等熵轻质活塞风洞中活塞行程、速度和压力的变化

等熵轻质活塞风洞是一种工作时间很短的风洞，来自高压空器中的气体推动活塞使气体等熵压缩，并在恒定的匹配压力下进入实验段，这对于瞬时热传导技术是合适的，已用于燃气透平叶片的冷却问题的实验研究中，本文对等熵轻质活塞风洞中的一些气动问题做了研究，分析出在不考虑活塞质量时活塞行程、速度与压力的关系式，并进行了实例分析。     

内燃机气缸套失圆对活塞动压润滑和摩擦特性的影响

根据流体动力润滑理论与活塞动力学方程建立了相关分析模型,在考虑内燃机工作过程中实际存在的气缸套失圆变形基础上,分析了活塞的横向运动,考察了活塞裙部的压力场和摩擦特性.结果表明:与不考虑失圆变形时相比,考虑失圆变形时的润滑油膜压力场的峰值降低,裙部流体压力负荷得以缓解;考虑失圆变形后的摩擦力和摩擦功耗增大,失圆程度越大,所产生的摩擦力和摩擦功耗的增量越大.因此,在活塞设计过程中应当重视失圆变形对活塞裙部润滑和摩擦特性的影响.     

自由活塞压缩管ALE方法数值模拟

当前国际上实现高焓气体流动的实验手段之一是自由活塞驱动类脉冲设备,包括自由活塞激波风洞和自由活塞膨胀管.采用自由活塞压缩管作为激波风洞和膨胀管的驱动段时,其驱动能力在很大程度上决定了该类设备的性能.本文采用计算流体力学中任意拉格朗日——欧拉方法(arbitrary Lagrangian Eulerian)数值模拟了压缩管内部的自由活塞运动和气体流动特征.采用移动网格技术来适应活塞运动边界,耦合求解网格运动和气体流动过程,并通过双时间步长方法进行流体运动的时间积分.为了满足几何守恒律(geometric conservation law),对移动网格的法向矢量和表面面积计算进行了修正.不同时刻的活塞位置试验测量结果及欧拉方法预测结果,以及基于简单波理论获得的运动活塞底部气体压力、活塞速度与活塞位置都与当前的ALE方法十分一致.该工作为下一步数值模拟自由活塞激波风洞和自由活塞膨胀管中包括压缩管、激波管和喷管等不同部位的耦合流动提供了基础.      

自由活塞激波风洞

自由活塞激波风洞是一种使用自由活塞压缩器驱动的高焓脉冲型激波风洞。这种风洞是由R J Stalker提出并在澳大利亚国立大学首先建成和逐渐发展起来的高焓实验设备。经过30多年的改进与发展,日趋完善,现已成为研究高超声速气动加热、计及真实气体效应的气体动力学现象、特别是超声速或高超声速燃氢冲压发动机(scamjet)的重要设备之一,受到国际上航空航天界的重视。本文概述了自由活塞激波风洞的发展过程,系统地阐述了这种设备的结构特点和运行原理,给出了性能参数的计算方法和算例,及其性能指标,并讨论了这类风洞的优缺点。      

活塞二阶运动及活塞裙部摩擦的瞬态分析

为分析不同工况下内燃机活塞-缸套系统的摩擦学和动力学行为,本文从内燃机系统动力学分析入手,结合流体润滑方程,建立了考虑系统变惯量影响的活塞二阶运动与摩擦学行为的瞬态分析模型.以某型号单缸机为例,计算和比较了整个启动过程中曲轴转速、二阶运动及摩擦功耗的变化;对比分析了启动时第一周期与稳定运行时某一周期内活塞二阶运动和活塞裙部摩擦学行为的差别.结果表明:该模型可应用于内燃机动力学和摩擦学行为的稳态及瞬态分析.     

缸套-活塞系统润滑行为与动力学行为耦合分析

建立了缸套-活塞系统油膜润滑与动力学行为耦合分析模型，并用数值方法进行了仿真计算，用有限元法计算了缸体的结构动力响应；通过采用有限差分法求解平均雷诺方程计算了缸套和活塞间的流体润滑特性，并探讨了活塞二阶振动的影响；采用顺序耦合的方法计算了考虑缸套-活塞摩擦、润滑与缸体结构振动、活塞二阶振动耦合作用的缸套-活塞间最小油膜厚度变化、摩擦力及摩擦功耗等．同不考虑缸体振动时的相应分析和计算结果对比发现，缸体结构振动对油膜润滑特性具有重要影响．     

考虑活塞回复的侧向后喷武器两相流数值模拟

为研究活塞回复运动对火药燃气流动的影响,基于两相流理论对活塞控制侧向后喷武器的发射过程进行了数值模拟研究。考虑控制侧向后喷通道开闭的活塞-弹簧系统的往复运动,建立了结合膛内气固两相流、活塞腔内流固耦合和侧向排气管内气体瞬态流动的武器发射过程数学模型,并将数值模拟结果与相关文献进行了比较验证。得到了该武器发射过程中膛内流场分布与稀疏波传播特性,并与普通武器的膛内流场进行了对比分析。进一步研究了活塞回复运动对火药燃气流动和减后坐效率的影响。结果表明:相对于不考虑活塞的回复运动,在弹丸初速都降低1.52%的情况下,因为活塞回复关闭后喷通道,其减后坐效率由38.86%下降到32.88%,说明在此类武器研究中,不可忽视活塞回复运动。     

基于当地流活塞理论的气动弹性计算方法研究

发展了一种高效、高精度的超音速、高超音速非定常气动力计算 方法------基于定常CFD技术的当地流活塞理论. 运用当地流活塞理论计算非定常 气动力，耦合结构运动方程，实现超音速、高超音速气动弹性的时域模拟. 运用这 种方法计算了一系列非定常气动力算例和颤振算例，并和原始活塞理论、非定 常Euler方程结果作了比较. 由于局部地使用活塞理论假设，这种方法大大地克服 了原始活塞理论对飞行马赫数、翼型厚度和飞行迎角的 限制. 与非定常Euler方程方法相比，当地流活塞理论的效率很高.     

活塞驱动下颗粒状HMX床的燃烧转爆轰DDT）实验研究

采用盖帽探针、离子探针实验,研究了活塞驱动点燃时ＤＤＴ管中颗粒状ＨＭＸ床的燃烧转爆轰现象。从研究的结果得出,活塞驱动时产生的压缩波引起颗粒状炸药床的 燃烧,燃烧波引起炸药起爆。     

含活塞的管内湍流的数值模拟

应用两方程模式和 SIMPLER 算法对含活塞的管内复杂湍流进行了数值模拟.活塞直径和外管内径之比为0.8,雷诺数为6.05×10~4.数值模拟得到了三个回流区.下游回流的分离-再附长度是活塞直径的1.5倍.间隙段存在流速超越现象,但不存在后台阶流动计算中的核心区现象.文中给出了数值模拟的详细成果.     

高速斜入水和水平入水气炮水箱实验系统

为开展模型高速斜入水和水中高速航行的水流场实验研究,研制了立式和卧式气炮与水箱组合的实验系统。通过快速阀和活塞阀控制气炮激发和驱动状态,一级气炮采用高压空气直接驱动弹托和模型,二级气炮采用高压空气驱动重活塞压缩使集气腔中产生高压气体,再驱动弹托和模型达到预定速度。通过调节水箱和发射管角度,使高速模型斜入水或水平入水。其中,立式可变发射角二级气炮可发射质量1～1000 g的模型至2500 m/s最大速度,卧式一级气炮可发射质量1～100 kg的模型至300 m/s最大速度。和小气室、高燃气压力火药驱动方式相比,新型气炮采用大体积、中低驱动压力气室,高压气体更接近等熵膨胀做功,调节高压气体压力,能较好地满足模型质量和速度的宽范围要求。结合光反射通断法测速、高速摄影和阴影流场显示等测量技术,得到立式气炮压缩管重活塞运动速度、压缩管末端压力时间曲线和模型倾斜与水平入水的流场阴影图像。结果表明:重活塞速度在膜片破裂前和理论计算值符合较好,但破膜后差异较大。立式气炮流场阴影图像反映了模型斜入水产生的空中和水中激波以及在气水界面的反射激波、空泡形成和侧向气水界面的破碎与飞溅等现象。从卧式气炮的模型水平入水阴影图像提取气泡轮廓,清楚地看出尾部气泡气水界面的波动和失稳。和商业计算软件Fluent计算结果相比,空泡上游区域基本重合,但尾流区域强湍流导致两者存在明显差异。和水洞实验相比,气炮水箱实验系统近真实地再现高速入水过程伴随的冲击和动态空化等物理现象和模型尺度效应。     

Free-piston driver optimisation for simulation of high Mach number scramjet flow conditions

The University of Queensland (UQ) is currently developing high Mach number, high total pressure scramjet flow conditions in its X2 and X3 expansion tube facilities. These conditions involve shock-processing a high-density air test gas followed by its unsteady expansion into a low-pressure acceleration tube. This relatively slow shock-processing requires the driver to supply high pressure gas for a significantly greater duration than normally required for superorbital flow conditions. One technique to extend the duration is to operate a tuned free-piston driver. For X2, this involves the use of a very light piston at high speeds so that, following diaphragm rupture, the piston displacement substitutes for vented driver gas, thus maintaining driver pressure much longer. However, this presents challenges in terms of higher piston loading and also safely stopping the piston. This article discusses the tuned driver concept, the design of a very lightweight but highly stressed piston, and details the successful development of a new set of tuned free-piston driver conditions for X2.     

非火药驱动的二级轻气炮的发射参数分

介绍了一台５７ｍｍ口径一级压缩气炮驱动的１０ｍｍ口径二级轻气炮，并分析了这种气炮的特点。对其发射参数和发射效果之间的关系进行了数值计算模拟，计算弹速与实测弹速的差异小于１０％。根据计算模拟结果，分析了活塞质量、活塞驱动气压、泵管初充气压和弹丸释放气压等发射参量同弹速和二级气室的气压气温峰值的关系，评估了１０／５７二级轻气炮的发射能力。     

Numerical study of condensing a small concentration of vapour inside a vertical tube

The purpose of this study is to analyse the combined heat and mass transfer of liquid film condensation from a small steam–air mixtures flowing downward along a vertical tube. Both liquid and gas stream are approached by two coupled laminar boundary layer. An implicit finite difference method is employed to solve the coupled governing equations for liquid film and gas flow together with the interfacial matching conditions. The effects of a wide range of changes of three independent variables (inlet pressure, inlet Reynolds number and wall temperature) on the concentration at exit tube, local Nusselt and Sherwood numbers, film thickness, accumulated condensate rate and temperature are carefully examined. The numerical results indicate that in the case of condensing a small concentration of vapours from a mixture, the resistance to heat and mass transfer by non-condensable gas becomes very intense. The comparisons of average Nusselt number and local condensate heat transfer coefficient with the literature results are in good agreement.     

高焓膨胀管中压缩管最佳长度设计分析

中国空气动力研究与发展中心超高速所即将建成的高焓喷胀管采用自由活塞驱动,为了能够使该设备有效运行试验时间达到最长,需要对设备中的压缩管长度进行优化。针对压缩管中的自由活塞运动,本文通过数值求解单一组分和混合驱动气体条件下的活塞运动准一维常微分控制方程组,分析了不同试验设计参数和不同驱动气体介质对压缩管定压驱动时间的影响。采用数值解结合脊线(局部极值曲线)理论获得了定压驱动时间局部极值曲面,基于压缩管四种摩尔比例驱动气体(100%H2,85%H2+15%N2,100%He,85%He+15%Ar)和三组压缩比(λ=60,100,140)下的极值曲面,研究发现,定压驱动时间脊线高度随着压缩管的有效长度(初始活塞头部到压缩管末端膜片的距离)和内径之比L/D增加而增加。本文研究最终获得了给定参数条件下满足最长定压驱动时间要求的最佳压缩管长度。     

Improvement of a free piston driver for a high-enthalpy shock tunnel

In order to improve the operation of a high-enthalpy free piston shock tunnel its tuned operation was studied analytically and experimentally. First, the piston motion in the free piston driver tube was analytically solved by proposing a simple piston/gasdynamic model, and the tuned operation condition was formulated as an eigenvalue with which the piston has sufficiently high speed at the moment of diaphragm rupture, so as to maintain a constant driver gas pressure, and reduces its speed to come to rest when very closely approaching the end of the driver tube. Second, the result of this analysis was validated by its comparison with experiments which were conducted in the medium-sized free piston shock tunnel HEK installed at the NAL Kakuda Research Center. By observing the detail of piston landing at the end of the driver tube the present tuned operation was found to be successfully achieved with the operating condition given here. Its advantages in improving the pressure recovery factor and in enhancing the stagnation enthalpy were successfully demonstrated. Received 8 June 1997 / Accepted 1 October 1997     

二级轻气炮内弹道的数值模拟与性能分析

为了优化二级轻气炮的设计参数和工作参数,必须进行数值模拟。本文介绍了准一维不定常流的Lagrangian算法,讨论了数值模拟中的若干问题,分析了气动过程。根据我们的数值模拟,归纳了影响气炮性能的一些基本规律,可供选择工作参数时综合分析。     

Nonlinear gas oscillations in a closed tube driven by the aperiodic motion of a piston

Nonlinear gas oscillations in a closed tube driven by the aperiodic motions of a piston as a result of the action of the external and internal pressure drop are studied. The external pressure takes two values alternating at the moment of change of direction of motion of the piston. Two models of the motion of the gas are considered. Model 1 is formed by a system of equations representing the mass, momentum, and entropy conservation laws. As distinct from model 1, model 2 includes the total energy conservation law in place of the entropy conservation laws. Kazan’. Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 2, pp. 134–142, March–April, 1998. The work was carried out with partial support from the Russian Foundation for Fundamental Research (project No. 96-01-00484).     

Model investigations of convective heat transfer and pressure loss in diagonal membrane heating surfaces

 The paper presents the results of an investigation concerning heat transfer and pressure loss in air crossflow of diagonally shaped membrane heating surfaces. The heat and mass transfer analogy by means of naphthalene sublimation technique is used in order to evaluate mean Nusselt number values in such tube banks. The effect of tube bank arrangement on heat transfer coefficients and flow resistance is discussed. Convective heat transfer and pressure loss characteristics of diagonally shaped membrane tube banks, plain tube banks and ordinary membrane tube banks are compared. Received on 15 June 2000 / Published online: 29 November 2001     

The effect of air on solid body impact with water in two dimensions

In this paper we study the motion of wedge and catamaran shaped hulls initially in air, then impacting with water. We consider motion in two dimensions and simulate the impact using SPH in a form suitable for two-phase flow. This SPH algorithm has been tested for a variety of problems involving air and water with very good results. However, we supplement those tests by simulating the dynamics of bubbles, and the motion of piston driven by the pressure of air in a tube. The former confirms that our algorithm simulates the motion of two fluids with a high density ratio (in this case 1000) while the latter is relevant to the impact of a catamaran shaped hull where the trapped air cushions the impact. In both cases the results are in very good agreement with theory. When applied to simulate the dynamics of a wedge falling into a fluid the results are in good agreement with theory and confirm that the effect of the air on the motion is small because the air can escape easily as the wedge enters the water. When applied to simulate a model catamaran hull in two dimensions, where the air is trapped beneath the hull, the effect of air is pronounced. The simulations with the catamaran hull are not in close agreement with experiments because the hull in three dimensions does not trap air effectively as it does in two dimensions.