级间接触耦合的失谐叶盘模态局部化问题研究

基于有限元实体建模方法,建立了燃气轮机拉杆转子中两级叶盘系统有限元模型,分析比较了有无级间接触耦合作用下叶盘系统的模态特性,重点研究了轮盘级间接触耦合效应对叶盘系统频率转向特性的影响。研究表明,级间接触耦合作用下出现了叶盘耦合振动的复杂振动形式,振动能量不再局限于单级叶盘;级间耦合作用导致叶盘系统的频率转向特性发生改变,频率转向区内的模态不再高度密集,降低了叶盘系统对失谐的敏感度。建立了叶片刚度失谐的两级叶盘系统有限元模型并进行模态分析,结果显示失谐叶盘系统模态局部化程度较低。     

基于微动滑移摩擦模型的失谐叶盘系统振动分析

在航空发动机叶-盘系统中,由于叶片失谐导致严重的振动局部化,造成局部叶片的高周疲劳,拟采用增加叶根干摩擦的方法降低失谐叶-盘系统振动幅值,减轻其振动局部化程度。基于微动滑移摩擦模型建立叶根阻尼器干摩擦力本构关系,采用等效椭圆代替阻尼器力与位移函数关系的迟滞回线,获得阻尼器的等效阻尼、等效刚度;将等效阻尼、等效刚度作用于叶-盘系统集中参数模型上,建立单个扇区三自由度整周失谐叶-盘系统动力学方程;采用谐波平衡法对其进行振动特性分析,讨论了叶根干摩擦对失谐叶盘系统振动特性的影响。结果表明:叶根摩擦能显著降低系统共振幅值;有叶根摩擦系统较无叶根摩擦系统的共振峰在频率上延后;增加叶根摩擦可有效降低失谐叶-盘系统的振动局部化程度。     

裂纹叶片分布对失谐叶盘结构振动特性的影响*

摘要：基于有限元实体建模方法,建立了含穿透型裂纹的失谐叶盘结构有限元模型,揭示了两个裂纹叶片的分布情况对失谐叶盘结构振动特性的影响规律。研究表明,两个裂纹叶片的分布情况对失谐叶盘结构的基频以及模态局部化程度均有较大影响,并发现当两个裂纹叶片处于相邻位置时,失谐叶盘结构的基频最小,模态局部化程度最高,且该现象在弱耦合条件下尤为突出。而离心力(转速)对含两个裂纹叶片的失谐叶盘结构振动局部化有减弱作用。     

含摩擦与间隙的失谐叶盘系统振动局部化研究

 针对叶片榫头与轮盘榫槽连接处间隙及摩擦,基于叶盘结构典型集中参数模型,建立含干摩擦、间隙的非线性动力学方程,研究失谐叶盘系统振动局部化。在叶身刚度随机失谐下分析叶盘系统对不同耦合刚度的固有特性及共振响应。结果表明,非线性谐调叶盘系统亦出现振动局部化现象。利用振幅放大系数对线性、非线性失谐叶盘系统振动响应局部化研究,振幅放大系数呈失谐阈值现象,且非线性干摩擦、间隙作用会降低失谐系统振动响应局部化程度。而谐调叶盘系统非线性振动,随气流激励力频率变化,系统呈非简谐单周期运动、多周期谐波运动、混沌运动等多种动力学行为。失谐因素存在会使非线性失谐叶盘系统动力学行为更复杂。     

失谐叶盘结构振动响应局部化实验研究

基于作者提出的预测失谐叶盘结构最大失谐幅值放大系数及最坏失谐模式的方法,利用搭建的行波激励实验系统,针对典型的整体叶盘结构模型试件进行了失谐振动响应局部化实验。首先通过有限元仿真确定失谐叶盘振动响应局部化实验所需的最坏失谐模式,然后经过数据采集与后处理得到行波激励下失谐叶盘结构的强迫响应,通过实验验证了失谐跳变-强迫响应局部化现象,实验结果与理论分析取得较好一致性。     

基于硬涂层的主动失谐整体叶盘建模与分析

通过在整体叶盘各扇区叶片上涂敷不同厚度的硬涂层可以将主动失谐减振与硬涂层阻尼减振技术简单而有效地应用于整体叶盘。为了探究该方法的减振特性,首先给出了利用单个失谐扇区的结构矩阵组集成完整主动失谐叶盘结构矩阵的方法,并利用泰勒展开和最小二乘法建立了叶片上的涂层厚度与涂层引起的叶片失谐矩阵这两者的近似关系。在此基础上,利用公称模态子集法对失谐叶盘结构进行减缩建模。接着,通过与完整有限元的计算结果对比验证了所提出的近似关系与减缩模型的正确性。最后,利用该减缩模型和蒙特卡罗模拟分析了行波激励下基于硬涂层的主动失谐叶盘振动特性。研究表明:叶盘基体随机失谐下,该方法可以明显降低整体叶盘的响应水平。     

含裂纹离心压缩机叶轮结构的振动局部化

针对离心压缩机在复杂运行工况下的失谐与裂纹问题,研究裂纹与失谐对叶轮结构振动响应和振动局部化的影响规律。首先,采用三维有限元模型建立具有复杂几何形状的叶轮结构的定量分析模型,并通过在裂纹界面上定义接触的形式模拟裂纹的呼吸效应。其次,通过采用混合界面模态综合法对系统自由度进行缩减,以解决了采用三维有限元模型分析非线性系统动态响应时所存在的计算量大和收敛困难的问题。最终,采用Monte Carlo方法对含裂纹的失谐叶轮结构进行统计分析,研究随机失谐和裂纹故障对叶轮结构振动局部化的影响规律。结果表明裂纹和失谐都会对结构的振动响应产生显著的影响,并会导致振动能量的集中和振动局部化现象。     

多级叶盘结构随机失谐响应特性分析

为研究多级叶盘结构最大失谐强迫响应幅值及最坏失谐模式,通过没置失谐变量为优化变量,提出了运用遗传算法和序列二次规划混合方法确定最大的失谐强迫响应幅值及最坏失谐模式的通用方法.针对典型三自由度扇区单级和耦合两级叶盘结构集中参数模型计算了相应谐凋系统叶片刚度失谐时的最大失谐幅值放大系数及最坏失谐模式,揭示了失谐跳变-局部化...     

考虑失谐的弱耦合周期天线结构的振动主动控制研究

建立了弱耦合周期天线结构的动力学计算模型,基于该模型研究了结构失谐前后的振动特性;并应用最优控制方法,对该结构失谐前后振动的主动控制进行了研究;数值仿真结果表明：弱耦合周期天线结构参数的小量失谐会导致结构振动模态产生明显的局部化,失谐前后的振幅之比约为30%;在进行此种结构的振动主动控制时必须考虑失谐的影响,否则会导致振动控制系统的失效。     

抑制失谐星载天线振动局部化的失谐优化及控制改善

为了抑制随机失谐星载天线结构的振动局部化及其导致的振动控制失效问题,建立了径向肋天线结构的单肋多自由度集中参数模型,提出了一种衡量结构整体振动模态品质的局部化因子;分析了失谐肋的安装顺序对结构整体模态振型的影响,利用遗传算法对失谐肋的安装顺序进行了减振优化,并评估了失谐优化对天线振动控制系统性能的提升。结果表明,对于一组具有特定随机失谐参数的径向肋,基于本文的模态局部化因子和智能搜索算法可以快速、准确地得到其最优或近似最优安装顺序,不仅能大大改善天线整体振动模态品质、降低结构振动响应,还能提高天线结构控制系统效能。     

Reliability-oriented optimal design of intentional mistuning for a bladed disk with random and interval uncertainties

When interblade coupling is weak, the dynamic response of a bladed disk is very sensitive to the presence of uncertainties. Excessive response variation can be very harmful. Previous studies have indicated that introducing blade-to-blade difference in nominal design, known as intentional mistuning, could reduce the level of response variation. In this research, an efficient computational framework that yields the optimal design of intentional mistuning is developed to maximize the bladed disk reliability. Both the random uncertainty of blades and the interval uncertainty of disk connections are considered. The Metropolis–Hastings algorithm is applied to find the worst case response under interval uncertainty, and Monte Carlo simulation is employed to account for the random mistuning effect. A gradient-based approach is then established to find the minimum design modification needed to achieve a designated reliability level. Case studies are carried out to illustrate the effectiveness of the proposed method.     

Genetic particle swarm parallel algorithm analysis of optimization arrangement on mistuned blades

This article introduces a method of mistuned parameter identification which consists of static frequency testing of blades, dichotomy and finite element analysis. A lumped parameter model of an engine bladed-disc system is then set up. A bladed arrangement optimization method, namely the genetic particle swarm optimization algorithm, is presented. It consists of a discrete particle swarm optimization and a genetic algorithm. From this, the local and global search ability is introduced. CUDA-based co-evolution particle swarm optimization, using a graphics processing unit, is presented and its performance is analysed. The results show that using optimization results can reduce the amplitude and localization of the forced vibration response of a bladed-disc system, while optimization based on the CUDA framework can improve the computing speed. This method could provide support for engineering applications in terms of effectiveness and efficiency.     

Free transverse vibration of rotating blades in a bladed disk assembly

This paper investigates the natural frequency of free transverse vibration of blades in rotating disks to examine the relationship of natural frequencies, blade stiffness and nodal diameters to study how neighboring blades react upon each other and affect blade natural frequency. With the use of elastic hinge theory and a cantilever beam model subjected to either a transverse concentrated force or a bending moment at the free end, the force-deflection stiffness/moment-rotation stiffness of the beam have been developed. Thereafter, the reaction forces and moments from the neighboring blades have been determined without the need for an exact solution of large deformation of cantilever beams including geometrical nonlinearity effects. With the use of the energy conservation principle and modal theory, the natural frequency of free transverse vibration of blades in rotating disks has been determined for any nodal diameter. A comparison of the analytical and finite element solutions for a bladed disk with uniform aerofoils shows that the analytical method presented in this paper is accurate.     

Vibration based damage detection of rotor blades in a gas turbine engine

This paper describes the problems concerning turbine rotor blade vibration that seriously impact the structural integrity of a developmental aero gas turbine. Experimental determination of vibration characteristics of rotor blades in an engine is very important from fatigue failure considerations. The blades under investigation are fabricated from nickel base super alloy through directionally solidified investment casting process. The blade surfaces are coated with platinum aluminide for oxidation protection. A three dimensional finite element modal analysis on a bladed disk was performed to know the likely blade resonances for a particular design in the speed range of operation. Experiments were conducted to assess vibration characteristics of bladed disk rotor during engine tests. Rotor blade vibrations were measured using non-intrusive stress measurement system, an indirect method of blade vibration measurement utilizing blade tip timing technique. Abnormalities observed in the vibration characteristics of the blade tip timing data measured during engine tests were used to detect the blade damage. Upon disassembly of the engine and subsequent fluorescent penetrant inspection, it was observed that three blades of the rotor assembly were identified to have damaged. These are the blades that exhibited vibration abnormalities as a result of large resonant vibration response while engine tests. Further, fractographic analysis performed on the blades revealed the mechanism of blade failures as fatigue related. The root cause of blade failure is established to be high cycle fatigue from the engine run data history although the blades were put into service for just 6 h of engine operation.