考虑叶尖间隙变化影响的高速旋转叶片监测技术研究

叶尖定时技术因其非接触性、全面监测性及低成本等众多突出优点使其成为当前高速旋转叶片在线监测领域中的研究热点,但传统基于电涡流传感器的叶尖定时测试中未考虑因叶尖间隙变化引起的叶片振动幅值测量误差,导致系统测量精度不足,测量结果中存在误差较大。针对该问题通过对叶尖间隙变化及脉冲响应的关系进行了实验研究,并在此基础上提出了一种提高基于电涡流传感器的叶尖定时系统测量精度的信号处理方法,通过耦合脉冲信号上升沿时刻与脉冲响应幅值来提高系统的测量精度。最后通过高速风机叶片进行了实验验证。结果表明,该方法在叶尖间隙波动的情况下可以保持较好的叶片振动测量精度。     

电涡流式汽轮机自锁叶片叶尖间隙测量研究

针对汽轮机自锁叶片叶尖间隙的测量要求,提出一种改进的叶尖间隙测量方法,设计了一种适用于汽轮机工作环境的电涡流传感器及其信号处理方法。当自锁叶片旋转时,其围带及锁紧处会交替经过电涡流传感器探头,产生电压信号,通过检测电压信号,应用相应信号处理方法进行处理以获取叶尖间隙。在高速动平衡室使用某型汽轮机末级长叶片进行实验对方法进行验证,实验结果表明所述改进的叶尖间隙测量方法在汽轮机自锁叶片的叶尖间隙测量中是可行的,可测量转速达到3 000 r/min,整圈叶片个数达60个的自锁叶片叶尖间隙。     

高分辨率转子叶尖间隙测量传感器的设计及验证

航空发动机旋转机械的叶尖间隙对其性能和安全具有重要意义。为了通过主动间隙控制系统准确控制涡轮叶尖间隙,需要通过高分辨率的测量传感器实现叶尖间隙的精确测量。由于电涡流式非接触测量方法具有良好的抗干扰性、响应速度和灵敏度等优点,基于电涡流感应原理,设计一种适用于微小间隙动态测量的高分辨率传感器。通过静态标定分析和动态测量实验,验证设计传感器的性能,结果表明设计的传感器分辨率可达10μm,量程可达3 mm,满量程范围测量重复性在0.5%以内。同时,用该方法测量了转子在12 000~15 000 r/min下的叶片长度变化。研究结果表明设计的电涡流传感器的分辨率能够反映间隙动态变化情况且具有良好的动态响应,验证了其在转子叶尖动态间隙测量中应用的可行性。     

基于高频响电涡流传感器的汽轮机带冠叶片振动测量技术（英文）

针对汽轮机带冠叶片的健康监测需求,提出了一种基于高频响电涡流传感器的带冠叶片振动参数测量方法。转子旋转时,电涡流传感器感知叶冠面积变化,通过检测叶片发生振动时叶冠面积变化信号的到达时间,并应用叶尖定时(Blade tip timging, BTT)数据分析方法获取叶片振动参数。设计了一种适用于汽轮机工作环境的电涡流传感器和一种高带宽调幅解调电路,使响应带宽达到250 kHz以上。某型汽轮机末级叶片振动试验结果表明所设计的高频响电涡流传感器和变面积型叶尖定时测振技术在汽轮机带冠叶片的应用是可行的。     

用电涡流传感器测量轮辋尺寸的方法及误差分析

通过应用电涡流传感器扫描测量轮辋尺寸的试验 ,及时对不同的测量区段进行标定 ,确定各个测量区段的标定函数 ,测量轮辋尺寸 ,最后进行了测量误差分析     

电涡流传感器的特性分析与标定方法

结合电涡流传感器的原理,分析了采用电涡流传感器测量位移时传感器特性与被测体尺寸的关系,研究了不同被测材料对电涡流传感器灵敏度的影响,提出了电涡流传感器的标定方法。     

电涡流传感器探头线圈的参数化设计与制造

探头线圈是电涡流传感器的最核心的部件,其设计参数对电涡流传感器的性能有直接影响。建立电涡流传感器探头线圈的等效模型,根据理论推导和ANSYS参数化建模仿真,分析探头线圈的设计参数对电涡流传感器线性度、灵敏度和测量范围的影响。根据所确定的设计参数,利用印刷电路板制造工艺,制作PCB板探头线圈,并测试了基于PCB板探头线圈的电涡流传感器的静态和动态性能。结果表明,PCB板探头线圈制造工艺成熟稳定,一致性很高,质量容易保证,基于PCB板探头线圈的电涡流传感器可以满足实际应用的需要。     

三维叶尖间隙光纤探头设计及输出特性研究

对航空发动机叶片三维叶尖间隙的动态检测可以间接拾取到叶片动态应变参数,获取更全面的叶片健康监测信息。双圈同轴光纤束由于其优良的抗电磁干扰、抗高温特性可以作为发动机叶片三维叶尖间隙动态检测的传感单元。依据双圈同轴光纤束三维位移输出特性模型,建立了3个双圈同轴光纤束基元组成结构的探头输出特性模型,分析了基元拓扑结构、基元间距、光源参数对探头耦合效应的影响,提出了航空发动机叶片三维叶尖间隙光纤测量探头的设计方案,并通过加工出的探头成品实验研究对检测探头输出特性模型进行了验证。     

电涡流传感器动态响应特性研究

为了提高磁悬浮轴承高频电主轴控制系统中电涡流传感器的动态响应特性,针对恒频调幅式电涡流位移振动传感器,分析了电涡流传感器的基本结构和工作原理,建立了电涡流传感器检测电路数学模型,分析了电涡流传感器动态响应特性与检测线圈谐振回路品质因数 Ｑ 的关系,提出了对电涡流传感器动态响应特性在不影响灵敏度和线性测量范围的情况下进行线性校正的方法,从而使电涡流传感器幅频响应带宽提高一倍甚至几倍以上,相位角的滞后量也可以大大减小,充分满足了对磁悬浮轴承高速转子进行位移和振动的非接触性监测的需要。     

基于有限元分析的涡流传感器性能研究

电涡流传感器探头是涡流检测系统的关键部件,其检测灵敏度影响系统的性能。运用COMSOL Multiphysics软件构建了圆柱差分型、单正交矩形柱型和双正交矩形柱型传感器模型。通过有限元仿真与试验验证分析了传感器的检测性能。进一步研究分析了传感器在裂纹宽度、长度和深度上的检测性能,分析比较了3种传感器的检测灵敏度,确定了在以裂纹为检测对象的电涡流传感器探头中采用双正交矩形柱型结构更合理。基于仿真结果优化设计了具有更高检测灵敏度的双正交矩形柱型传感器。     

Numerical study on flow characteristics at blade passage and tip clearance in a linear cascade of high performance turbine blade

A numerical analysis has been conducted in order to simulate the characteristics of complex flow through linear cascades of high performance turbine blade with/without tip clearance by using a pressure-correction based, generalized 3D incompressible Navier-Stokes CFD code. The development and generation of horseshoe vortex, passage vortex, leakage vortex, tip vortex within tip clearance, etc. are clearly identified through the present simulation which uses the RNG k-ε turbulent model with wall function method and a second-order linear upwind scheme for convective terms. The present simulation results are consistent with the generally known tendency that occurs in the blade passage and tip clearance. A 3D model for secondary and leakage flows through turbine cascades with/without tip clearance is also suggested from the present simulation results, including the effects of tip clearance height.     

Influence of tip clearance on pressure fluctuations in an axial flow pump

Rotor-stator interaction in axial pumps can produce pressure fluctuations and further vibrations even damage to the pump system in some extreme case. In this paper, the influence of tip clearance on pressure fluctuations in an axial flow water pump has been investigated by numerical method. Three-dimensional unsteady flow in the axial flow water pump has been simulated with different tip clearances between the impeller blade tip and the casing wall. In addition to monitoring pressure fluctuations at some typical points, a new method based on pressure statistics was proposed to determine pressure fluctuations at all grid nodes inside the whole pump. The comparison shows that the existence of impeller tip clearance magnifies the pressure fluctuations in the impeller region, from the hub to shroud. However, the effect on pressure fluctuation in the diffuser region is not evident. Furthermore, the tip clearance vortex has also been examined under different tip clearances.     

发动机地面起动时涡轮叶尖间隙动态变化规律

基于涡轮叶尖间隙主动控制的需要,本文分析了涡轮叶尖间隙的变化机理,建立了机匣、叶片和转子的简化模型,同时基于某型发动机试车数据计算了涡轮叶尖间隙,研究了发动机地面起动时涡轮叶尖间隙动态变化规律。结果表明:地面起动时涡轮叶尖间隙呈减小趋势,机匣形变量上升速率最大,叶片变化量对叶尖间隙变化影响最小,可为发动机地面起动时涡轮叶尖间隙控制策略的设计提供参考。     

不同流量系数下叶顶间隙对离心压缩机模型级性能的影响

通过CFD技术,分析了不同流量系数下叶顶间隙对离心压缩机模型级性能的影响。结果表明,对于中、小流量系数模型级,叶顶间隙越大,其效率曲线下降越大,而对于大流量系数模型级,有一定的叶顶间隙可改善叶轮内流场,反而有利于离心压缩机效率性能。无论何种流量系数模型级,存在一定的叶顶间隙则可提升能头曲线。     

A model to study the reduction of turbine blade vibration using the snubbing mechanism

Blade vibration reduction is an important task in high performance turbo machinery for power generation, in order to avoid the risk of blade failure due to the overcoming of fatigue limit. A possible way to obtain this result is a contact related phenomenon, i.e. by physically limiting the vibration amplitude on the blade tip leaving a small gap between the shrouds of adjacent blades. When the relative displacement between adjacent blades exceeds the gap, in a certain vibration mode of the blade row, a contact occurs between the shrouds, the relative motion is restricted and energy is dissipated by friction and impact during the contact. This is called the snubbing mechanism.In this paper, an original simplified model of bladed disks, in which the snubbing mechanism can occur, is presented and numerical integration in time domain furnishes the time histories of the vibrations of the blades. The level of vibration reduction is then evaluated in some different modes that could be excited for instance by the fluid flow. It is also shown that unlucky combinations of system and excitation parameters can effect also a certain magnification instead of a reduction of the vibration amplitudes.Experimental results on single blade and blade groups of a steam turbine are used to tune the parameters of the system.     

飞行试验中的发动机叶尖间隙测量方法

对飞行试验中的航空发动机叶尖间隙测量方法进行探讨,分析了实际飞行中影响发动机叶尖间隙的因素,在此基础上对叶尖间隙测量的试飞方法进行了探讨。     

对旋轴流风机叶顶间隙对其气动噪声的影响

为探究改变叶顶间隙对矿用对旋式轴流风机气动噪声的影响，建立不同叶顶间隙的风机三维模型，并结合风机性能试验验证模型的正确性。利用Fluent对风机进行定常模拟、非定常模拟和噪声预估，分析了声功率级和声压级随叶顶间隙的变化情况。结果表明：叶根与轮毂交界处、叶顶间隙处和相邻两叶片中间部位的声功率级随间隙的增加而增大，且叶顶处吸力面声功率级高于压力面。不同间隙下风机的A级声压值总体上呈先急剧下降后上升再逐渐下降的趋势，间隙变大后，风机在各监测点处的A级声压值随之增大。与高频处相比，间隙对中低频处的A级声压值影响更加显著。     

增强稀疏分解及其在叶片振动参数识别中的应用

叶端定时是发动机叶片监测有效手段,相比于传统的应变片测量方式,叶端定时不仅可以同时监测所有叶片的振动状态,而且不会对叶片本身的振动造成影响。但是叶端定时采样数据存在高度欠采样的特点,针对该问题,提出基于增强稀疏分解(Enhancing sparse decomposition,ESD)的叶片振动参数辨识技术。稀疏分解是一种在冗余字典中对信号进行分解,通过求解优化问题得到信号在冗余字典下最稀疏解的信号处理方法。增强稀疏分解相比于传统的基追踪算法,可以得到更为稀疏的解。在建立了增强稀疏优化模型后采用原对偶内点法对优化问题进行求解,从而实现信号特征参数的有效辨识。将提出的基于增强稀疏分解的叶片振动参数辨识技术应用于不同类型的仿真数据和转子叶片试验台参数辨识,并与传统的MUSIC算法和最小二乘拟合相对比,提出的算法可以有效避免频谱混叠和泄露现象,并滤除其他频率成分的干扰,得到更清晰的谱图。     

汽轮机再热后级内颗粒冲蚀特性

汽轮机再热后级内叶片受到固体颗粒冲蚀,严重影响着汽轮机的安全经济运行。以某超临界汽轮机再热后第1+1/2级(第一级与相邻级的喷嘴)扭叶片为研究对象,通过拉格朗日法模拟不同粒径颗粒三维运动轨迹,并采用Finnie冲蚀模型,研究不同动静轴向间隙及不同负荷下颗粒对叶片的冲蚀特性。结果表明,由于动叶高速旋转,颗粒撞击到动叶时会获得与主流方向相反的速度,进而又反弹回静叶。较大粒径颗粒在动静叶片轴向间隙内"反复反弹"是造成再热后级内冲蚀的主要原因。适当增大动静轴向间隙可以有效地减少反弹回静叶的颗粒数量。当动静轴向间隙为5 mm时,反弹回静叶的颗粒为10%,轴向间隙增大为8 mm时,没有颗粒反弹回静叶。当机组负荷降低时,固体颗粒撞击叶片后的反弹角增大、反弹回静叶的数量增多,颗粒在动叶和下级静叶轴向间隙内反弹后,只有极少颗粒能够流出下级静叶。     

Study on unsteady tip leakage vortex cavitation in an axial-flow pump using an improved filter-based model

The aim of the present investigation is to simulate and analyze the tip leakage flow structure and instantaneous evolution of tip vortex cavitation in a scaled axial-flow pump model. The improved filter-based turbulence model based on the density correction and a homogeneous cavitation model were used for implementing this work. The results show that when entering into the tip clearance, the backward flow separates from the blade tip near the pressure side, resulting in the generation of a corner vortex with high magnitude of turbulence kinetic energy. Then, at the exit of the tip clearance, the leakage jets would re-attach on the blade tip wall. Moreover, the maximum swirling strength method was employed in identifying the TLV core and a counter-rotating induced vortex near the end-wall successfully. The three-dimensional cavitation patterns and in-plain cavitation structures obtained by the improved numerical method agree well with the experimental results. At the sheet cavitation trailing edge in the tip region, the perpendicular cavitation cloud induced by TLV sheds and migrates toward the pressure side of the neighboring blade. During its migration, it breaks down abruptly and generates a large number of small-scale cavities, leading to severe degradation of the pump performance, which is similar with the phenomenon observed by Tan et al. [35].