拱形围带叶片组振动特征分析及实验研究

对拱形围带连接的叶片组利用模态综合方法进行了振动特性分析,并采用脉冲激励等方法对叶片组作了实际测试。分析中考虑了自由界面部件高阶截断模态的影响,而且以对接界面位移耦合叶片各部件及拱形围带。本文的工作为汽轮机拱形围带长叶片结构提供了一种有效的振动特性分析方法。     

混合界面直接分支模态综合法

在直接分支模态综合法(本质上属自由界面模态综合法)的基础上,提出并深入研究了混合界面直接分支模态综合法。混合界面法将复杂庞大的结构取做主体部件,而将与此主体部件相连的其余部分视为分支部件。对主体部件采用自由界面,分支部件则采用固定界面。各子结构之间完全独立计算,并且通过计入主、从子结构的剩余模态矩阵的办法来补偿所舍去的高阶模态分量,保证了计算精度。本方法从工程应用的实际出发,通过模拟航空发动机机匣管路系统的数值算例,验证了混合界面法的正确性。     

改进的直接部件模态综合法

Yee和Tsuei提出的直接部件模态综合法将自由界面模态综合法与频响函数相结合 ,简化了计算过程、减少了计算量 ,并便于与实验模态分析相结合。本文在其基础上利用矩阵级数展开的方法将被截断高阶模态的贡献用保留模态和系统物理特性矩阵精确表达 ,结合分块计算方法 ,进一步减少了计算量并有效地提高了计算精度 ,且确定了模态截断准则。数值算例表明其行之有效     

失调叶片盘耦合振动中叶片模态精度问题

本文用试验模态分析与数值计算相结合的方法,为真实叶片盘耦合振动模态综合提供了获得高精度的叶片模态的简便途径.     

柴油机机体的模态试验与分析法

柴油机机体是柴油机的主体结构部件，研究其动态特性对于了解整机的振动特性非常重要。本文介绍了柴油机机体的试验模态分析方法，以及用该方法分析了６１０８型柴油机机体。求得该机体的前八阶模态频率、阻尼及振型，为该机体的结构改进和柴油机的减振降噪提供了依据     

复合柔性结构全局模态函数提取与状态空间模型构建

随着航空航天等领域中实际工程结构的大型化和柔性化,结构的非线性振动和主动振动控制问题越来越凸显.分析和处理此类结构出现的复杂振动问题的关键在于建立系统的非线性动力学模型与状态空间模型.对于由柔性部件、刚体、连接部件构成的复合柔性结构,由于各部件之间的振动耦合效应,单个柔性部件在悬臂、简支和自由等静定边界下的模态与结构的真实模态有较大差异.为此,本文提出复合柔性结构全局模态的解析提取方法,通过全局模态离散得到系统非线性动力学模型,从而构建状态空间模型.该方法采用笛卡尔坐标描述系统的运动,建立系统的运动方程;结合描述柔性部件的偏微分方程、刚体的常微分运动方程、连接界面处力、力矩、位移和转角的匹配条件以及系统的边界条件,利用分离变量法给出统一形式的频率方程,获取系统的固有频率和解析函数表征的全局模态.这里提出的全局模态提取方法不仅便于复合柔性结构固有频率和全局模态的参数化分析,而且为建立复合柔性结构低维非线性动力学模型和状态空间模型提供了有效的途径,对于推进这类结构的非线性动力学分析与主动振动控制研究具有重要意义.      

连结子结构与自由界面模态综合法在非线性动力分析中的应用

本文提出了一种由线性连接元和非线性连接元组成的连接子结构，并将这种连接子结构用于自由界面的模态综合技术。利用非线性振动理论的渐近方法，求得经模态综合法降维后系统方程的近似解析解。从而将具有连接子结构的自由界面的模态综合技术推广应用到具有局部非线性的复杂结构系统的动力分析，为利用非线性振动理论的渐近方法及动力系统理论进一步研究高维非线性动力学系统的振动特性、分岔及混沌行为创造了一种新的途径。算例表明，该方法具有足够的精度。     

风力机叶片非线性挥舞分析

将风力机叶片简化为绕轮毂旋转的变截面Euler-Bernoulli悬臂梁,基于Greenberg公式给出非线性气动力,建立叶片挥舞振动非线性控制方程.由于变截面梁的弯曲刚度和线密度是沿梁轴线变化的函数,无法给出模态函数解析式,论文提出使用假设模态法计算的模态函数,作为基函数对控制方程进行Galerkin截断,通过将挥舞振动分解为静态位移和动态扰动合成,对其进行动态响应分析,同时讨论了叶轮转速、风速和旋转位置对振动特性的影响.研究表明:(1)叶轮转速对叶片挥舞特性影响显著,风速和叶片转角对振动特性影响很小.(2)静态位移随风速增加而增大,大体上成线性关系,气动阻尼随风速增加而减小.(3)风速较低时,非线性挥舞振动表现为衰减振动,随着风速增加,振动由衰减振动演化为周期运动,再由周期运动演化为拟周期运动.     

航空发动机复合材料叶片振动疲劳特性研究

针对发动机复合材料叶片开展了振动疲劳特性研究。首先通过模态测试获得叶片结构的振型图,确定叶片在振动中应力最大部位疲劳薄弱部位;其次采用振动台施加窄带随机激励载荷,并监测其疲劳薄弱部位的应变水平,获得了复合材料叶片的振动响应及疲劳特性。试验结果显示,叶片在350με应变水平下的振动疲劳寿命为5.46×106;复合材料叶片的固有频率随试验时间的增加而降低。上述结果可为复合材料叶片在发动机中的应用提供部分依据。     

风机塔筒结构横向振动特性的快速计算方法

本文提出了一种风机塔筒结构横向振动特性的快速计算方法．将机舱和叶片整体、连接法兰盘分别简化为集中质量,塔筒简化为非均匀悬臂梁,建立风机塔筒结构横向振动方程．给出了用假设模态法计算塔筒结构固有频率和模态函数的过程．通过与文献及有限元数值结果比较验证了方法的有效性．本文方法仅需给出结构的基本参数,如截面半径变化规律、法兰盘位置和质量、机舱及叶片质量,便可快速求解其频率和模态,无需建立其复杂的力学模型．     

A design method for turbomachinery blading in three-dimensional flow

A mixed spectral finite element scheme for the implementation of a design method for turbomachinery blading in three-dimensional subcritical compressible flow is presented. The method gives the detailed blade shape that would produce a prescribed tangential mean swirl schedule, given the hub and shroud profiles, the number of blades and their stacking position. After a presentation of the mathematical formulation of the design theory, the current numerical approach is described. It is then applied to the design of blading for radial inflow turbine impellers in three-dimensional flow.     

The worst response of mistuned bladed disk system using neural network and genetic algorithm

The objective of this paper is to develop an integrated approach using artificial neural networks (ANN) and genetic algorithms (GA) for predicting the worst response of mistuned bladed disk. ANN is used to predict the responses of bladed disk system which are used further in evaluation of fitness and constraint violation in GA process. A multilayer back-propagation neural network is trained with the results obtained from finite element model for different bladed disk configurations. Subsequently, GA is employed for arriving at optimum configuration of the bladed disk system by maximizing the blade responses. By integrating ANN with GA, the computational time required for obtaining optimal solution could be reduced substantially. The efficacy of this approach is demonstrated by carrying out studies on mistuned bladed disk systems for different sets of mistuning parameters, namely mistuning in modulus of elasticity and length of blades. Finally, the effect of adding shroud at the tip of blades in reducing the maximum response of the bladed disk system was investigated.     

LES Study of Flow Between Shrouded Co-rotating Disks

Large eddy simulations of turbulent flow between shrouded co-rotating disks, representing a simplified model of a hard disk drive, are performed. The computation domain surrounds a complete disk and is bounded at top and bottom by half a disk. Therefore, it is possible to compute the fluctuating pressure field surrounding the middle disk. Also, the influence of the shroud geometry is taken into account by comparing a flat shroud wall and a wall with rib chambers. In the flat shroud case, the fluctuating pressure on the upper- and lower-surface of a disk indicates a strong correlation with fluid motion travelling across the disk-tip clearance region. However, in the ribbed shroud case the organized flow structure that is observed in the flat shroud case disappears and the fluctuating pressure acting on the surface of the disk is remarkably diminished.     

Simultaneous measurements of disk vibration and pressure fluctuation in turbulent flow developing in a model hard disk drive

The complex flow features inside hard disk drive models are investigated in an axisymmetric and a semi-open shroud configurations. For the axisymmetric case, we have employed both experimental and computational approaches. The experiment focuses on both flow dynamics and the disk vibration, where measurements of the fluctuating pressure and velocity are undertaken at some representative points. The correlation between the disk vibration and the fluctuating pressure in the turbulent flow between disks is evident from the spectral analysis. The experimentally observed fluctuating pressure and velocity are partly due to the disk vibration and its contribution could be estimated by comparing the experiment with the results of a large eddy simulation. For the semi-open shroud case, although the characteristic peaks attributable to the large-scale vortical structure are still observed in the power spectra, the pressure fluctuation and the disk vibration are suppressed when the arm is inserted.     

High-speed stereoscopic PIV study of rotating instabilities in a radial vaneless diffuser

This paper presents an experimental analysis of the unsteady phenomena developing in a vaneless diffuser of a radial flow pump. Partial flow operating conditions were investigated using 2D/3C high repetition rate PIV, coupled with unsteady pressure transducers. Pressure measurements were acquired on the shroud wall of the vaneless diffuser and on the suction pipe of the pump, whereas PIV flow fields were determined on three different heights in the hub to shroud direction, inside the diffuser. The classical Fourier analysis was applied to both pressure signals to identify the spectral characteristics of the developing instabilities, and the high-order spectral analysis was exploited to investigate possible non-linear interaction mechanisms between different unsteady structures. A dedicated PIV averaging procedure was developed and applied to the PIV flow fields so as to capture and visualize the topology of the spectrally identified phenomena. The influence of these phenomena on the diffuser efficiency was also investigated.     

Thermoelastic Contact of a Shroud Ring and a Cylinder under Unsteady Friction-Induced Heat Release

Mathematical formulation is performed and a solution is found for a quasi-static thermoelastic problem of contact interaction of an elastic shroud ring and a hollow circular cylinder inserted into this ring, which are compressed by a load varied along the axis of the system, under the condition of an unloaded contact over the ring surface or over the circumference contour. The radial displacements of the contact surface of the shroud ring are approximated by displacements of the surface of a long circular hollow cylinder. Unsteady friction-induced heat release caused by the action of friction forces owing to shroud ring rotation over the cylinder with a time-dependent low angular velocity is taken into account. The problem is reduced to a system of integral equations whose structure is determined by the form of thermophysical contact conditions. A numerical algorithm of the solution is proposed, and the influence of the problem parameters on the contact pressure and temperature distributions is considered. Based on an analysis of results, a conclusion is made that the character of axial variation of the compressing load has a significant effect on the distribution of contact pressure in describing the kinematic condition of interaction of bodies in accordance with Hertz’s theory.__________Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 46, No. 4, pp. 161–178, July– August, 2005.     

基于多块嵌套结构动网格的拦截弹防热保护罩的二维分离模拟

在末制导阶段,拦截弹上的红外热保护罩要进行分离,分离引起的气动力变化将直接影响到导弹的制导精度.采用多块嵌套结构动网格技术数值模拟了拦截导弹的热保护罩的二维分离过程.给出了在整个分离过程中,两片保护罩运动的轨迹,并且给出了各个时间步对应的压力云图.预测了由于前激波而产生的作用在导弹上气动力的振荡.跟踪了在各个时刻流场对于导弹上红外窗口的影响.     

设置反拱加固的拱结构力学性能研究

提出了一种设置反拱结构的拱桥加固方法,该方法是通过在主拱圈拱肋下方设置反拱,在反拱和拱肋之间用竖杆相连,并通过抗弯预埋件和抗剪锚栓把反拱的拱脚和拱肋连接,使反拱结构和原主拱圈共同形成结构受力体系。本文基于有限元参数分析方法,通过设置6个不同参数:拱的矢高f1、拱的拱轴系数m1、反拱的矢高f2、反拱的拱轴系数m2、反拱与待加固拱的等效半径比i、反拱纵向长度与待加固拱的总跨径的比值Kr,以考虑不同拱桥、反拱结构参数对原拱桥关键截面内力、跨中挠度及整体屈曲系数的影响。基于大量计算数据的参数拟合,分别获得跨中弯矩、跨中挠度、拱脚弯矩、拱脚推力、整体屈曲系数的拟合表达式。通过对拟合数据的分析,获得了反拱加固的拱桥结构力学特性的相关变化规律。最后对一个100m跨径拱桥进行加固计算分析,结果表明:本文提出的加固方法不但可以显著提高待加固桥梁的整体刚度与稳定性,而且可有效地降低主拱关键截面的内力。     

Flow and performance characteristics of twin-entry radial turbine under full and extreme partial admission conditions

This paper presents numerical and experimental investigation of the performance and internal flow field characteristics of twin-entry radial inflow turbines at full and extreme partial admission conditions. The turbine is tested on a turbocharger test facility, which was developed for small and medium size turbochargers. Experimental results show that the lowest efficiency corresponds to extreme conditions. Therefore, flow field analyzing is employed to consider these conditions. The flow pattern in the volute and impeller of a twin-entry turbine is analyzed using an in-house fully three-dimensional viscous flow solver. The computational performance results are compared with the experimental results and good agreement is found. The flow field at the outlet of the turbine is investigated using a five-hole pressure probe; the numerical results are also compared with experimental measurements at the outlet of the rotor. For the volute, results show that lowest entropy gain factor corresponds to the extreme conditions, particularly when shroud side entry is fully closed. At the inlet of the rotor for equal admission conditions, the incidence angle is mostly in the optimum values. However, large variation in the incidence angle is seen in the extreme conditions, which lead to larger incidence losses and consequently a lower efficiency. In addition, entropy distribution contours corresponding to the exit plane are considered. For full admission, the location of low entropy gain factor at this plane occupies a region near the shroud side of suction surface as well as near the hub side of the pressure surface that corresponds to a region of high absolute flow angle. However, for the extreme cases, the low entropy gain factor occupies a relatively larger region near the shroud side than full admission. So, higher loss generation is noted at the extreme cases. Moreover, this entropy gain factor region is increased when shroud side entry is fully closed.     

Highly spatially resolving laser Doppler velocity measurements of the tip clearance flow inside a hard disk drive model

The flow in the tip clearance of a hard disk drive model has been investigated with laser Doppler techniques. The flow was driven by co-rotating disks inside a cylindrical enclosure in order to simulate a hard disk drive used for data storage devices. The main focus of the investigation was on the understanding of complex flow behavior in the narrow gap region between the disk tip and the outer shroud wall, which is supposed to be one of the causes of flow induced vibration of the disks. Experiments in the past have never been able to examine this region because of the lack of the spatial resolution of sensors in the highly three-dimensional flow in the region. In the present investigation, the flow velocity in the tip clearance region was measured with optical measurement techniques for the first time. The flow behaviors are investigated for four different conditions with two different gap widths and two different shapes of the shroud walls with and without ribs. The velocity measurements were taken both with conventional laser Doppler velocimetry and using a laser Doppler velocity profile sensor with a spatial resolution in the micrometer range. The circumferential velocity component was measured along the axial and radial directions. The steep gradients of the circumferential mean velocity in both directions were successfully captured with a high spatial resolution, which was achieved by the velocity profile sensor. From the supplementary investigations, the existence of vortex structures in the tip clearance region was confirmed with a dependence on the shroud gap width and the shroud shape. The interactions of the two boundary layers seem to be the source of the complex three-dimensional behaviors of the flow in this region.