周边切口短圆柱试件的杆杆型冲击拉伸试验系统的弹塑性有限元分析

基于一维试验原理提出了用带有周边切口的短金属圆柱试件进行平面应变型弹塑性动态断裂韧度的测试方法；对该复杂的动力学系统进行了轴对称的弹塑性有限元分析，并计算了动态围道^J积分；根据对试件功能转换关系的分析和Rice公式的物理意义，提出了用试件两端平功载荷－两端相对位移曲线（P^-△）推广Rice公式计算试件的远场J积分，由此得到的P^-△曲线基本上消除了与裂纹运动无关的质心运动动能的影响。论证了J积分作为裂端的表征参量，且当切口深度比大于70％时，Rice公式有较高的计算精度，为平面应变型弹塑性动态断裂韧度的表征与测试提供了依据。     

一种弹塑性材料动态起裂韧度的J表征和测试方法

在数值计算的基础上提出了一个弹塑性材料动态起裂韧度的J表征和测试方法．这一方法利用自行研制的间接杆-杆型冲击拉伸试验装置，对周边切口的短圆柱试件实施基于一维试验原理的弹塑性材料动态断裂试验；利用试件两端的平均载荷—相对位移曲线(P-δ)或平均载荷-裂纹张开位移曲线(P-△)，推广Bice远场公式获得动态J积分；采用柔度变化率法确定裂纹起裂点，从而得到动态起裂韧度JJD．这一方法的优点在于利用P-δ或P-△曲线将外力对试件所做的与裂纹运动无关的质心惯性运动动能近似地从总能量中分离出来，且平均载荷P在起裂前以至失稳扩展前是单调增的，同时试验获得的P-δ和P-△曲线光滑，这使得用J积分作为裂纹尖端的表征参量以及用柔度变化率法确定起裂点和失稳点具有坚实的物理基础．     

受压裂纹周边应力极值线及起裂特征研究

通过理论解析并结合数值模拟试验,研究了裂纹倾角对受压裂纹近周第一主应力场和剪应力场的影响。为了能够反映原生裂纹周边的次生裂纹特征,根据原生裂纹近周应力场提出了可描述裂隙岩体中次生裂纹起始位置、起始方向、发展方向的应力极值线的概念。从理论上对应力极值线进行了定义,并通过典型的数值试验分析了应力极值线随裂纹倾角变化的特征与演变过程,进一步从应力极值线角度描述了受压原生裂纹的次生张性裂纹和次生剪切裂纹的特征。研究结果表明:随裂纹倾角增大第一主应力极值线与原生裂纹相交点从裂纹中部向裂纹端部移动,但剪切应力极值线与裂纹相交点始终位于裂纹端部;第一主应力极值线在与原生裂纹相交处垂直于原生裂纹,但最终方向与压力方向平行;剪应力极值线始终与原生裂纹大致共面。研究结果对认识裂隙岩体试样破坏模式、解释张性次生裂纹和剪切次生裂纹的起裂及发展机理有一定的借鉴意义。     

环形板受弯的弹塑性参数解

已知图1示厚度为h的环形簿板,外周边简支,内周边自由并受集度为M的弯矩作用.当M超过某一极限值之后,环内周边进入塑性,M再增大,内周边出现的塑性区扩展,板呈现部分弹性和部分塑性状态.文献[1]对该问题的塑性极限状态进行过分析,但没有给出弹塑性表达式以及弹塑性分界线与M间关系.本文对这一问题用参数给出了弹塑性内力解答以及     

低频振动波在砂土层中的传播衰减规律研究

压路机高铁路基在建设过程中产生低频振动的振动波，在周边砂土层的传播扰动对周边房屋造成损伤．本文采用DA&P-B01型数据采集分析系统和配套的891-2拾振器，在不同距离处布置测试点进行振动试验，得到各测试点的时程变化曲线并加以分析，运用符合率结合前人研究成果验证本次实验的正确性．结果表明：低频振动波在砂土层中的峰值频率相同，振动速度、加速度、能量同距离的递减曲线为指数函数与幂函数的共同作用，且衰减速率与距离呈递减关系．本试验得到的结论可为同一地质条件的施工以及振动影响范围预测提供理论参考，为日后深入研究奠定基础．     

撞击载荷下数字电子散斑离面位移的测试研究1）

采用瞬态光学图像采集技术，实现了动态数字散斑干涉（ＤＳＰＩ）．以周边固支圆板受法向撞击集中载荷为例，对其离面位移场进行了测试．实验值与动有限元计算结果比较，两者是比较接近的     

外爆条件下冲击波与组合壳结构的相互作用

为研究冲击波与组合壳结构的相互作用，针对带防护墙的地面直立钢筋混凝土组合壳结构，考虑结构安置于地面和周边围土2种工况，开展结构爆炸实验，分析了结构外表面冲击波荷载分布及振动特性。实验结果表明:冲击波作用下，结构外表面爆炸荷载主要产生在冲击波绕射过程，确定荷载时应考虑冲击波压力在绕射传播过程中的自然衰减；整个结构中与冲击波最早接触的构件先产生振动，而后由于结构整体参与使得振动频率降低，振动幅值减小；结构周边围土可降低防护墙迎爆部分构件的振动频率，减小防护墙和组合壳的振动幅值。     

撞击载荷下数字电子散斑离面位移的测试研究1）

采用瞬态光学图像采集技术，实现了动态数字散斑干涉（ＤＳＰＩ）．以周边固支圆板受法向撞击集中载荷为例，对其离面位移场进行了测试．实验值与动有限元计算结果比较，两者是比较接近的     

用阻尼最小二乘法解梯形薄板的大挠度弯曲问题

本文以双重三角级数为试函数，用配点法建立残值方程，并用阻尼最小二乘法求解，研究了分析周边简支可动梯形薄板的几何非线性弯曲问题，并给出两个算例，由计算结果显示，效果良好且工作量较少，本文的计算结果可直接用于工程。     

岩石钻爆开挖中预裂缝的隔震效果分析

通过应力波与由节理刚度系数描述的预裂缝的相互作用分析，考虑预裂缝在爆炸应力波作用下的闭合效应及预裂缝充水等条件下，研究了预裂缝的隔震机制与隔震效果，从而为岩石开挖过程中周边控制爆破方式的优选提供了理论依据。     

基于仿生设计的风力发电机叶片力学性能的实验研究

根据风力机的基本理论和相似理论设计了一个翼型为SG6050,半径为1m的小型风力机叶片。运用结构仿生学原理,对所设计的风力机叶片进行了仿生物中轴铺层设计。通过模态实验与应变实验,比较了传统设计与仿生设计两种不同风力机叶片的力学性能。模态实验结果表明,基于仿生设计的叶片的前六阶固有频率比传统叶片的前六阶固有频率减少约8％;两种叶片的固有频率均满足设计要求;仿生设计的叶片几乎不会改变叶片的动态特性。而应变实验表明,仿生设计的叶片在各种工况下的应变均大于传统的叶片约10％～20％。新设计的叶片具有较好的柔性,有效减小了叶片的应力,提高了叶片的疲劳寿命。     

Investigation of flow separation in a transonic-fan linear cascade using visualization methods

An extensive experimental study into the nature of the separated flows on the blade suction surface of modern transonic fans is described in this paper. The study was a subtask of a larger experimental effort focused on blade flutter excited by flow separation in the blade tip region. The tip sections of airfoils on transonic fan blades are designed for precompression and consequently they differ from sections on the rest of the blade. The blade tip section was modeled by a low aspect ratio blade and therefore most of the blade tested was exposed to the secondary flow effects. The aim of this work was to supply reliable data on flow separation on transonic fan blades for validation of future analytical studies. The experimental study focused on two visualization techniques: surface flow visualization using dye oils and schlieren (and shadowgraph) flow visualization. The following key observations were made during the study. For subsonic inlet flow, the flow on the suction surface of the blade was separated over a large portion of the blade, and the separated area increased with increasing inlet Mach number. For the supersonic inlet flow condition, the flow was attached from the leading edge up to the point where a bow shock from the upper neighboring blade imposed on the blade surface. Downstream, there was a separated flow region in which air flowed in the direction opposite the inlet flow. Finally, past the separated flow region, the flow reattached to the blade surface. For subsonic inlet flow, the low cascade solidity resulted in an increased area of separated flow. For supersonic flow conditions, the low solidity resulted in an improvement in flow over the suction surface.     

A new Navier–Stokes inverse method based on mass‐averaged tangential velocity for blade design

This paper presents a novel viscous inverse method for blade design. In this inverse design method the mass‐averaged tangential velocity and the blade thickness are prescribed, and the corresponding blade profile is sought. The blade profile is then computed iteratively using the discrepancies between the prescribed mass‐averaged tangential velocity distribution and its calculated distribution on an initial blade. The re‐design of an axial rotor blade, starting from an initial arbitrary profile in subsonic flow regimes, demonstrates the merits and robustness of this approach. Copyright © 2008 John Wiley & Sons, Ltd.     

Simulation of the stress-strain state and evaluation of the blade loading capacity in the case of impermeability testing of engine housings

A numerical methodology for determining the stress-strain state and the blade loading capacity is proposed to study the blade failure on the basis of stress redistribution in a given blade cross section due to an additional thermal loading and on the basis of the failure enforcement action on this cross section at a given frequency of rotation. The stress-strain state of the blade is numerically studied when the blade cross section is weakened. The proposed methodology is used to test the impermeability of a gas turbine engine housing using an acceleration stand.     

航空发动机压气机叶片振动频率与温度的关系

以某型航空发动机压气机第六级叶片为例，研究了温度对叶片振动频率的影响。发现由于温度的升高导致了材料弹性模量的下降，而弹性模量的下降又导致了叶片在发动机一定的转速范围内，除一阶振动外，其余各阶振动的动频均小于静频，因此与通常的工程处理方法不同，研究压气机叶片的动频时，应考虑温度的影响。     

Supercritical and subcritical dynamic flow-induced instabilities of a small-scale wind turbine blade placed in uniform flow

There is a growing interest in extracting more power per turbine by increasing the rotor size in offshore wind turbines. As a result, the turbine blades will become longer and therefore more flexible, and a flexible blade is susceptible to flow-induced instabilities. In order to design and build stable large wind turbine blades, the onset of possible flow-induced instabilities should be considered in the design process. Currently, there is a lack of experimental work on flow-induced instabilities of wind turbine blades. In the present study, a series of experiments were conducted and flow-induced instabilities were observed in wind turbine blades. A small-scale flexible blade based on the NREL 5 MW reference wind turbine blade was built using three-dimensional printing technique. The blade was placed in the test section of a wind tunnel and was subjected to uniform oncoming flow, representing the case of a parked wind turbine blade. The blade׳s tip displacement was measured using a non-contacting displacement measurement device as the oncoming wind speed was increased. At a critical wind speed, the blade became unstable and experienced limit cycle oscillations. The amplitude of these oscillations increased with increasing wind speed. Both supercritical and subcritical dynamic instabilities were observed. The instabilities were observed at different angles of attack and for blades both with and without a geometric twist. It was found that the blade twist had a significant influence on the observed instability: a blade without a twist experienced a strong subcritical instability.     

A moderate deflection composite helicopter rotor blade model with an improved cross-sectional analysis

The compatibility between a composite beam cross-sectional analysis based on the variational asymptotic approach, and a helicopter rotor blade model which is part of a comprehensive rotorcraft analysis code is examined. It was found that the finite element cross-sectional analysis code VABS can be combined with a moderate deflection rotor blade model in spite of the differences between the formulations. The new YF/VABS rotor blade model accounts for arbitrary cross-sectional warping, in-plane stresses, and moderate deflections. The YF/VABS composite rotor blade model was validated against experimental data and various rotor blade analyses by examining displacements and stresses under static loads, as well as aeroelastic stability of a composite rotor blade in hover, and forward flight vibratory hubloads of a four bladed composite rotor.     

Performance improvement of small-scale rotors by passive blade twist control

A passive twist control is proposed as an adaptive way to maximize the overall efficiency of the small-scale rotor blade for multifunctional aircrafts. Incorporated into a database of airfoil characteristics, Blade Element Momentum Theory is implemented to obtain the blade optimum twist rates for hover and forward flight. In order to realize the required torsion of blade between hover and forward flight, glass/epoxy laminate blade is proposed based on Centrifugal Force Induced Twist concept. Tip mass is used to improve the nose-down torsion and the stabilization of rotating flexible blade. The laminate blades are tested in hover and forward flight modes, with deformations measured by Laser Displacement Sensor. Two Laser Displacement Sensors are driven by the tracking systems to scan the rotating blade from root to tip. The distance from blade surface to a reference plane can be recorded section by section. Then, a polynomial surface fitting is applied to reconstruct the shape of rotating blade, including the analysis of measurement precision based on the Kline–McClintock method. The results from deformation testings show that nose-down torsion is generated in each flight mode. The data from a Fluid Structure Interaction model agrees well with experimental results at an acceptable level in terms of the trend predictions.     

刮擦线速度对TC4叶片与Ni-G封严涂层磨损行为的影响

利用高速刮擦试验机模拟了压气机叶片与封严涂层的刮擦行为,研究了TC4（钛合金）叶片材料与Ni-G（镍-石墨）封严涂层体系在线速度30~150 m/s范围内的磨损行为.通过对叶片样品端面及涂层样品磨痕的SEM-EDS、XPS分析和涂层样品磨痕表面的显微硬度测试,探讨了对摩体系的磨损机制.结果表明：随着线速度的增大,叶片样品的磨损率呈现先升后降的趋势;在低线速度下涂层样品致密化使叶片样品磨损轻微,中等线速度下叶片样品与涂层样品磨痕中高硬度转移层的刮擦造成叶片样品磨损加剧,高线速度下叶片样品端面较厚氧化膜减轻叶片材料向涂层的转移导致叶片样品磨损下降.     

Bifurcation phenomena of the reversal behavior of an automobile wiper blade

Reducing the noise generated by windshield wipers during reversal is desirable. As a fundamental first step in exploring the cause of this noise, the present study attempts to theoretically and experimentally clarify the dynamics of the behavior of the wiper blade near the reversal point. First, an experiment is conducted to observe the reversal behavior using the cross sectional model of the blade rubber. In order to theoretically explain the experimentally observed phenomena, an analytical link model of the wiper blade is introduced. The reversal behavior of a blade is theoretically investigated through the bifurcation analysis by considering Coulomb??s friction during reversal. Then we show the continuous variation of the angle of blade rubber, and predict a rapid variation of the normal force, which can cause reversal noise, acting to the blade rubber.