基区无吹氦环柱型高超音速低温喷管流场分析

设计了小基区、基区不吹He的环柱型高能化学激光器环形HYLTE喷管 阵列,并使用数值模拟的方法对环形HYLTE喷管阵列流场的气动性能和光学性能进行了分 析. 结果表明,该设计有利于形成ν= 1 →ν = 0之间振转跃迁谱线,不利 于ν = 2→ν =1之间振转跃迁谱线的形成,由于光腔区绝大多数的HF(2)分 子碰撞去激活后成为HF(1)分子,从而使1P谱线的小信号增益倍增,无基 区吹He的设计有利于提高高能化学激光 器的效率. 采用小基区的设计可以增大喷管阵列的功率流密度,无基区吹He的设计不但可 以使复杂的环形高超音速低温喷管叶片的加工与装配得到简化,而且降低了激光器工作 气体的消耗. 因此该设计不但有利于实现高能激光器的紧凑化设计,还有利于节省高能 激光器建造和运行的成本.     

一种紧凑型快前沿Marx发生器的设计

介绍用电感器作为充电和接地器件的10级、300kV、纳秒上升时间气体绝缘Marx发生器的结构设计及电场分析。设计的中心引出触发极环形场畸变开关可以实现发生器建立。为了减少建立时间,设计了与主电极一体的对地增容电极。采用电容器并联同轴结构降低树立电感。为进一步加快前沿,设计了水介质锐化电容。模拟结果表明,发生器可以输出上升前沿为5ns,电压为300kV的脉冲。     

风沙两相流跃移层中沙粒相的速度分布

从单个跃移沙粒在气流中的运动方程出发导出了风沙两相流中沙粒相速度分布函数的Boltzmann方程，对风沙流研究中几种不同的分布函数及其相应的统计平均值等基本概念给出了严密的数学定义，指出了不同分布函数之间的区别和联系，在略去铅垂方向空气阻力的情况下，给出了沙粒相速度分布函数沿铅垂方向的边缘分布，作为风沙流中跃移理论的主要基础之一。利用结果对前人在风沙流研究中发现的某些重要规律和现象进行了解释。     

喷水推进双级轴流泵流体动力性能CFD分析

采用高质量结构化网格对某喷水推进双级轴流泵整个数值模拟系统的各部件进行区域离散,利用CFD方法预报该泵扬程、功率和效率等外特性,分析其内部流动情况。计算结果与实验数据的较好吻合证明了CFD方法可以作为通过试验求取喷水推进双级轴流泵特性曲线的辅助方法。研究中对有、无轴情况下双级轴流泵外特性的预报和比较结果表明,轴对该泵动力性能预报结果影响不大;通过计算叶片压力分布,验证了该双级泵叶轮叶片设计中采用的线型;通过观察一、二级导叶出口的流动状态,分析了该泵设计中存在的缺陷,并为导叶改进设计提出建议。     

非保守圆薄板的轴对称振动和稳定性

建立了受切向均布随从力作用的圆薄板在面内周边可移、不可移两种情况下的轴对称控制方程，用打靶法直接导出求解变系数常微分方程特征值问题数值解的计算式．通过数值计算，给出了周边可移、不可移的简支、固支圆板自振频率和临界载荷的特征曲线以及相应的临界发散载荷，并分析了泊松比对圆板自振频率和临界载荷的影响．     

纳米压痕残余应力场拉曼光谱实验研究

本文采用纳米压入仪在晶向为〈111〉和〈100〉的两种单晶硅片表面压入1000nm,卸载后得到深度约为550~570nm的压痕。使用共聚焦显微拉曼光谱仪对压痕周边区域进行测量,采用场扫描成像技术得到了压痕周边拉曼频移、半高宽、峰强等拉曼信息,通过分析由频移求得残余应力场的分布。在实验的基础上讨论了残余应力场的分布,以及晶向对应力场分布的影响,近似给出了压痕边缘最大压应力与微裂纹尖端最大拉应力。对其他拉曼信息的分析表明,半高宽和峰强信息与材料晶格结构的变化相关,在一定程度上也可以反映残余应力的作用。     

基于原子体积场拉普拉斯算子对金属玻璃剪切转变区的预测

剪切转变区(shear transformation zone, STZ)作为金属玻璃塑性事件的一个基本特征单元,已被研究者们逐渐接受,但STZ产生的机制和来源仍具争议.本文采用分子模拟方法对Cu64Zr36金属玻璃在受简单剪切加载时的变形行为展开了研究.结果表明,体系的初始构型与加载后STZ的产生是相关的.虽然原子体积场及其梯度可以用来有效表征金属玻璃中局部原子构型的非均匀性,但它们与STZ产生的区域没有直接明显的对应关系.基于此,提出一个新的局域结构参数ξ来用于金属玻璃中STZ产生区域的预测,它由两部分构成:原子体积场的拉普拉斯算子和体积场梯度分量的绝对差值.原子体积场的拉普拉斯算子为负且绝对值较大时,体积场梯度向量呈现向内指的分布特征,代表体系中的局域软区;而体积场梯度分量的绝对差值则用于遴选体积场梯度不同的分布模式.进一步地,建立了该结构参数与非仿射位移和剪切局部化三者关系,发现特定的体积场梯度向量分布模式,将导致局部剪切增强的非仿射位移场,从而更容易诱发STZ的形成.相关性分析表明,该参数与STZ区域平均相关性高于78%,因此,该参数能有效用于金属玻璃剪切转变区的预测,且运用拉普拉斯算子的思想有望应用于金属玻璃力学行为的理论分析.     

基于数字粒子图像的细水雾全场速度测量

水文通过利用激光片光照明细水雾喷雾场和采用数字成像系统获取了喷雾粒子的运动轨迹图像，进而通过研制相应的图像处理和分析软件，重建了细水雾雾场粒子的速度分布，本方法是直接对流场中的粒子成像。因而测量时无需施加示踪粒子对数字成像系统的图像获取速度要求不高，且在图像数据的分析处理方面不像DPIV技术的互相关算法，对示踪粒子的数密度有一定的限制，因此，本方法可用于不宜添加示踪粒子或流场中粒子数密度较低的喷雾场或其它两相流场中粒子速度场的测量。     

基于原子体积场拉普拉斯算子对金属玻璃剪切转变区的预测

剪切转变区(shear transformation zone, STZ)作为金属玻璃塑性事件的一个基本特征单元,已被研究者们逐渐接受,但STZ产生的机制和来源仍具争议.本文采用分子模拟方法对Cu64Zr36金属玻璃在受简单剪切加载时的变形行为展开了研究.结果表明,体系的初始构型与加载后STZ的产生是相关的.虽然原子体积场及其梯度可以用来有效表征金属玻璃中局部原子构型的非均匀性,但它们与STZ产生的区域没有直接明显的对应关系.基于此,提出一个新的局域结构参数ξ来用于金属玻璃中STZ产生区域的预测,它由两部分构成:原子体积场的拉普拉斯算子和体积场梯度分量的绝对差值.原子体积场的拉普拉斯算子为负且绝对值较大时,体积场梯度向量呈现向内指的分布特征,代表体系中的局域软区;而体积场梯度分量的绝对差值则用于遴选体积场梯度不同的分布模式.进一步地,建立了该结构参数与非仿射位移和剪切局部化三者关系,发现特定的体积场梯度向量分布模式,将导致局部剪切增强的非仿射位移场,从而更容易诱发STZ的形成.相关性分析表明,该参数与STZ区域平均相关性高于78%,因此,该参数能有效用于金属玻璃剪切转变区的预测,且运用...     

连续体结构的拓扑与形状集成优化算法

以连续体结构的拓扑与形状优化设计技术作为研究对象,将拓扑优化、形状优化、有限元分析和计算机辅助设计有机地集成在一起,构建了优化设计模型;研究了用B样条曲线曲面逼近拓扑优化后的结构体边界,进行边界光滑处理;在形状优化中,设计变量定义为B样条曲线或曲面的控制顶点的运动,建立了边界节点移动速度场计算方法和边界形状调整方法及模型更新理论,有效地控制节点的运动,给出了相应的算法和计算表达式,寻求较快的搜索方向,以合理速度分布尽快使形状变为最佳。设计实例的结果表明了本文所建立的模型的合理性和方法的有效性。     

A Digital Particle Image Velocimetry Study on Jets Issuing from Hybrid Inclined Nozzles

Digital particle image velocimetry was used to study hybrid inclined nozzles formed by combining flat- and inclined-sections, where the latter are designed based on the aspect-ratios (AR = 2 and 4) of half-ellipses. Results show that AR2 nozzle exhibits flow behaviour largely similar to inclined nozzles with inclined vortex roll-ups moving away from the nozzle centerline. In contrast, AR4 nozzle leads to significantly more intense near-field flow behaviour caused by the sharper junctions, which prevent similar movement of the vortex roll-ups. Streamwise vortices are also observed to form off the peaks of inclined-sections which produce wider jets-spreads along the inclined-sections due to associated lateral jet fluid ejection, though there is a limit to the jet-spread increment. Lastly, both nozzles produce higher turbulent stress levels over those of the conventional circular nozzle, and vortex roll-up vectoring leads to higher turbulent stresses for the AR2 nozzle along certain measurement planes.     

喷管对水下爆轰气泡形态和压力特征影响的实验研究

针对具有不同类型喷管的爆轰管在水下爆轰中形成的燃气射流问题,搭建了爆轰实验平台,研究了单次爆轰过程中尾部喷管对水下气泡形态与压力特征的影响。采用数字粒子图像测速技术对高速摄影机拍摄得到的气泡脉动图片进行流场可视化分析,得到各喷管工况下的气泡速度场。为了确认爆轰管内是否形成稳定爆轰波,并观察爆轰波在气液两相界面上的透反射特性,爆轰管尾部安装有2个动态压力传感器,同时在距离喷管一定距离处设置一个水下爆炸传感器,以监测水中传播的压力波。结果表明：扩张喷管工况下的气泡脉动过程与直喷管工况基本一致,但扩张喷管提高了燃气射流速度,气泡膨胀体积更大;因为燃气射流的持续性,收敛喷管工况下的气泡脉动过程具有明显差异,气泡膨胀体积较小,但气泡二次脉动时长相较于一次脉动时长衰减更小;扩张喷管提高了气泡脉动强度,扩张喷管工况下的气泡脉动压力与透射冲击波压力远大于直喷管工况下的气泡脉动压力与透射冲击波压力;收敛喷管工况下的气泡脉动压力与透射冲击波压力都较小,但收敛喷管燃气射流的持续性减缓了气泡脉动压力的衰减速度。相比于直喷管,扩张喷管工况下的气泡脉动时间、气泡脉动压力与透射冲击波压力都更大。收敛喷管工况下的气泡...     

Profiling the Supersonic Part of a Plug Nozzle with a Nonuniform Transonic Flow

The effect of transonic flow nonuniformity on the profiling of optimal plug nozzles is studied in the inviscid gas approximation. Sonic and supersonic regions providing maximum thrust for given nozzle dimensions and a given outer pressure are designed for given subsonic contours and calculated nonuniform transonic flows. As in the case of uniform flow on a cylindrical sonic surface, the initial regions of the designed contours satisfy the condition that in these regions the flow Mach number is unity or near-unity. In all the examples calculated, the optimal plug nozzles produce a greater thrust than the optimal axisymmetric and annular nozzles with a near-axial flow for the same lengths and the same gas flow rates through the nozzle. It is established that contouring without regard for transonic flow nonuniformity can result in considerable thrust losses. However, these losses are due only to a decrease in the flow rate, while the specific thrust may even increase slightly.     

Determination of specific thrust in unchoked regimes and design of a separationless convergent nozzle contour

The variation of the specific thrust R_Y on the angle of inclination of the wall is analyzed within the framework of the ideal gas model using the results of specific impulse and flow rate calculations for conical convergent nozzles. It is shown that in unchoked regimes nozzles with different have almost the same values of R_Y for both subcritical and supercritical pressure ratios _c. On the interval _C < 6 typical of convergent nozzles conical convergent nozzles with =30–90° have almost the same value of the specific thrust, maximal relative to the R_Y of nozzles with < 30°. In the presence of viscosity forces local boundary layer separation may occur in the neighborhood of the entrance section of the convergent nozzle. A method of constructing a separationless convergent nozzle contour with enhanced thrust is developed on the basis of a boundary layer separation criterion. The separationless contour is determined for given values of the flow rate, specific heat ratio, Reynolds number, wall temperature and initial boundary layer displacement thickness.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 158–164, January–February, 1990.     

不同当量比下喷管对旋转爆震特性的影响研究

为研究不同当量比下喷管构型对旋转爆震特性的影响,以煤油预燃裂解气为燃料,氧气体积分数为30%的富氧空气为氧化剂,开展了无喷管、收敛喷管、扩张喷管和收敛扩张喷管等工况下旋转爆震特性实验研究。实验发现,当量比为0.73～1.30时旋转爆震可稳定工作。随着当量比和喷管构型的变化,爆震波出现了单波、不稳定的对撞双波和稳定的对撞双波等3种传播模态。喷管构型对模态转换和旋转爆震波速有重要影响,收敛和收敛扩张喷管会促使新波头的产生,导致爆震波主要以双波对撞模态传播;而扩张喷管工况下,爆震波主要以单波模态传播。收敛喷管和收敛扩张喷管会使得波速最大值偏离化学恰当比,收敛扩张喷管可以提升爆震波速。     

Thrust shock vector control of an axisymmetric conical supersonic nozzle via secondary transverse gas injection

Transverse secondary gas injection into the supersonic flow of an axisymmetric convergent–divergent nozzle is investigated to describe the effects of the fluidic thrust vectoring within the framework of a small satellite launcher. Cold-flow dry-air experiments are performed in a supersonic wind tunnel using two identical supersonic conical nozzles with the different transverse injection port positions. The complex three-dimensional flow field generated by the supersonic cross-flows in these test nozzles was examined. Valuable experimental data were confronted and compared with the results obtained from the numerical simulations. Different nozzle models are numerically simulated under experimental conditions and then further investigated to determine which parameters significantly affect thrust vectoring. Effects which characterize the nozzle and thrust vectoring performances are established. The results indicate that with moderate secondary to primary mass flow rate ratios, ranging around 5 %, it is possible to achieve pertinent vector side forces. It is also revealed that injector positioning and geometry have a strong effect on the shock vector control system and nozzle performances.     

压力容器斜接管区域应力状态的实验研究

压力容器接管区域应力场的获得是压力容器强度分析和结构设计的基础。本文采用实验研究的方法,对压力容器斜接管区域的应力状态进行分析研究。根据实验研究的目的,按照工程设计标准设计、制造了一台大型带有两个斜接管压力容器的实验模型,进行了实验方案设计,采用电测法进行了容器斜接管区域的应力测试,在实验数据科学、合理处理的基础上,获得了容器斜接管区域的应力状态和分布规律。实验研究结果表明,容器斜接管锐角侧、钝角侧和相贯线最低点都存在着较大的局部应力,且锐角侧的局部应力数值最大,但是相贯线上的局部应力影响范围较小。     

LES and RANS modelling of under-expanded jets with application to gaseous fuel direct injection for advanced propulsion systems

A density-based solver with the classical fourth-order accurate Runge-Kutta temporal discretization scheme was developed and applied to study under-expanded jets issued through millimetre-size nozzles for applications in high-pressure direct-injection (DI) gaseous-fuelled propulsion systems. Both large eddy simulation (LES) and Reynolds-averaged Navier-Stokes (RANS) turbulence modelling techniques were used to evaluate the performance of the new code. The computational results were compared both quantitatively and qualitatively against available data from the literature. After initial evaluation of the code, the computational framework was used in conjunction with RANS modelling (k-ω SST) to investigate the effect of nozzle exit geometry on the characteristics of gaseous jets issued from millimetre-size nozzles. Cylindrical nozzles with various length to diameter ratios, namely 5, 10 and 20, in addition to a diverging conical nozzle, were studied. This study is believed to be the first to provide a direct comparison between RANS and LES within the context of nozzle exit profiling for advanced high-pressure injection systems with the formation of under-expanded jets. It was found that reducing the length of the straight section of the nozzle by 50% resulted in a slightly higher level of under-expansion (∼2.6% higher pressure at the nozzle exit) and ∼1% higher mass flow rate. It was also found that a nozzle with 50% shorter length resulted in ∼6% longer jet penetration length. At a constant nozzle pressure ratio (NPR), a lower nozzle length to diameter ratio resulted in a noticeably higher jet penetration. It was found that with a diverging conical nozzle, a fairly higher penetration length could be achieved if an under-expanded jet formed downstream of the nozzle exit compared to a jet issued from a straight nozzle with the same NPR. This was attributed to the radial restriction of the flow and consequently formation of a relatively smaller reflected shock angle. With the conical nozzle used in this study and a 30 bar injection pressure, an under-expanded hydrogen jet exhibited ∼60% higher penetration length compared to an under-expanded nitrogen jet at 100 μs after start of injection. Moreover, the former jet exhibited ∼22% higher penetration compared to a nitrogen jet issued through the conical profile with 150 bar injection pressure.     

Effect of Gas Non-Ideality on the Performance of Laval Nozzles with an Abrupt Constriction

The flows in Laval nozzles with a ero-length region of abrupt constriction and in nozzles with smooth entrance regions are studied on the basis of the Reynolds equations supplemented by a differential turbulence model. It is established that the viscosity effect does not lead to flow separation in the vicinity of the minimum section of optimal nozzles with an abrupt constriction. In all the examples calculated, the thrust of these nozzles is greater than that of nozzles with smooth a constriction and an optimally contoured supersonic part, the flow rate through the nozzle being larger when viscosity is taken into account than in the ideal (inviscid) case.