Vibrations measurements for shrouded blades of steam turbines based oneddy current sensors with high frequency response

With the development of power plants towards high power and intelligent operation direction,the vibrations or failures of blades,especially the last stage blades in steam turbines,happen more frequently due to the unstable operating conditions brought by flexible operation.A vibration measuring method for the shrouded blades of a steam turbine based on eddy current sensors with high frequency response is proposed,meeting the requirements of non-contact heath monitoring.The eddy current sensors produce the signals which are related to the area changing of every blade’s shroud resulting from the rotation of stator.Then an improved blade tip timing(BTT)technique is proposed to detect the vibrations of shrouded blades by measuring the arrival time of each area changing signal.A structure of eddy current sensors is developed in steam turbines and an amplitude modulation/demodulation circuit is designed to improve the response bandwidth up to 250 kHz.Vibration tests for the last stage blades of a steam turbine were carried out and the results validate the efficiency of the improved BTT technique and the high frequency response of the eddy current sensors presented.

Multi-probe linear fitting and time of arrival linear correction method to analyze blade vibration based on blade tip timing without once-per-revolution

Blade vibration monitoring can ensure the safe operation of aeroengine rotor blades.Among the methods of blade vibration monitoring,Blade Tip Timing(BTT)method has attracted more and more attention because of its advantages of non-contact measurement.However,it is difficult to install the Once-Per-Revolution(OPR)probe in the confined space of aeroengine,and the failure and instability of the OPR signal will reduce the reliability of the blade vibration analysis results,which directly affects the accuracy of the blade vibration parameters identification.The Multi-Probe linear fitting and Time of Arrival(ToA)Linear Correction method based on the BTT(MP-LC-BTT)without OPR is proposed to reduce the errors of single probe linear fitting method for blade vibration displacement analysis.The proposed method can also correct the calculation error of blade vibration displacement due to the nonlinear change of rotation speed,which can improve the analysis accuracy of the blade vibration displacement.A new blade vibration model conforming to the actual vibration characteristics is established,and the effectiveness of the proposed method is verified by numerical simulation.Finally,the reliability and accuracy of the MP-LC-BTT method have been verified by the experiments which include two high-speed blade test-benches and an industrial axial fan.This method can be used in the actual aero-engine monitoring instead of the BTT method with OPR.

基于叶尖定时数据奇异值分解的振动事件识别

叶尖定时数据自动化测量及处理是旋转机械在线监测和智能运维的必要环节,快速、准确判断叶片振动类型,实现振动事件识别是数据自动化测量及处理的关键。提出了一种基于加窗叶尖定时数据奇异值分解的振动事件识别方法,仅需单只传感器准确识别叶片同步、异步振动事件。基于不同叶片叶尖定时数据时延特性,加窗构造了“类重构吸引子矩阵”,根据矩阵奇异值特征实现振动事件识别。开展了方法仿真及实验验证,仿真与实验结果一致性良好,压气机试验件测试数据表明,叶片发生振动事件时第1奇异值增大为7倍以上,其中发生异步振动事件时第2奇异值增大为14倍以上,提出方法能够准确识别叶片同步、异步振动事件。

无转速同步下叶片同步振动参数辨识误差修正

叶片振动非接触在线测量是保障大型旋转机械健康高效运行的重要环节,振动参数的精确辨识是叶片振动高精度测量的关键。无转速同步下,传统基于叶尖定时的叶片同步振动参数辨识方法忽略了叶片振动带来的时间误差,直接影响了参数辨识精度。为修正无转速同步下的叶片同步振动周向傅里叶拟合误差,提出了一种改进的叶片同步振动参数高精度辨识方法。利用叶片振动角位移,修正叶片到达时刻,优化传感器之间的振动位移差测量模型,提高了叶片振动幅值及振动倍频的辨识精度。开展了仿真和实验验证,二者结果一致性良好,在振动倍频值10、6、5处,改进方法与传统方法相比,信号恢复精度分别提高11.79μm、5.21μm、3.26μm,所提方法具有良好的误差修正效果。

基于参考键相动态追踪的无转速叶尖定时测量方法

针对叶尖定时系统在测量转子叶片振动过程中转速同步传感器安装困难的问题,提出基于参考键相动态追踪的叶尖定时测量方法。假设整级转子叶片间存在随机失谐,则在变转速工况下各叶片并非同时达到共振状态,在每转内,利用各叶片到达传感器的实测到达时间,计算叶片在相邻叶尖定时传感器间的局部平均转速与转子整圈平均转速的偏差值,判断同级所有叶片的振动状态,选择几乎不振动的叶片作为该圈的参考键相,计算目标叶片在该圈的振动位移值,依此类推,计算各圈目标叶片的振动位移,实现转子叶片在无转速参考下的非接触式振动测量。试验验证结果表明,与传统叶尖定时方法相比,利用该方法计算出的叶片振动位移所辨识出的叶片振动频率相对误差小于0.2%,振动位移相对误差小于10%,说明基于参考键相动态追踪的叶尖定时测量方法不仅能在无转速参考的情况下准确计算出叶片的振动位移,更能准确地辨识出叶片振动参数。

旋转叶片流固耦合振动对叶端定时测振的影响

叶端定时是一种先进的旋转叶片在线振动监测方法,但其测量准确性受其测点位置变化影响较大,如何选取合适的测点具有重要研究价值。为考虑叶片颤振及其流固耦合振动对测点位置的影响,设置流场圆柱绕流产生涡阶,并对不同转速和裂纹位置下旋转叶片的扭转情况进行分析。计算比较离心载荷时正常叶片的扭转振动,流固耦合下正常叶片、裂纹叶片的扭转振动及叶端各点扭转偏移量对叶端定时测振测点位置的影响。结果表明:流固耦合作用下,转速和裂纹位置对叶片的扭转振动影响较大;叶端定时测振传感器在转速较低时应安装在靠近叶片前缘处,而转速较高时应安装在靠近叶端中间位置。

双叉式叶尖结构对风力机功率与振动的影响研究

为改良风力机的振动性能,提出一种用于小型风力机叶片的双叉式叶尖结构改型设计方案,对改型后不同叶尖夹角的双叉式叶尖结构风力机叶片进行外特性测试与振动特性试验,得到叶片的输出功率以及振动频率。通过与未改型叶片的对比发现:双叉式叶尖结构在(3~9)m/s的低风速段和中风速段能提高风力机的输出功率;双叉式叶尖结构可以调整风轮振动频率曲线的走势,使风轮更快地脱离共振区,且使共振转速更远离额定转速。由此可见双叉式叶尖结构能有效地改良风力机的振动性能。其中叶尖夹角为90°的双叉式叶尖结构叶片性能最优。

A novel none once per revolution blade tip timing based blade vibration parameters identification method

The vibration caused blade High Cycle Fatigue(HCF)is seriously affects the safety operation of turbomachinery especially for aero-engine.Thus,it is crucial important to identify the blade vibration parameters and then evaluate the dynamic stress amplitude.Blade Tip Timing(BTT)method is one of the promising method to solve these problems.While,it need a high resolution Once Per Revolution(OPR)signal which is difficult to get for the aero-engine.Here,a Coupled Vibration Analysis(CVA)method for identifying blade vibration parameters by a none OPR BTT is proposed.The method assumes that every real blade has its own vibration performance at a given speed.Whereby,it can take any blade as the reference blade,and the other blades using the reference blade as the OPR for vibration displacement calculating and further parameter identifying.The proposed method is validated by numerical model.Also,experimental studies are carried out on a straight blade and a twisted three dimensional blade test rig as well as a large industrial axial compressor respectively.The results show that the proposed method can accurately identify the blade synchronous vibration parameters and quantitatively evaluate the mistuning in bladed disks,which lays a foundation for the reliability improvement of aero-engine.

Lock-in phenomenon of tip clearance flow and its influence on aerodynamic damping under specified vibration on an axial transonic compressor rotor

In this study,the lock-in phenomenon of Tip Clearance Flow(TCF)instabilities and their relationship to blade vibration are investigated numerically on an axial transonic rotor with a large tip clearance.The capabilities of simulating instability flow and lock-in phenomenon are verified on a transonic rotor and a NACA0012 airfoil by comparing with the test data,respectively.The lock-in phenomenon is first numerically confirmed that may occur to TCF instabilities when its frequency is close to the blade vibration frequency.The lock-in region becomes wider with the vibration amplitude increasing,and it is also affected by modal shapes.For the rotor at the simulation conditions in this study,the bending mode results in a wider lock-in region than the torsional mode.In the lock-in region,the phase difference between the Tip Clearance Vortex(TCV)and the blade vibration changes with the flow condition and the frequency ratio of the blade vibration and the TCV instabilities.The frequency of the TCV instabilities reduces with the mass flow decreasing.Therefore,reducing mass flow and increasing frequency ratio have similar effects on the TCV phase,which causes a significant variation on the unsteady pressure amplitude in the blade tip area.Thus,the aerodynamic damping changes significantly with the TCV phase.The aerodynamic damping displays a nonlinear relationship with the vibration amplitude,and it changes from negative to positive with the vibration amplitude increasing at the same frequency ratio.The negative damping is mainly provided by the tip area of the blade.For unlocked conditions,the period of the TCF instabilities fluctuates over time,and it cannot be directly separated by their frequency features.Inter Blade Phase Angle(IBPA)also has an important influence on the feature of the TCV instabilities.The occurrence of frequency lock-in also requires“appropriate”IBPA.For the examined working conditions,the frequency lock-in occurs under 0 ND(Nodal Diameter),but not under 8 ND.However,no matter 0 ND or 8 ND,the phase of TCV always locks onto the IBPA at the examined conditions.

基于叶尖定时的非接触式旋转叶片异步振动分析

基于叶尖定时原理设计一套旋转叶片振动实时检测系统,该系统主要由光纤传感、数据采集、振动分析三个部分组成。光纤传感的核心是叶尖定时传感器和光电转换模块的设计,数据采集实现对转换后的脉冲数据进行高速采集、预处理和与计算机之间的高速通信,振动分析则由计算机软件进行实时处理并显示分析结果。整套系统在现场某大型压气机上进行了原理性验证,同时在高速模拟转子上通过了实时性验证,异步振动分析结果与应变片监测的数据完全吻合,保证了整套系统最终应用于压气机叶片振动的在线实时监测。

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。

基于叶尖定时的旋转机械叶片振动信号重建

基于叶尖定时原理采集的旋转机械叶片振动信号是离散的欠采样信号,利用插值法对其重建的时域信号能反映叶片振动峰值等参数特征,为故障诊断提供依据。通过分析简谐振动的数学模型和信号采样及重构定理,提出在匀转速下利用若干均匀安装在机匣上的叶尖定时传感器采集叶片振动信息进行振动位移信号重建的新方法。利用高阶B样条函数构建的插值核函数具有快速收敛的特点,在减小信号截断误差的同时降低了算法复杂度,利于工程应用。介绍信号重建误差的来源,其测量精度对转速稳定性有较高要求,通过计算机仿真和模拟振动平台气激试验分析该方法性能,验证其在实践中的有效性。

基于叶尖定时的旋转机械叶片振动频率辨识ESPRIT方法

基于叶尖定时原理采集的旋转机械叶片振动信号是多频率混叠的欠采样信号,通过分析振动信号的数学模型,提出了在均匀转速下利用两个叶尖定时传感器构成有延迟的双通道,采用旋转不变子空间技术(ESPRIT)辨识多个叶片振动频率的新方法。介绍该方法的理论依据,推导了频率估计解模糊的具体步骤,通过计算机仿真和模拟振动平台气激实验分析该方法频率估计性能,验证了其在工程实践中的有效性。

恒速下旋转叶片同步振动辨识方法

欠采样极度减少了同步振动信息,为实现恒速下辨识旋转叶片同步振动参数,分析了基于叶尖定时测振原理的同步振动欠采样模型.设计了一种利用多支任意分布的叶尖定时传感器辨识叶片振动参数的方法,从理论上推导了振动倍频遍历算法.将该方法在某型号航空设备上进行模拟验证实验,实验结果表明,该方法可以准确实时地辨识出振动倍频、振动频率、振幅等参数,并还原出叶片同步振动信号,恢复精度约2,μm.成功克服了恒速下叶片同步振动欠采样的辨识难度,进一步完善了叶尖定时测振系统.

基于光纤技术的叶端定时传感器

叶端定时测量是一种新型的在线实时测量叶片振动的有效方法 ,激光光纤叶端定时传感器是整个测试系统设计的关键 .该文研究了叶端定时测量方法 ,并对应用于高速旋转汽轮机叶片振动在线实时监测的光纤叶端定时传感器进行了设计研究和试验 ,研究了一个具有高分辨、大频宽和高信噪比的激光光纤传感器的设计方案 。

间断相位法测量叶片同步振动幅值的研究

叶片发生同步振动时,采集到的振动信息大为减少,给振动的分析带来很大困难。针对该问题,基于非接触式叶尖定时测振原理,采用间断相位法对振动幅值进行分析,并对间断相位法的测量原理进行了推导分析以及计算机仿真,具有重要的理论价值,为同步振动幅值的测量打下理论基础。

旋转叶片振动测量新的技术方案研究

压气机的旋转叶片必须能够承受非常高的静应力和动应力。静态应力可通过测量或理论计算确定 ,静态应力的理论计算与测量结果相当吻合 ;但动态应力主要靠试验测量来确定 ,其理论计算尚未能满足应用的需要。叶片的振动测量因而成为涡轮机械的一个重要研究领域。介绍了旋转叶片传统的测量技术 ,以及近几年来欧美国家正在研究的非接触式旋转叶片振动测量技术———叶端定时测量技术 ,并针对某应用对象进行了测量方案的研究。

双参数法辨识叶片同步振动的研究

基于叶尖定时测振原理,对双传感器测量叶片同步振动的双参数分析方法进行理论推导,建立叶片同步振动分析模型并进行计算机仿真,得出双参数辨识叶片同步振动的具体方法。利用自主开发的叶尖定时测振系统在某型号航空设备上成功完成振动检测试验,采用双参数法对试验数据分析处理,准确辨识出叶片同步共振的幅值、固有频率、倍频等参数,所得结果与理论分析基本一致。

基于LuGre摩擦模型的叶片碰撞摩擦特性研究

建立了基于LuGre摩擦模型的叶片冠间碰撞摩擦模型,研究了叶片冠间接触碰撞和摩擦的动力学特性和减振机理。并研究了冠间间隙、动静摩擦系数对成组自带冠叶片碰撞摩擦减振效果的影响。通过分析摩擦过程中鬃毛的变形,对LuGre模型进行有条件的简化,研究了带冠叶片接触碰撞运动和摩擦运动的分岔特性。研究结果表明,LuGre摩擦模型可以更加完善的描述预滑动阶段叶片冠间的摩擦特性。

涡轮机叶片同步振动参数辨识方法研究(建模仿真)

基于叶尖定时非接触式叶片振动测量技术,提出一种需要较少传感器又能提高测量精度的叶片同步振动参数分析方法。通过低转速到高转速运行过程,测量出叶片振动位移随转频变化之间的关系,根据非线性最小二乘拟合算法获得叶片谐共振点处的中心频率、振动最大幅值、相位、振动恒偏量,但无法获得叶片振动倍频值。对谐共振动点附近处的频率值进行恒速运转,不同位置处的传感器获得不同的振动位移,通过GARIV算法获得各叶片在对应谐共振频率点处的倍频值,结合扫频拟合获得的叶片振动参数可做出叶片坎贝尔图。基于以上的识别方法,提出了叶尖计时传感器的布置方法,并对实际测量中可能存在的干扰因素进行了详细的仿真分析,验证了方法的可行性。该辨识方法的实验验证将在《涡轮机叶片同步振动参数辨识方法研究(实验研究)》一文中给出。