Experimental-numerical investigation of the dynamic stability of flexural-torsional vibrations of compressor blades under conditions of attached and separated flow. Part 1. Procedure and equipment for the determination of nonstationary aerodynamic characteristics

We present the results of investigations of the aerodynamic stability of flexural-torsional vibrations of compressor blades under conditions of attached and separated flow with regard for the cross and mutual aerodynamic links of the blades in a broad range of variations of the phase shift, the ratio of the amplitudes of translational and angular components of their displacements, and the angle of attack. A procedure and equipment used for the experimental determination of the nonstationary aerodynamic characteristics of the blades are described on the basis of the model of flat-plate airfoil cascades. __________ Translated from Problemy Prochnosti, No. 2, pp. 129–142, March–April, 2007.     

Effect of attack angle on the nonstationary aerodynamic characteristics and flutter resistance of a grid of bent vibrating compressor blades

The angle of attack is studied by experiment for its effect on grid resistance to flutter for a plane compressor grid which includes four translationally vibrating blades. It is established that large critical angles of attack corresponding to stalled flow of blades increase sharply the probability of the occurrence of flutter both for individual blades and for the grid as a whole. It is shown that the reason for this phenomenon is a drop in aerodynamic damping of blades with single vibrations and a marked increase in their mutual aerodynamic effect.Translated from Problemy Prochnosti, No. 10, pp. 78–81, October, 1993.     

Experimental-numerical investigation of the dynamic stability of flexural-torsional vibrations of compressor blades under conditions of attached and separated flow. Part 2. Cross aerodynamic characteristics

We consider the results of investigation of cross aerodynamic characteristics of compressor blades and their dynamic stability under flexural-torsional vibrations for the cases of attached and separated flows in broad ranges of variations of the phase shift, the ratio of amplitudes of the translational and angular components of displacements, the angle of attack, the reduced frequency of vibrations, and the geometry of the blade cascade. Translated from Problemy Prochnosti, No. 4, pp. 89–100, July–August, 2009.     

考虑风速分布的叶片MPC气弹控制

作为叶片失效的重要原因,颤振一直是风电领域研究重点。以抑制叶片工作过程中的颤振为目的,建立分析模型时应充分考虑实际风速分布特别是风切变和塔影效应对叶片振动的影响,并在离散化后求取平均输入风速。针对小型风力机叶片气动弹性稳定性问题进行综合分析,根据实体结构建立叶片气弹模型,考虑非线性气动力作用时叶片大攻角、大风速工况下产生的高频、高幅失速颤振,模拟典型截面仿真振动位移。通过模型预测控制的滚动优化和误差矫正控制叶片挥舞、摆振两个运动方向的振动频率和幅值,结果表明振动形式实现控制后可在短时间内达到稳定且静差可接受。     

Optimization design of axial fan blade

A series airfoil was obtained through optimization design which aimed to promote lift–drag ratio, and the new airfoil series was used to construct a blade. The chord length and installation angle of the blade along the blade height were optimized by using orthogonal optimization. Three design options (straight blades, C-type blades and forward swept blades) are examined in this paper. Taking an axial fan as the research object, the whole 3D numerical simulation was conducted by using Ansys-CFX. Axial fans with three kinds of blades are discussed and compared under design and off-design conditions. The present results show that: under design conditions, the total pressure efficiency of the axial flow fan with the forward swept blade is the highest, and the C-type blade has slightly lower efficiency while the straight blade has the lowest efficiency. Under off-design conditions, the aerodynamic performance of the forward-swept blade and C-type blade fans are better than that of the straight-blade fans.     

Swept blade influence on aerodynamic performance of steam turbine nozzle cascades

To improve the aerodynamic performance of steam turbine nozzle cascades, it is significant to study the effect of swept blades to control the flow field within the cascade. Numerical simulations of three different sweep angle blades (?20°, +20° and 0°) were carried out, using CFD modelling. Simulation results showed that the aft-swept blade can effectively improve the corresponding flow characteristics and reduce the total pressure loss. Meanwhile, it has better aerodynamic performance than the straight blade and the fore-swept blade.     

叶片厚度对旋涡风机叶片噪声的影响分析

利用三维CFD模型对旋涡风机内部流场进行模拟分析,获得叶片表面的压力脉动信息,以叶片表面压力流场作为气动声源,通过求解FW-H方程,计算了叶片产生的远场气动噪声;并以叶片表面的压力脉动信号作为激励源,计算了叶片振动产生的噪声。计算结果表明叶片厚度在1 mm到4 mm的范围,其气动噪声基本保持不变,结构噪声随叶片厚度减小而大幅增加,进一步分析得出叶片产生的噪声以气动噪声为主,结构噪声基本可以忽略。     

风力机复合材料柔性叶片的颤振分析

将风力机叶片简化为薄壁复合材料封闭截面弯扭耦合变形梁,基于Hamilton原理并结合变分渐进法（VAM）,建立风力机叶片的气动弹性力学模型。结构模型包括材料各向异性,截面翘曲,离心载荷,科里奥利加速度,以及预锥角和预扭转角的影响。气动载荷采用叶素动量理论和准定常气动力理论进行描述。将位移按广义坐标进行模态展开,采用Galerkin法导出系统的质量、刚度和阻尼矩阵,采用特征值技术进行叶片颤振性能的数值求解。针对周向反对称刚度配置（CAS）叶片进行数值近似计算,揭示了入流比、预扭转角和纤维铺层角等参数对风力机叶片颤振性能的影响。     

风力机叶片挥舞摆振气弹失稳分析

为避免风机叶片在强风作用下发生破坏,需对其采取停机保护措施。该文研究叶片处于非旋转状态时的挥舞摆振气弹失稳现象发生的条件。基于风力机叶片简化模型,采用迭代法求解叶片的自振频率及振型,建立了非旋转叶片挥舞摆振气弹效应响应的振型叠加法,该方法可以便捷地进行叶片多工况气动弹性响应分析。计算了在不同风速不同攻角条件下叶片的挥舞摆振气弹效应响应,得到了叶片挥舞摆振响应随风速和风攻角的变化规律以及不稳定风攻角的分布特征。结果表明:在某些风攻角下,风机叶片挥舞摆振失稳现象在风速较低的情况就有可能发生,其响应幅值与结构阻尼联系紧密。另外,挥舞摆振失稳会大大增加作用于叶片上的风荷载,并进一步造成叶片结构的损伤破坏。     

风力机运行过程中气动载荷变化工程分析

为提高风力发电机组设计可靠性,需得到风力机在实际运行过程中叶片气动载荷的计算方法.从工程角度出发,对风力发电机使用的NACA专用翼型进行分析,结合薄翼理论推导出攻角变化特点,并依据风切变理论和塔影效应得到风力机实际运行时叶片在各个位置点的气动载荷.依据实际情况对风轮受力平面进行工程简化,得到风力机叶片气动载荷的计算方法.将此方法计算出的气动载荷与试验测量结果进行比对,吻合度较好.     

Modeling Smart Structure of Wind Turbine Blade

With the increasing size of wind turbine blades, the need for more sophisticated load control techniques has induced the interest for aerodynamic control systems with build-in intelligence on the blades. The paper aims to provide a way for modeling the adaptive wind turbine blades and analyze its ability for vibration suppress. It consists of the modeling of the adaptive wind turbine blades with the wire of piezoelectric material embedded in blade matrix, and smart sandwich structure of wind turbine blade. By using this model, an active vibration method which effectively suppresses the vibrations of the smart blade is designed.     

Aerodynamic design and analysis of a 10 kW horizontal-axis wind turbine for Tainan,Taiwan

The purpose of the present study is to develop a small-scale horizontal-axis wind turbine (HAWT) suitable for the local wind conditions of Tainan, Taiwan. The wind energy potential was first determined through the Weibull wind speed distribution and then was adapted to the design of the turbine blade. Two numerical approaches were adopted in the design and analysis of the HAWT turbine blades. The blade element momentum theory (BEMT) was used to lay out the shape of the turbine blades (S822 and S823 airfoils). The geometry of the root region of the turbine blade was then modified to facilitate integration with a pitch control system. A mathematical model for the prediction of aerodynamic performance of the S822 and S823 airfoils, in which the lift and drag coefficients are calculated using BEMT equations, was then developed. Finally, computational fluid dynamics (CFD) was used to examine the aerodynamic characteristics of the resulting turbine blades. The resulting aerodynamic performance curves obtained from CFD simulation are in agreement with those obtained using BEMT. It is also observed that separation flow occurred at the turbine blade root at the tip speed ratios of 5 and 7.     

Influence of the shape of the blade tip on the emitted noise in the air-gap between the rotor and the housing of an axial fan

The paper presents influence of the rotor blade tip shape of an axial fan on the emitted noise and on its aerodynamic characteristic. Appropriate measurements were first performed on the integral level of the same rotor with the two blade tip shapes: blade tip configuration A where the blade tip has the form of the prolonged basic blade, and configuration B with the winglet where the tip was slightly pushed towards the suction side of the blade. Moreover results of local pressure and sound pressure measurements in the area of the air gap made possible detailed analysis of the avarage pressure distribution and its time variance. The results showed strong dependence of the blade tip design on the emitted noise distribution, whereas changes of the aerodynamic characteristic with both tip designs were hardly noticed. The correlation between the emitted sound power level of the fan and the air pressure variance enabled to locate mechanism and origin of the noise generation in the zone between two consecutive rotor blades.     

后缘小翼智能旋翼减振效果影响因素分析

建立了带后缘小翼智能旋翼气动弹性载荷计算模型及减振优化分析方法。模型考虑刚体后缘小翼的气动力与惯性力对弹性桨叶系统的影响,使用粘性涡粒子法结合翼型查表法计算旋翼气动载荷,采用力积分法计算桨叶与桨毂载荷,构造了包含桨叶根部扭转及桨毂振动载荷为目标函数的优化问题,基于最速下降-黄金分割组合优化算法寻找最佳小翼偏转规律。研究发现,建立的后缘小翼载荷控制方法有效,可降低振动目标函数70%。桨叶的弹性扭转使后缘小翼能有效实施减振,但弹性扭转对小翼气动力矩的放大作用使减振时通常伴随着桨叶扭转载荷增大的现象。     

Analytic extraction of the elastic coupling mechanisms in composite blades

An aeroelastic model for a hingeless helicopter blade with a composite flex-beam is presented. The model employs structural analysis for laminated flex-beams of solid cross-sections with symmetric layup, and the study encompasses configurations with Beamwise Bending-Twist coupling and Chordwise Bending-Twist coupling. The structural dynamics of blades with coupled composite flex-beams is studied by a special purpose methodology that allows the creation of a refined uncoupled reference blade for each case. This procedure enables the determination of the net effects which are induced by the elastic couplings. By examining the stability characteristics of the blades in the frequency domain and their response in the time domain, the paper supplies additional information regarding the trade-off between stability and vibration characteristics in both the transient and the steady-state, forward-flight regimes. The analysis also examines the effect of different types of composite materials and quantitatively identifies the relation between elastic properties and their potential to improve blade stability margins.     

A numerical study of incompressible Navier-Stokes flow through rectilinear and radial cascade of turbine blades

A numerical study is conducted to analyse the two-dimensional incompressible Navier-Stokes flows through the rectilinear and radial cascade of turbine blades. The flows are turbulent and their characteristics are relevant to those of the hydraulic turbines. For the rectilinear cascade, calculations have been made for a NACA 80 series turbine blade with various angles of attack. The outflow turning angle, force coefficients and static pressure distribution have been compared between the prediction and measurement with satisfactory agreements being obtained. The implications of flow turning angles on the total pressure loss are also discussed. The effects of grid distribution on the numerical predictions are also observed.     

风力机翼型在复合运动下的动态失速数值分析

现代大型风力机在工作时叶片经历大变形与振动,将会对其周围的动态流场产生影响,从而导致气动力的改变。因此有必要深入研究风力机翼型在复合运动情况下的动态失速气动特性,以正确预测大型风力机运行时的载荷。该文应用计算流体力学方法,对S809翼型在不同运动形式下的动态失速特性进行了二维数值分析。首先对翼型在作俯仰运动下的轻失速和深失速情况分别结合S-A、SST k-ω和RSM三种湍流模型进行了动态失速数值模拟,结果表明S-A、SST k-ω和RSM三种湍流模型都能有效地计算出翼型的气动力。然后采用SST k-ω模型仿真了翼型在挥舞运动、俯仰摆振耦合运动下的动态失速气动特性,并与相同工况条件下翼型作俯仰运动时的气动特性进行了对比分析。发现翼型在挥舞运动下的动态失速虽然弱于俯仰运动,但其强度不容忽视;而翼型在作俯仰与摆振耦合运动时比单纯作俯仰运动时的失速程度更深。因此在风力机设计阶段为获得保守的气动载荷预测,有必要将叶片截面在挥舞与摆振方向的运动转换成等效攻角,叠加在主攻角上进行动态失速气动力计算。     

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.     

Response surface approach to aerodynamic optimization design of helicopter rotor blade

This paper describes a hovering rotor blade design through the suitable combination of flow analysis and optimization technique. It includes a parametric study concerned with the influence of design variables and different design conditions such as objective functions and constraints on the rotor performance. Navier–Stokes analysis is employed to compute the hovering rotor performance in subsonic and transonic operating conditions. Response surface method based on D‐optimal 3‐level factorial design and genetic algorithm are applied to obtain the optimum solution of a defined objective function including the penalty terms of constraints. The designs of the rotor airfoil geometry and the rotor tip shape are performed in subsonic and transonic conditions, and it is observed that the new rotor blades optimized by various objective functions and constraints have better aerodynamic characteristics than the baseline rotor blade. The influence of design variables and their mutual interactions on the rotor performance is also examined through the optimization process. Copyright © 2005 John Wiley & Sons, Ltd.     

跨音轴流风扇叶片气弹稳定性研究

基于弱耦合的能量法原理,对近失速工况下NASA 67跨音风扇叶片进行了气弹稳定性分析。本文发展的三维线性插值方法为CSD/CFD数据交换提供了基础。采用FLUENT动网格技术,实现了振动叶片绕流计算。数值模拟了NASA 67叶片前三阶模态振型激励下的非定常气动响应。通过分析叶片表面非定常气动力和振动位移之间的相位差发现：该相位差的存在决定了非定常气动力做功的正、负。由叶片表面非定常压力分析结果得出近失速工况下,叶片的气动弹性稳定性受叶片模态振型和激波的影响较为显著。