水中悬浮隧道锚索在剪切流中的涡激响应

以Iwan改进的尾流振子模型为基础，给出了剪切流中水中悬浮隧道锚索横向涡激振动的工程分析方法，分析了悬浮隧道重浮比以及剪切流特性对锚索涡激响应的影响．计算结果表明，悬浮隧道重浮比的改变，使锚索各阶模态的频锁区域分布发生变化，从而改变了结构的涡激振动响应；剪切流陡度参数的增大会使锚索涡激响应的幅值减小，若使用均匀流场代替剪切流场计算悬浮隧道锚索的涡激振动，会过高估计其响应幅值．

水中悬浮隧道在波浪场中非线性动力响应的研究

针对水中悬浮隧道在波浪力作用下动力响应的问题,通过柔度系数法推导得到了悬浮隧道的等效刚度系数,考虑了不同自由度运动之间的耦合作用,建立了悬浮隧道管段的动力响应模型,在时间域内采用逐步积分法迭代求解其运动控制方程.波浪力采用Airy线性波理论和Morison方程计算.计算结果表明,在波浪力作用下悬浮隧道管段产生较大的横荡位移,且随着波频或锚索中预张力的减小,响应振幅增大.在悬浮隧道的动力响应分析中,若不考虑不同自由度运动之间的耦合作用,会过低估计垂荡响应的幅值.

水中悬浮隧道在冲击载荷作用下的计算模型与数值模拟

建立了水中悬浮隧道在冲击载荷作用下的简化计算模型。用等效质量法将圆柱壳分布质量折算成冲击点处的集中质量,模型中考虑流体附加质量和系统阻尼的影响。根据碰撞过程中的动量守恒、变形过程中的能量守恒以及结构的位移与内力关系,得到问题的解析解。为验证解析解,在ANSYS/LS-DYNA中建立了动态冲击有限元分析模型。通过算例分别考察了在忽略和考虑流体附加质量两种情况下,冲击点位置和冲击速度对冲击点处最大径向位移的影响,将解析解与数值解进行对比,结果吻合较好。然后采用数值模拟方法得到了系统阻尼对计算结果的影响规律。数值模拟过程中还可以得到冲击点处的最大Mises应力。

蜡纸存贮法在高超声速脉冲风洞舵—锥干扰流场显示中的应用

简述了蜡纸存贮法在高超声速脉冲风洞锥—舵干扰流场显示中的应用,给出了迎风面内舵周围干扰区立体和平面展开两种油流谱图,揭示了其三维干扰流动的特征。

土的卸载试验和在万家寨引水隧洞变形分析中的应用

万家寨引黄工程隧洞总干线~#7隧洞位于偏关县葛家山至水泉河间，总长约9.21km，其中土洞长2.685km，隧洞开挖直径6.012m，衬砌内径5.46m，衬砌厚0.25m，每环由4块六角形管片组成，管片与洞壁间用豆砾石灌浆回填。~#7隧洞部分穿过地质年代为第四纪（Q3）黄土，其颗粒组成和物理性质指标见表1，2。土名为黄土状粉土。为分析计算隧洞和管片在周围土体作用下，及在通水和放空情况下的应力和变形情况，对~#7土洞进行有限元分析。在确定的c,#phi#值时，分别取原状土进行了卸载、加载试验，并计算出邓肯－张模型中的k,n,R_f,G,F,D进行比较。文中还对用两种试验获得的模型参数进行有限元变形分析的结果进行比较。

扫描式总压耙在高超声速推进风洞流场测量中的应用

在风洞实验中,为了保证实验结果的可靠性,首先需要了解流场的品质.笔者自行设计研制了用于高超声速推进风洞流场测量的带有水冷装置的可移动式扫描总压耙.对于出口截面为300mm×187mm的风洞喷管,通过计算机程序控制,可在3s时间内实现全截面间歇式或连续式扫描,最大移动速度可达250mm/s,而且定位准确.通过扫描结果,分析了流场压力均匀性、稳定性以及实验结果的可重复性,同时还给出了风洞喷管出口截面的总压与马赫数等值线图.从而为超燃冲压模型发动机实验提供参考数据.

Oscillatory Flow Induced Hydrodynamic Forces upon a Pipeline near Erosive Sandy Seabed

An experimental study of the properties of hydrodynamic forces upon a marine pipeline is presented in this paper, in the equilibrium scour conditions for various Keulegan-Carpenter numbers and various initial relative gaps between pipeline and the erosive sandy seabed. The tests are conducted in a U-shaped oscillatory water tunnel with a sand box located at the bottom of the test section. According to the experimental results, the maximum horizontal forces on the pipelines with an initial gap to seabed will decrease to some extent due to scouring process. For engineering appliances, it seems safer to estimate wave induced forces on pipelines under the assumption that seabed is plane. However, it should be noticed that great changes would be brought to the frequency properties of lift forces because of the sandy scour beneath the pipeline, which occurs for certain KC numbers.

Direct initiation of detonation with ignition tube

Experiments of direct initiation of hydrogen-oxygen by means of a hot turbulent jet were made. Results indicate that the length of ignition tube is the dominant factor in determining the ignition capability of hot turbulent jet, and that the ignition capability of turbulence jet increases with the length of ignition tube. Because this ignition capability can meet the demands of a gas-detonation-driver shock tunnel and it doesn't require additional facilities, the hot turbulent jet initiation method can be applied to large hydrogen-oxygen detonation-driver shock tunnels. Influences of obstacles on the ignition capability were also studied. It was found that the presence of obstacles weakens the ignition capability of a hot turbulent jet.

Research progress on high-enthalpy and hypersonic flows

The research progress on high-enthalpy and hypersorlic flows having been achieved in the Institute of Mechanics, Chinese Academy of Sciences, is reported in this paper. The paper consists of three main parts: The first part is on the techniques to develop advanced hypersonic test facilities, in which the detonation-driven shock-reflected tunnel and the detonation-driven shock-expanded tube are introduced. The shock tunnel can be used for generating hypersonic flows of a Mach number ranging from 10 to 20, and the expansion tube is applicable to simulate the flows with a speed of 7 similar to 10km/s. The second part is dedicated to the shock tunnel nozzle flow diagnosis to examine properties of the hypersonic flows thus created. The third part is on experiments and numerical simulations. The experiments include measuring the aerodynamic pitching moment and heat transfer in hypersonic flows, and the numerical work reports nozzle flow simulations and flow non-equilibrium effects on the possible experiments that may be carried out on the above-mentioned hypersonic test facilities.

高频感应等离子体风洞的流场研究

高频感应等离子体风洞适合于基础研究特别是用于防热材料的催化特性的研究，本文用实验测量和数值模拟了该风洞的温度场和速度场。温度场是用OSA （Optical Spectrum Analyzer）进行光谱分析得到的，同时用水冷总压和静压探针对风洞的流场进行测量得到了速度场的空间分布。数值模拟采用完全二维的高频感应等离子模型，我们通过求解相关的能量方程、流体动力学方程和电磁场方程得到了相应的温度场和流场。比较了数值模拟结果与实现测量结果，并给出了不同运行参数下的典型数值结果。

Experimental Demonstration Of A New Concept Of Drag Reduction And Thermal Protection For Hypersonic Vehicles

A new idea of drag reduction and thermal protection for hypersonic vehicles is proposed based on the combination of a physical spike and lateral jets for shock-reconstruction. The spike recasts the bow shock in front of a blunt body into a conical shock, and the lateral jets work to protect the spike tip from overheating and to push the conical shock away from the blunt body when a pitching angle exists during flight. Experiments are conducted in a hypersonic wind tunnel at a nominal Mach number of 6. It is demonstrated that the shock/shock interaction on the blunt body is avoided due to injection and the peak pressure at the reattachment point is reduced by 70% under a 4A degrees attack angle.

Development And Application Of Flexible Substrate Sensors In Instantaneous Heat Flux Measurement

A new type of sensor with the flexible substrate is introduced. It is applicable in measuring instantaneous heat flux on the model surface in a hypersonic shock tunnel. The working principle, structure and manufacture process of the sensor are presented. The substrate thickness and the dynamic response parameter of the sensor are calculated. Because this sensor was successfully used in measuring the instantaneous heat flux on the surface of a flat plate in a detonation-driven shock tunnel, it may be effective in measuring instantaneous heat flux on the model surface.

Experimental Study Of Multi-Hole Cooling For Integrally-Woven, Ceramic Matrix Composite Walls For Gas Turbine Applications

In this paper, multi-hole cooling is studied for an oxide/oxide ceramic specimen with normal injection holes and for a SiC/SiC ceramic specimen with oblique injection holes. A special purpose heat transfer tunnel was designed and built, which can provide a wide range of Reynolds numbers (10(5)similar to 10(7)) and a large temperature ratio of the primary flow to the coolant (up to 2.5). Cooling effectiveness determined by the measured surface temperature for the two types of ceramic specimens is investigated. It is found that the multi-hole cooling system for both specimens has a high cooling efficiency and it is higher for the SiC/SiC specimen than for the oxide/oxide specimen. Effects on the cooling effectiveness of parameters including blowing ratio, Reynolds number and temperature ratio, are studied. In addition, profiles of the mean velocity and temperature above the cooling surface are measured to provide further understanding of the cooling process. Duplication of the key parameters for multi-hole cooling, for a representative combustor flow condition (without radiation effects), is achieved with parameter scaling and the results show the high efficiency of multi-hole cooling for the oblique hole, SiC/SiC specimen. (C) 2008 Elsevier Ltd. All rights reserved.

高焓激波风洞自由流参数测量的数值重建

高焓风洞中参数测量本身受到高温非平衡效应影响,单纯依靠实验测量不足以确定详细的风洞自由流参数.本文以JF-10高焓激波风洞为背景,通过喷管-试验段-测量仪模型非平衡流场的连贯计算,开展自由流参数测量的数值重建.在比较分析测量仪模型绕流场的计算结果和实验测量值的基础上,结合喷管流场的数值模拟结果,共同确定高焓风洞的详细自由流参数.

Aerodynamic characteristics research on wide-speed range waverider configuration

Waverider generated from a given flow field has a high lift-to-drag ratio because of attached bow shock on leading edge. However, leading edge blunt and off-design condition can make bow shock off leading edge and have unfavorable influence on aerodynamic characteristics. So these two problems have always been concerned as important engineering science issues by aeronautical engineering scientists. In this paper, through respectively using low speed and high speed waverider design principles, a wide-speed rang vehicle is designed, which can level takeoff and accelerate to hypersonic speed for cruise. In addition, sharp leading edge is blunted to alleviated aeroheating. Theoretical study and wind tunnel test show that this vehicle has good aerodynamic performance in wide-speed range of subsonic, transonic, supersonic and hypersonic speeds.