基于叶尖定时的旋转叶片同步振动辨识新方法

为掌握旋转叶片在不同工作转速下的振动特性,利用叶尖定时测振系统对旋转叶片进行振动测试。分析了基于变速扫频测量的速矢端迹法理论,设计了一种多传感器辨识叶片同步振动的新方法。运用该方法对某型号航空设备的旋转叶片进行振动测量实验,准确地辨识出不同转速下旋转叶片的振动倍频、动频、振幅及阻尼系数等参数。频率和振幅辨识重复性精度分别高达0.0072Hz和5.7um。正确绘制出叶片振动坎贝尔图,实验辨识结果与叶片理论设计结果基本一致。     

磁致伸缩层合悬臂梁式作动器的振动分析

为了分析磁致伸缩薄膜型层合悬臂梁式作动器的振动问题,应用磁致伸缩材料的非线性本构关系,由哈密尔顿原理导出了双层悬臂梁的振动微分方程。采用分离变量方法和常微分方程组的解析解法对磁致伸缩薄膜型层合悬臂梁的自由振动和受迫振动进行了理论分析。数值算例表明本文计算结果与有限元结果吻合较好,从而佐证了本文理论模型和求解方法的正确性,并讨论了几何参数、材料参数对层合梁固有频率的影响。还分析了在周期输入磁场激励下悬臂梁的挠度响应,且挠度响应呈现出倍频效应的动态特性。      

旋转叶片异步振动全相位FFT辨识方法

基于叶尖定时的旋转叶片振动测量技术属于严重的欠采样方法.为实现旋转叶片异步振动辨识,分析了基于叶尖定时的异步振动信号模型,设计了一种利用全相位FFT分析技术的多传感器遍历的异步振动辨识方法,从理论上推导了全相位FFT以及多传感器遍历算法,并进行了计算机仿真验证.运用该方法在某型号航空设备的旋转叶片完成振动测量实验,实验结果表明,叶片异步振动辨识结果与叶片理论设计基本一致.成功解决了叶片异步振动欠采样问题,进一步完善了叶尖定时测振系统.     

旋转叶片异步振动的频率识别技术

基于非接触式叶尖定时测振原理，针对叶片异步振动的欠采样问题，采用“5＋2”双采样速率方案进行采样，通过频率辨识技术来获得叶片的真实振动。将实验测得的振动频率与应变片法测量结果进行比对表明，所测频率与叶片振动的坎贝尔曲线一致，是叶片振动的真实频率。同时，比对结果验证了测量方案的正确性，也说明了该辨识技术具有很高的实际应用价值。     

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.     

Particle swarm-based structural optimization of laminated composite hydrokinetic turbine blades

Composite blade manufacturing for hydrokinetic turbine application is quite complex and requires extensive optimization studies in terms of material selection, number of layers, stacking sequence, ply thickness and orientation. To avoid a repetitive trial-and-error method process, hydrokinetic turbine blade structural optimization using particle swarm optimization was proposed to perform detailed composite lay-up optimization. Layer numbers, ply thickness and ply orientations were optimized using standard particle swarm optimization to minimize the weight of the composite blade while satisfying failure evaluation. To address the discrete combinatorial optimization problem of blade stacking sequence, a novel permutation discrete particle swarm optimization model was also developed to maximize the out-of-plane load-carrying capability of the composite blade. A composite blade design with significant material saving and satisfactory performance was presented. The proposed methodology offers an alternative and efficient design solution to composite structural optimization which involves complex loading and multiple discrete and combinatorial design parameters.     

Failure of last-stage turbine blades in a geothermal power plant

This paper presents an investigation into causes of failure of geothermal steam turbine blades. Several L-0 blades of geothermal steam turbines of 110 MW capacity suffered failures, causing forced outages of the turbines. To assess the causes of failure, the natural frequencies of the blades installed on the rotor were measured in the laboratory. The measured frequencies were compared with the natural frequencies calculated through a finite-element analysis (FEA) of the blade. The FEA was also used to calculate the vibratory stresses on the blade numerically. Also, the investigation analyzed the operational data and the history of the blade failures on several rotors of different units from the same system. The results of previous repairs were reviewed, and metallurgical investigations were conducted to identify the mechanical and metallurgical modes of failure. The results of the investigation showed that the fracture of two blades was attributed to installation and manufacturing errors and aggravated by general deterioration of the blades. The deterioration was caused by the erosion and corrosion process that resulted from moisture condensation in the steam.     

磁致伸缩铺层阻尼板壳结构的振动分析

通过理论分析讨论了含磁致伸缩材料和黏弹性材料铺层的层合板壳结构的频率和损失因子。假设黏弹性层仅发生剪切变形, 对磁致伸缩层应用偏置磁场下的线性本构, 推导得到由磁致伸缩层、黏弹性层、复合材料基本层组成的约束阻尼薄壳结构的运动方程, 并求得结构振动频率和损失因子的解。对板、曲板等算例的计算结果表明, 用磁致伸缩材料作约束层可使层合结构损失因子提高。      

Vibration analyses of general thin and moderately thick laminated composite curved beams with variable curvatures and general boundary conditions

Abstract

An exact semianalytical method for vibration analysis of general thin and moderately thick laminated composite curved beams with variable curvatures and general boundary conditions is presented. In the framework of the first-order shear deformation theory, the method combines the variational principle and multilevel partition technique. As one of the innovation points, the general boundary conditions are enforced by using the virtual boundary spring technology. Each of the fundamental beam unknowns is then invariantly expanded as Jacobi polynomials. The convergence study and numerical verifications of the laminated composite curved beams with various boundary conditions are carried out.     

Buckling and free vibration of non-homogeneous composite cross-ply laminated plates with various plate theories

Various theories of homogeneous laminated plates are extended to study the buckling and free vibration behavior of non-homogeneous rectangular composite laminates. The equations governing the dynamic response of non-homogeneous composite laminates are deduced. Numerical results for the natural frequencies and critical buckling loads of symmetric cross-ply laminates are presented. The influences of the degree of non-homogeneity, aspect ratio, thickness ratio and in-plane orthotropy ratio on the natural frequencies and critical buckling loads are investigated. The results obtained for homogeneous cases are compared with their counterparts in the literature. The study concludes that the classical plate theory is inadequate for predicting the structural response of non-homogeneous laminates, and that the free vibration and the state of the stability are affected strongly by the degree of nonhomogeneity.     

Using finite element analysis/optimum design in the determination of elastic constants by vibration testing

Abstract

Combining vibration testing and numerical methods is a potential alternative approach for determining elastic constants of materials because of nondestructive testing, single testing, and producing average properties. In order to simplify the modeling processes and to reduce complicated derivations in the numerical method, the combination of finite element analysis and optimum design is adopted in this work to inversely calculate the elastic constants. In this method, the effects of some parameters, including the finite element mesh, the mode number, constraints on state variables, the optimization method, and initial values and loops, are discussed. It is proved that the present method with 10×10 mesh, 6 vibration modes, 5% constraint on state variables, and subproblem approximation can obtain accurate results. Average values can be used to avoid the scatter in results due to different initial values, and do‐loops may not be necessary. It is also clearly demonstrated that the present method can correctly extract 2 or 5 elastic constants for isotropic or orthotropic materials.     

基础简谐激励下匀速旋转运动电流变夹层梁的振动稳定性

摘 要：建立了基础激励和定轴转动联合作用时电流变夹层梁的运动微分方程,着重研究了基础简谐激励和匀速旋转运动作用时电流变夹层梁的振动稳定性。采用多尺度法获得了梁的一次近似解析解和参激振动失稳的条件。通过对电流变夹层梁在不同激励参数、控制电场和旋转角速度时的振动响应时间历程曲线和对应相图的数值分析,探讨了电场作用下电流变夹层梁的参激振动稳定性。仿真结果表明,在一定的条件下,可以通过控制作用于电流变夹层梁的电场强度来改变系统出现运动不稳定的临界激励幅值,提高结构的动力稳定性。     

先进生物质复合材料在风电叶片中的应用

竹材是生长速度快、性能好的生物质材料之一。由于竹材外侧性能远高于内侧, 采用分级加工方法可制备由外侧到内侧的A、B、C、D 级竹层积材。通过与其他风电叶片材料比较, A 级竹篾层积材的性能超过了目前风电叶片使用的木层积材, 与玻璃纤维增强塑料的性能接近。用这种先进生物质复合材料制作的新一代风电叶片, 具有可再生性、加工消耗能源少、无废弃物、成本低、废旧产品易于处理等一系列优点。      

Free vibration analysis of generally laminated beams via state-space-based differential quadrature

A new method of state-space-based differential quadrature is presented for free vibration of generally laminated beams. By discretizing the state space formulations along the axial direction using the technique of differential quadrature, new state equations at discrete points are established. Applying end conditions and using matrix theory, the general solution is derived. Taking account of the boundary conditions at the top and bottom planes, frequency equation governing the free vibration of generally laminated beams is then formulated. The method is validated by comparing numerical results with that available in the literature.     

A pseudo-fully stressed design approach for optimum design of steel frames

An iterative approach based on the fully-stressed design concept employing scaling to find an efficient search path to the optimum design is developed for statically indeterminate elastic frames subjected to behavioural constraints on member stresses and nodal displacements, and side constraints on member sizes. In this approach the fully stressed solution, which recognizes only the stress constraints, is scaled to the boundary of the feasible design region by employing the other constraints on the structure. The inactive constraints in an iteration are identified by the Kuhn-Tucker conditions. The computed stresses of the inactive constraints, for the time being, are considered to be the allowable values in order to develop a pseudo-fully stressed solution with a new set of allowable stresses. Convergence takes places when the normalized change in the value of the objective function between the scaled and unsealed pseudo-fully stressed designs is less than a specified tolerance. The method employs the established relationships between sectional area, section modulus and moment of inertia of W-shapes to express the objective and constraint functions in terms of one design variable for each member. The efficiency and accuracy of the method in optimization of structural steel frames is demonstrated by sample problems designed for stress, displacement and minimum size constraints. The algorithm is verified against published results.     

《小型航空涡轮增压器叶片强度振动研究》

在进行的某型航空活塞发动机废气涡轮增压器气动和结构改进设计的基础上,针对涡轮增压器叶片强度振动问题进行分析。计算结果表明,在工作转速范围内,叶片不会出现强度和振动问题,满足工程使用要求。     

Random response of a rotating composite blade with flexure–torsion coupling effect by the finite element method

A finite element model is employed to investigate the mean square response of a damped rotating composite blade with flexure–torsion interaction under stationary or non-stationary random excitation. The effects of transverse shear deformation and rotary inertia are considered. The finite element model can satisfy all the geometric and natural boundary conditions of a thick blade. The blade is considered to be subjected to white noise, band-limited white noise or filtered white noise excitation. The numerical results indicate that the increment of rotational speed will reduce the mean square response. It is also found that the mean square response decreases when the low natural frequency of base decreases. Inversely, the mean square response increases when the high natural frequency of base decreases. It is also shown that the fiber orientations have a significant effect on the mean square response of an orthotropic blade under random excitations. Moreover, the flexure–torsion coupling effect on the mean square response is changed by different fiber orientations.     

Free vibration analysis of thick laminated plates using a mixed finite element

Abstract

A mixed finite element scheme based on assumed local high‐order displacements is proposed for the free vibration of thick laminated plates. The effects of transverse shear deformation, transverse normal stress and rotary inertia are considered in the formulation. Cross‐ply laminates with simple supports and angle‐ply laminates with clamped edges are presented as examples. The three dimensional elasticity solutions of cross‐ply laminates with simple supports are used to assess the accuracy of the present scheme. The effects of the span‐to‐thickness, aspect and material anisotropy ratio on the fundamental natural frequency are investigated. The present results are compared with the results in the published literature, and agree closely with the 3‐D elasticity solutions.     

Active control of functionally graded laminated cylindrical shells

An analytical method on active vibration control of smart FG laminated cylindrical shells with thin piezoelectric layers is presented based on Hamilton’s principle. The thin piezoelectric layers embedded on inner and outer surfaces of the smart FG laminated cylindrical shell act as distributed sensor and actuator, which are used to control vibration of the smart FG laminated cylindrical shell under thermal and mechanical loads. Here, the modal analysis technique and Newmark’s integration method are used to calculate the dynamic response of the smart FG laminated cylindrical shell with thin piezoelectric layers. Constant-gain negative velocity feedback approach is used for active vibration control with the structures subjected to impact, step and harmonic excitations. The influences of different piezoelectric materials (PZT-4, BaTiO₃ and PZT-5A) and various loading forms on the active vibration control are described in the numerical results.     

Forced vibration and low-velocity impact of laminated composite plates

The layerwise theory of Reddy is used to study the low velocity impact response of laminated plates. Forced-vibration analysis is developed by the modal superposition technique. Six different models are introduced for representation of the impact pressure distribution. The first five models, in which the contact area is assumed to be known, result in a nonlinear integral equation similar to the one obtained by Timoshenko in 1913. The resulting nonlinear integral equation is discretised using a time-element scheme. Two different interpolation functions, namely: (i) Lagrangian and (ii) Hermite, are used to express the impact force. The Hermitian polynomial-based representation, obviously more sophisticated, is introduced to verify the Lagrangian-based representation. Due to its modular nature the present numerical technique is preferable to the existing numerical methods in the literature. The final loading model, in which the time dependence of the contact area is taken into account according to the Hertzian contact law, resulted in a relatively more complicated but more realistic, nonlinear integral equation. The analytical developments concerning this model are all new and are reported for the first time in this paper. Also a simple, but accurate, numerical technique is developed for solving our new nonlinear integral equation which results in the time-history of the impact force. Our numerical results are first tested with a series of existing example problems. Then a detailed study concerning all the response quantities, including the in-plane and interlaminar stresses, is carried out for symmetric and antisymmetric cross-ply laminates and important conclusions are reached concerning the usefulness and accuracy of the various plate theories. This paper, presented at a symposium to celebrate the Golden Jubilee of the Aerospace Department, Indian Institute of Science, Bangalore first appeared as a paper inComputational Mechanics (1994) 13: 360–379