转化到复数域直接频响函数来消除正反进动模态叠加的影响,为使用有理多项式法识别转子正进动模态参数提供更高精度数据。采用有理多项式法对传统频响函数和复数域直接频响函数进行拟合识别,得到转子系统的模态参数从而进行稳定性评价,并通过理论计算和试验验证,结果表明该方法准确性较高。该方法可为提高离心压缩机的转子稳定性提供理论和技术基础。     

基于电磁激励的柔性转子系统轴承等效参数辨识

随着高端透平机械的发展,迫切需要准确预测转子系统的模态阻尼以确保在工作条件下稳定运行,而准确可靠的辨识出轴承的动力学性能参数是先决条件。通过电磁轴承作为激振器给柔性转子施加激励力,并综合多截面测点的转子振动信息准确识别转子的轴承参数。将转子-轴承系统转换为被控对象和控制器的闭环控制系统,从而把轴承参数的识别问题转为控制系统的控制器参数识别,解决传统识别方法转子轴承中心和振动位移测量点不一致的情况,并且可提高参数识别的准确度。建立高精度的转子有限元模型进行基于模型的参数识别,并开展试验研究以验证该方法的可行。通过使用识别的轴承刚度阻尼参数预测的转子稳定性参数（固有频率与对数衰减率）与通过传统的扫频激励的测量方法得到的结果相比较,验证该方法的准确性。该识别方法可为轴承参数的辨识提供便捷的方法并为提高高端透平机械的稳定性设计提供理论和技术基础。     

起落架摆振的子空间模态参数辨识

为给起落架稳定性合格审定提供依据,国内首次在某民用飞机上进行了摆振试验。试验时,在跑道上安装了激励板,飞机按要求的速度滑过激励板以激励起结构的动态响应。子空间模态参数辨识方法被引入到数据处理中,为剔除虚假模态,稳定图被引入以判别真实模态频率和系统的阶次。最后给出该飞机起落架的模态参数辨识结果。结果表明:激励板能有效地激励起结构的动态响应,结合了稳定图的子空间模态参数辨识方法给出了较好的辨识结果,起落架未发生摆振。     

透平机械三转子四支撑轴系不平衡振动特性

针对汽轮机、压缩机等透平机械三转子四支撑轴系经常发生不平衡振动现象,研究轴系中各转子振型不平衡的响应特性。采用有限元法构建三转子四支撑轴系动力学有限元模型,分别在各跨转子上施加一阶、二阶弯曲振型不平衡,分析高低转速下轴系的涡动轨迹,以揭示各转子振型不平衡与轴系振动响应的关联。通过搭建的三转子四支撑轴系转子振动实验台,开展各跨转子不平衡激励下轴系振动响应测试,分析共振点和幅、相频特性,得出结论:这类轴系跨内加重振动响应由轴系模态振型和激励类型共同决定,兼具有转子外伸端振动特性。该结论可为消除这类三转子四支撑轴系不平衡故障提供参考。     

自动化立体仓库巷道堆垛机的振动测试与工作模态分析

在运行条件下对自动化立体仓库巷道堆垛机进行了振动测试。使用频域分解技术(FDD)和时域随机状态子空间辨识技术(SSI)分别从加速度响应数据提取了堆垛机的工作模态参数，包括固有频率、阻尼比和模态振型。在0～87Hz频带内采用两种不同的模态参数辨识方法估计的5个模态相当一致。分析结果表明：两种辨识算法都是有效的，估计的模态参数是可靠的。分析结果对于堆垛机的动力学修改和运行状态监控有重要的应用价值。     

基于恒位移测试的转子系统非线性支承刚度参数辨识研究

采用基于正弦扫频技术的恒位移测试方法来获取转子支承系统在一系列恒定位移幅值响应下的频响函数,并辨识转子支承的非线性刚度参数。首先对转子支承系统进行两端支承状态下的模态分析,得到转子系统在线性支承条件下的模态;然后采用正弦激励进行仿真测试,对转子支承进行不同水平的恒位移测试,通过模态分析得到不同响应水平下的模态参数,建立等效非线性参数与响应之间的关系,再结合等效线性化理论,识别非线性刚度参数。     

循环对称结构随机子空间法模态分析及验证

为探究仅基于响应测量的随机子空间法能否准确识别循环对称结构的重根模态,以制动盘为例,分别对其进行基于随机子空间法的模态分析及传统的试验模态分析,并提取了相应的模态参数,结果显示二者前9阶固有频率最大误差仅为0.66%,且振型吻合。表明仅基于响应测量的随机子空间法同样适用于循环对称类结构的模态分析。     

DHMA实验模态分析系统

东华测试推出的“DHMA实验模态分析系统”,包括可控激励系统、传感器、数据采集系统和实验模态分析软件,提供了进行实验模态分析所必需的软、硬件条件。DHMA模态实验系统通过对采样数据进行分析,可以精确得到被测结构的模态参数（固有频率、振型、阻尼比）,显示被测结构的振型三维动画,也可显示模型的时域或频域的运行动挠度ODS（Operating Deflection Shape）。     

DHMA实验模态分析系统

东华测试推出的“DHMA实验模态分析系统”,包括可控激励系统、感器、数据采集系统和实验模态分析软件,提供了进行实验模态分所必需的软、硬件条件。DHMA模态实验系统通过对采样数据进行分,可以精确得到被测结构的模态参数（固有频率、振型、阻尼比）,显被测结构的振型三维动画,也可显示模型的时域或频域的运行动传析析示挠度ODS（Operating Deflection Shape）。     

基于ODS方法的转子故障分析

转子系统在旋转机械中起着关键作用,一旦发生故障,将造成重大经济损失。因此,开展旋转机械转子故障诊断方法的研究具有重要工程意义。目前一般是基于传统傅里叶变换的频谱分析方法诊断转子故障。这种方法不能判断转子进动方向,容易误判机组发生故障原因。基于上述问题,研究运行变形振型(ODS)方法,并将其应用于转子故障实验中。用不同参数的变化来反应转子在不同工况下的ODS改变量,以此来判断转子发生哪一种故障以及故障的严重程度。最后运用仿真数据及实验结果验证了这种方法的正确性和有效性。     

磁轴承激励下转子系统动力学特性

为分析磁轴承激励下转子系统的振动机理,应用一维有限元方法建立了双盘转子系统动力学特性计算模型,研究了不同类型磁轴承激励下转子系统的动力学行为.研究结果表明:同向旋转的扫频激励力激发了转子系统的正进动模态,而反向旋转的扫频激励力激发了转子系统的反进动模态,两种情况下转子系统均以圆轨迹进动;由于单向简谐激励力可以分解为同向...     

考虑大幅值输入的随机子空间识别

随机子空间识别是一种可靠的时域模态参数识别算法,通常是利用结构在零初始状态作用下的动力响应来识别结构模态参数,而并没有考虑大幅值输入对识别结果的影响。针对此问题,研究了大幅值输入对随机子空间识别的影响并探讨了方法的适用性。首先,介绍了考虑大幅值输入的随机子空间识别理论基础;然后,通过一个两自由度系统进一步考虑了不同阶次模态、模态振型的相对精度随采样数和大幅值输入的变化情况;最后,以菜园坝长桥大桥拱肋脉动试验为算例,研究了考虑大幅值输入识别方法的适用性。结果表明:考虑大幅值输入能够提高识别的模态参数精度;相比频率,模态振型精度随采样数的变化具有一定的随机性;考虑大幅值的随机子空间识别对模态试验的完备性要求较高。     

Numerical prediction of rotordynamic coefficients for an annular-type plain-gas seal using 3D CFD analysis

Annular-type gas seals in many types of compressors and turbines are designed to reduce leakage and enhance the vibrational stability of the turbo machinery. Many researchers have attempted precise theoretical evaluation of the leakage and the rotordynamic coefficients from reaction forces of small seal gaps. The Bulk-flow model, which is based on Hirs’ lubrication equation, is a general method with advantages of simplicity and short computing time. However, due to the disadvantage of the long time required to develop analysis code, and constraints from complicated seal shapes, CFD analysis is currently preferred. In the present, the method for determining the rotordynamic coefficients of an annular plain-gas seal, which is the simplest shape of gas seals, is suggested by extending the analysis of an annular plain-pump seal. A relative coordinate system for steady-state simulation is defined to calculate the compressible flow field and dynamic pressure distribution of the seal gap. The present analysis is verified by comparison with results acquired from Bulk-flow analysis code and published experimental results. The 3D CFD rotordynamic coefficients results of direct stiffness(K) and cross coupled stiffness(k) show better improvements in prediction.     

Numerical simulation of rotordynamic coefficients for eccentric annular-type-plain-pump seal using CFD analysis

Annular seals are primarily used to control the leakage in turbomachinery, such as pumps. Consequently, annular seals substantially affect the stability of turbomachinery. Designing the annular seals of high performance pumps require the accurate prediction of the seal’s leakage flow rate and rotordynamic coefficients. The bulk-flow model is the traditional means for leakage flow rate analysis and predictions. Bulk-flow analysis is based on the Hirs’ lubrication equation, which simplifies the Navier-Stokes equation. However, the analysis of the bulk-flow model requires a great amount of time to develop an analysis code. Furthermore, the code possesses many constraints for analyzing seals with complicated shapes. 3D CFD simulations provide faster and less expensive estimates of the flow field for a wide variety of operating parameters and flow conditions. In this study, the flow field and the rotordynamic coefficients of a plain-eccentricannular seal were simulated with circular whirl orbits using 3D CFD code. A relative coordinate system was defined to calculate the 3D velocity profile and the dynamic pressure distribution of the seal clearance for each rotor whirling speed. The rotordynamic coefficients were determined by reaction forces of seal fluid, which were calculated by integrating the dynamic pressures to the whole area of seal. The results from our analyses were compared to existing theoretical calculations as well as compared to results acquired from experiments. The present 3D CFD results of leakage and rotordynamic coefficients of K and C showed better improvement in prediction.     

Self-excited vibrations of a rigid rotor rubbing with the motion-limiting stop

The solutions of the motion governing equations of the rotor-bearing-stop system are analyzed to acquire the behavior of the self-excited vibration. The numerical iteration method is put forward to obtain the periodic solution implying that the rotor whirls forward in the perfect annular orbit and keeps full rubbing with the stop.The dynamics parameters such as the stop-to-bearing stiffness ratio, the friction factor and the damping coefficient determine whether the periodic solution exists. They also affect amplitude and frequency of the periodic solution. The numerical stability analysis on the periodic solution concludes that the periodic solution behaves in an unstable motion state which will develop into the forward dry whip through full rubbing or converge to the decaying natural whirl without rubbing. The evolvement of the unstable full rubbing rests on the initial vibration energy of the rotor. The analysis on existence and stability of periodic solution may explain the observations of initiation of full rubbing observed in experiments.Suggestion on selecting dynamic parameters of the rotor-bearing-stop system is presented in order to avoid the full rubbing which has great or catastrophic harm to the rotating machinery.     

基于神经网络的转子动力系统稳定性辨识

利用ＢＰ反馈神经网络对高速转子动力系统的稳定性进行辩识,该问题的关键是考虑由轴承间隙影响而产生的非稳定性问题。给出相应的多参数稳定性问题的公式以及相应的一系列化为三维参数的代数不等式,利用有监督的学习神经网络将转子动力系统通常较宽范围的三维物理参数映射成一狭窄的区域。利用转子动力系统的解析仿真推导出系统的二值状态不等式,构造隐藏层和函数链两种神经网络。利用所选定的旋转系统的参数值进一步训练该函数链的神经网络,从而构成分类网络。用稳定性状态识别的误判率来评估分类神经网络的性能。     

Analysis of tiltrotor whirl flutter in time and frequency domain

The whirl flutter phenomenon in a rotor is induced by in-plane hub forces, and imposes a serious limit on the forward speed. In this paper, based on Greenberg’s model, quasi-steady and unsteady aerodynamic forces are formulated to examine the whirl flutter stability for a three-bladed rotor without flexible wing modes. Numerical results are obtained in both time and frequency domains. Generalized eigenvalue solution is utilized to estimate the whirl flutter stability in the frequency domain, and Runge-Kutta method is used to analyze it in time domain. The effects of varying the pylon spring stiffness and the swashplate geometric control coupling upon the flutter boundary are investigated. An optimum pitch-flap coupling parameter is discovered through the parametric study. Aeroelastic stability boundaries are estimated with the three different aerodynamic models. It is found that the analysis with the full unsteady aerodynamics predicts the highest flutter speed.     

Nonlinear Dynamic Analysis of a Rigid Rotor Supported By a Spiral-Grooved Opposed-Hemisphere Gas Bearing

The nonlinear dynamic behavior of a rigid rotor supported by a spiral-grooved opposed-hemisphere gas bearing is investigated in this article, focusing particular attention on its whirl motion. The finite element method combined with the finite difference method is employed to solve the time-dependent Reynolds equation that is coupled with the rotor motion considering five degrees of freedom. The rotor responses to the initial disturbance and synchronous and nonsynchronous excitations are investigated. To analyze the complicated dynamic behavior of the rotor–bearing system, the trajectories of the rotor centerline, time responses, phase portraits, power spectra, Poincare maps, and bifurcation diagrams are obtained from the numerical procedure. The results show that the conical whirl instability appears earlier than the cylindrical whirl instability with increasing rotational speed for the rotor–bearing system with no unbalance mass. Moreover, it reveals that the complex dynamic behavior of the system excited by unbalance mass varies with rotational speed and rotor mass. In addition, bifurcation diagrams employing the rotating speed and rotor mass as bifurcation parameters are obtained. Finally, the nonsynchronous excitation responses are presented, which behave in a different way than the synchronous excitation responses. The results of this study offer a further understanding of the nonlinear characteristics of spiral-grooved opposed-hemisphere gas bearings.