基于UG的航空发动机涡轮叶片模态分析

基于UG软件对某型航空发动机涡轮叶片的振动特性进行了研究,建立了该叶片的实体模型,并利用UG结构分析模块进行了模态分析,得到了叶片的各阶固有频率和相应的振型.根据计算结果分析了涡轮叶片的振动特性,为该叶片的设计优化和振动安全性检验提供了数值依据.     

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.     

基于激光自混合原理的涡轮叶片转速与叶尖间隙动态同步测量方法

针对在高温等恶劣环境下,航空发动机高转速下涡轮叶尖间隙测量稳定性差、易受干扰、精准度低等问题,提出一种基于激光自混合原理的涡轮叶片转速与叶尖间隙动态同步测量方法。 首先,提出基于三镜 F-P 腔模型的自混合干涉模型,并以此为基础构建测速和测距的数学模型;其次着重研究了涡轮叶片转动下动态自混合干涉信号的处理,将采集到的信号依次经过带通滤波以及小波降噪处理,再用 FFT 进行处理得到频率,由此求得叶尖间隙值;之后分别进行静态和动态激光自混合干涉测距实验进行验证;最后探讨影响动态测量的误差源,并对测量系统以及算法进行优化补偿。 实验结果证明,该方法可以有效地提高涡轮叶片转速与叶尖间隙的同步测量的稳定性及精度,测速相对误差为 1% ,叶尖间隙测量误差为 23 μm。     

A study on an axial-type 2-D turbine blade shape for reducing the blade profile loss

Losses on the turbine consist of the mechanical loss, tip clearance loss, secondary flow loss and blade profile loss etc.,. More than 60 % of total losses on the turbine is generated by the two latter loss mechanisms. These losses are directly related with the reduction of turbine efficiency. In order to provide a new design methodology for reducing losses and increasing turbine efficiency, a two-dimensional axial-type turbine blade shape is modified by the optimization process with two-dimensional compressible flow analysis codes, which are validated by the experimental results on the VKI turbine blade. A turbine blade profile is selected at the mean radius of turbine rotor using on a heavy duty gas turbine, and optimized at the operating condition. Shape parameters, which are employed to change the blade shape, are applied as design variables in the optimization process. Aerodynamic, mechanical and geometric constraints are imposed to ensure that the optimized profile meets all engineering restrict conditions. The objective function is the pitchwise area averaged total pressure at the 30 % axial chord downstream from the trailing edge. 13 design variables are chosen for blade shape modification. A 10.8 % reduction of total pressure loss on the turbine rotor is achieved by this process, which is same as a more than 1 % total-to-total efficiency increase. The computed results are compared with those using 11 design variables, and show that optimized results depend heavily on the accuracy of blade design.     

Analysis of fretting cracking condition for nub of steam turbine blade

Journal of Mechanical Science and Technology - Nub-and-sleeve of last-stage blade for steam turbine is a part-span damper. The nub is susceptible to fretting cracking since the nub is in contact...     

涡轮叶片三维叶尖间隙光纤检测系统

航空发动机涡轮叶片叶尖间隙呈三维变化特点,传统光纤式叶尖间隙检测系统的测量结果受维间耦合影响精度差,信息源单一。本文利用一种沿直角等腰三角排布的三路双圈同轴式光纤传感基元组成的传感探头,通过BP神经网络解耦方法,实现了从传感器输出到叶尖端面径向间隙、轴向倾角和周向倾角三维参量的解耦。设计加工三维测量光纤传感器和后续调理电路并对检测系统进行了静、动态实验验证。实验结果表明:该系统径向间隙静态测量的最大误差为47μm,标准差为10μm,轴向和周向倾角的静态测量最大误差分别为0.49°和2.32°,标准差分别为0.13°和0.36°。系统具有良好的重复性和可靠性,径向间隙的动态测量标准差小于18μm,轴向和周向倾角的动态测量标准差小0.2°和0.5°,能够满足航空发动机涡轮叶片叶尖间隙三维参量快速实时检测的需求。     

Optimization of a high pressure turbine blade tip cavity with conjugate heat transfer analysis

The current study aims to understand the aero-thermal performance of a cooled cavity tip in a single stage transonic turbine. The squealer tip of the uncooled turbine blade was reduced to an aerodynamic loss with suppressing leakage flow. However, the aerodynamic loss study of the cooled turbine blade tip is rare. It is necessary to study the tip cavity of the cooled turbine blade. Depth, front blend radius and aft blend radius of the cavity were set as design variables, and 30 cases were chosen using design of experiments. These cases were calculated with conjugate heat transfer method. Approximation model was made using the Kriging method, and tip cavity shape was optimized with multidisciplinary design optimization. Average total pressure loss behind the trailing edge and cooling effectiveness of blade tip surface were set to the objective function. The aerodynamic optimization model decreased 1.6 % of total pressure loss, the heat transfer optimization model increased 1.3 % point of cooling effectiveness and aero-thermal optimization model were found. Volume of tip cavity becomes larger when three design variables are grown. Amount of tip leakage flow and its distribution over the tip region increases and total pressure loss and cooling effectiveness increase. In terms of heat transfer, blade tip without cavity is advantageous. Total pressure loss coefficient, however, also increases over 5 %. To improve both aero-thermal characteristics of cooled blade tip, the design using the multidisciplinary design optimization is recommended.

     

Effect of blade tip pattern on blade load and vibration characteristics of a twin-stage axial flow fan

Focusing on a twin-stage axial fan, this paper investigates the effect of blade tip pattern on blade load and vibration characteristics. Steady simulations are first conducted to quantify the aerodynamic performance of various blade tip patterns. The finite element modeling analysis is performed to capture blade load and vibration characteristics, and Campbell diagram is introduced to evaluate resonance margin of different blade tip patterns. Results show that for all selected patterns, the first three mode shapes are mainly the bending of blade tip, which results in stress concentration at the blade root, while the last three are the waving in small range. The proposed blade tip patterns not only increase maximum stress and average deformation, but also significantly increase resonance margin near the rated speed. In addition, based on the harmonic response analysis, we find that the stress and amplitude frequency response will be notably altered by blade tip patterns.

     

基于ANSYS的某型航空发动机涡轮叶片的振动特性分析

以某型航空发动机的高压涡轮叶片为研究对象,采用Solidworks软件建立其三维实体模型,基于有限元分析软件ANSYS对其进行振动特性分析,得出叶片的振动频率特性和前六阶振动模态特性。仿真结果对涡轮叶片的设计和改进具有一定的指导意义。     

汽轮机摩擦阻尼叶片振动特性研究

利用摩擦阻尼对汽轮机叶片进行减振是一种简单而又行之有效的方法.文中研究了汽轮机摩擦阻尼器叶片在谐波激励作用下的振动特性.利用平均法求解系统主共振稳态响应方程,分析了系统参数与响应之间的关系.结果表明,系统参数取适当值时,阻尼器会处于最优的摩擦接触状态,获得较好的减振效果.所得结论对工程应用具有一定的指导意义.     

风轮机叶片雷达散射特性计算与解析式拟合

风轮机作为高大的运动障碍物,会对气象雷达的工作性能产生较为严重的影响,研究风轮机的电磁散射特性对于识别风电场干扰、评估其对气象雷达的影响具有重大意义。考虑了圆柱叶片介电常数对其雷达散射截面积(RCS)的影响,利用数值拟合的方法实现了不同材料圆柱叶片RCS仿真和解析式的拟合,并对拟合结果进行了验证;其次,考虑了风轮机叶片翼型对其RCS的影响,运用UG软件对某型号风轮机叶片进行了三维建模,对其回波信号进行微动特征分析,并与实测结果进行了对比,证明了该建模方法的正确性;最后利用数值拟合的方法给出了真实叶片RCS在一定范围内的解析计算公式。     

气冷涡轮叶片气热耦合数值模拟研究

采用气热耦合计算方法进行气冷涡轮气动性能-传热分析,这种方法无需指定对流换热系数和热流密度等经验参数,只须要给出气流与固体之间的流动换热物理条件.利用该方法对某三维涡轮导叶进行数值模拟,计算结果表明,气热耦合计算的叶片温度场更接近真实情况,针对该叶片尾缘烧蚀问题,利用气热耦合计算方法,研究了叶片尾缘冷却设计方案,通过对在尾缘开缝冷却方案的分析计算,结果表明,该设计方案可以使得尾缘最高温度下降了130K.     

Monitoring low cycle fatigue damage in turbine blade using vibration characteristics

A finite element based approach is used to simulate the evolution of low cycle fatigue damage in a turbine blade. The turbine blade is modelled as a rotating Timoshenko beam with taper and twist. A damage growth model for low cycle fatigue damage developed using a continuum mechanics approach is integrated with the finite element model. Numerical results are obtained to study the effect of damage growth on the rotating frequencies. It is found that low cycle fatigue causes sufficient degradation in blade stiffness for changes in rotating frequency to be used as an indicator to track damage growth. Continuum damage mechanics models in conjunction with finite element analysis are used to develop thresholds for damage indicators. By placing suitable threshold on the frequency change, it is possible to detect the onset of the final stage of damage in the structure before failure occurs.     

Identification of turbine blade flutter

Unstable vibrations during turbine flutter are studied. Analysis of strain gage records of blade vibrations and synchronous records of the pressure pulsations in the countercurrent gas flow shows that the damping of vibration modes is the most informative parameter determining flutter evolution. The time dependences of frequency spectra and of damping at these frequencies are determined by the Prony method. The coincidence of the eigenfrequencies of the blades and the synchronous character of the changes in the shape of the time dependences of damping at these frequencies and at the frequencies of the diametric modes of the pressure pulsations in the gas flow guarantee that it is collective vibrations of the blades related to the phenomenon of flutter that occur.     

大型风机叶片气动外形参数计算及三维建模方法

结合工程实践,基于Schmitz理论计算出风机叶片气动外形参数并利用三维坐标变换原理计算截面翼型空间分布位置,在此基础上,以大型三维设计软件UG为工作平台建立了叶片三维气动外形,并完全满足五轴数控加工制造要求,从而验证了该方法的可靠性.这一方法简化了复杂曲面的设计过程,提高了工作效率,为后续的数控加工、模具制作、结构设计及计算奠定了基础.     

Numerical study on characteristics of ship wave according to shape of waterway section

The ship wave phenomena in the restricted waterway were investigated by a numerical analysis. The Euler and continuity equations were employed for the present study. The boundary fitted and moving grid system was adopted to enhance the computational efficiency. The convective terms in the governing equations and the kinematic free surface boundary condition were solved by the Constrained Interpolated Profile (CIP) algorithm in order to solve accurately wave heights in far field as well as near field. The advantage of the CIP method was verified by the comparison of the computed results by the CIP and the Maker and Cell (MAC) method. The free surface flow simulation around Wigley hull was performed and compared with the experiment for the sake of the validation of the numerical method. The present numerical scheme was applied to the free surface simulation for various canal sections in order to understand the effect of the sectional shape of waterways on the ship waves. The wave heights on the side wall and the shape of the wave patterns with their characteristics of flow are discussed. Key Words: Ship Wave, Shallow Water, Waterway, Constrained Interpolated Profile (CIP) Algorithm     

Study of applying reverse engineering to turbine blade manufacture

A turbine blade has complex shaped free-form surfaces that can be modelled as surfaces with variable curvature by high-degree polynomials. Industry typically utilizes a turnkey system and special-purpose machine tool to manufacture turbine blades. A turkey system is a closed form design. Users need only input relevant data to this system to manufacture the product directly. However, users are unaware of the internal operation of the system. With rapidly advances in computing technology, commercial CAD/CAM systems can be utilized to design freeform surfaces and generate a tool path for the designed surfaces. This study uses a reverse engineering technology that is used to reconstruct the CAD model for a turbine blade. The prototype is measured by a coordinate measuring machine to obtain the geometrical control data points that are used to generate the CAD model in the UniGraphics (UG) CAD/CAM system. The UG/GRIP (GRaphics interactive Programming) language is used to generate the cutter location data rather than using the default UG CAM module. A five-axis NC code is acquired by the developed postprocessor and verified by the solid cutting simulation software VERICUT®. Real turbine blade machining is performed on a table/spindle tilting five-axis machine tool, demonstrating the effectiveness of the proposed approach.     

风力发电机叶片动力学研究与分析

根据风机气动相关理论,进行叶素空气动力学特性分析,并给出叶片气动力的计算表达式,采用ANSYS有限元分析软件对风机叶片模型进行振动模态分析,计算了叶片的固有频率、各阶振型图,为避免叶片发生共振、提高叶片使用寿命提供了分析方法。     

涡轮叶片铸件收缩率计算与分析

在航空发动机涡轮叶片的精铸模具设计中,收缩率的赋值是个重要的环节.以实测数据为基础重构测量模型,以截面线的内切圆圆心为收缩中心,研究截面线上每个点在法向的变化,由此来计算点收缩率,分析叶片的收缩率分布情况,得出了叶身收缩率分布非均匀性和非线性的结论.     

汽轮机叶片断裂原因分析研究

针对锅炉软水处理存在的普遍性问题,对汽轮机垢进行了分析;对叶片进行了热力计算分析;对额定工况与堵塞工况的第5级叶片进行了强度核算;对某垃圾电站的汽轮发电机组转子叶片断裂原因进行了分析,认定了其原因在于结垢引起了局部通流面积锐减,转子叶片的受力发生了很大的变化,以导致叶片断裂。研究结果表明,通过采用加强对汽机运行参数监控的方式,可及时发现蒸汽品质的变化,提高锅炉软水处理的能力,能够实现机组长期、经济地运行。