大型水平爆轰管中悬浮铝粉爆炸过程的实验研究

铝粉的燃烧与爆轰性能是粉尘爆炸领域研究的热点.利用长29.6m,内径199mm,配有40套喷粉扬尘系统的水平爆轰管,在40J电火花点火条件下,实现了悬浮铝粉-空气混和物火焰加速、爆燃、爆轰及其转捩过程,测得了爆炸波传播过程中的压力信号,并且观察到了爆轰波的稳定传播现象.实验结果表明,当铝粉浓度为300 g/m3时,在距离点火端10.15m(长径比L/D=51)处发生了DDT,测得的爆轰波传播过程中管内的最大爆速为1840m/s,最大峰值超压为10.5MPa.铝粉尘爆炸波在爆轰管内的传播过程可分为爆燃段、爆燃转爆轰(DDT)、爆轰增强以及稳态爆轰四个阶段.     

颗粒状HMX、RDX的燃烧转爆轰实验研究

用盖帽探针和离子探针实验研究了颗粒状炸药的燃烧转爆轰（以下简称DDT）过程。测试得到了DDT过程的压缩波，燃烧波，冲击波等。研究表明炸药的DDT过程复杂，点火方式，DDT管材料，炸药中的杂质等对炸药的DDT有一定的影响。     

爆轰波透射孔栅形成的高速爆燃波的结构和行为

以实验为主,研究光滑直管中乙炔氧气爆轰波透射孔栅形成的高速爆燃波结构和行为。实验以基于纹影平台的高速转鼓摄影记录孔栅下游近场内初始爆燃波的结构和发展,并以压力传感器跟踪其后继走向。研究发现,高速爆燃波是前驱激波和火焰的组合结构,随着初始压力的提升,它分别表现为紧随于前驱激波的层流和湍流燃烧火焰。入射爆轰胞格尺度小于或与孔栅扰动尺度相当时,湍流燃烧在下游近场迅速形成;层流结构的爆燃波通常无法抵制背景稀疏波而走向衰弱,而湍流燃烧结构可发生加速和向爆轰的转捩;他们之间存在一个不稳定的临界状态,高速爆燃波得以以0.5~0.6倍CJ爆轰速度传播较长距离,这一状态对应于双间断Rankine-Hugoniot关系的等容燃烧解。     

管道内全阻塞障碍物对气相爆轰波传播特性的影响

建立了长2 800 mm、内径为50 mm的圆管内爆轰波传播实验装置,采用光电二极管探测火焰锋面以获得爆轰波的传播速度,采用烟迹法记录爆轰波的胞格结构。通过在管道不同位置设置阻塞率为1的聚丙烯薄膜,研究不同初始压力下不同氩气稀释浓度的C₂H₂+2.5O₂+nAr预混气体爆轰波在通过全阻塞障碍物前后传播速度及胞格结构的变化。结果表明,气相爆轰波在达到稳态爆轰后,在通过全阻塞薄膜障碍物的过程中会产生2种不同的传播形式:速度亏损和爆轰失效。气相爆轰波穿过不同区域的传播过程可以分为3个阶段:稳态传播阶段、速度亏损阶段或爆轰失效阶段、过驱爆轰阶段。     

气相爆轰物理的若干研究进展

爆轰现象的研究已经有一百多年的历史了,爆轰物理的研究取得了许多重要进展.本文从爆轰波的经典理论、胞格爆轰波的多波结构、气相爆轰波形成机理、气相爆轰波传播机制等方面综述了相关的若干研究进展,评述了这些进展的科学性与局限性,并探讨了将来可能的研究方向.这些研究进展主要包括:CJ(Chapman-Jouguet)理论和ZND(Zel'dovich,von Neumann,D?ring)模型、爆轰波多波结构、爆轰胞格特征、直接起爆和爆燃转爆轰过程、热点起爆机制、爆轰波稳定性、扰动爆轰波的传播等.爆轰波是以超声速传播的自持燃烧现象,涉及了激波相互作用、燃烧化学反应、湍流扩散和流动不稳定性等复杂的气动物理过程,相关研究具有重要的学科理论意义.另外,爆轰燃烧具有高效的热化学能释放特点,在先进的热力推进技术方面有着重要的应用背景,因此相关研究也具有重要的工程应用价值.      

激波诱导火焰失稳与爆轰的条件研究

采用九阶WENO和十阶中心差分格式数值求解激波与火焰作用过程,考察了激波强度、火焰尺寸对激波与球形火焰作用过程的影响。结果表明,增大激波强度或火焰尺寸均可在流场中引发爆轰,但激波强度的影响更大,并且其引发的爆轰可使火焰迅速膨胀,放热率提高,从而影响燃烧特性;此外,爆轰波传播过程中会迅速消耗可燃预混气,合并原有的反射激波,并在流场中形成局部高压区,极大地改变流场结构。     

探索发展激波风洞爆轰驱动技术

发现了燃烧驱动激波管中入射激波马赫数异常升高的起因. 实验显示爆轰驱动能力强于燃烧驱动, 从而推动爆轰驱动技术的发展. 采用卸爆管消除爆轰波反射高压以及双爆轰驱动段全部消除爆轰波后的Taylor稀疏波, 使反向和前向爆轰驱动模式具有实用价值. 反向爆轰驱动技术还成功用来延长激波风洞试验时间.      

不同角度分叉管道内氢气-空气爆轰传播特性

在3种角度分叉管道内开展化学计量比氢气-空气爆轰实验,采用自制的火焰传感器和烟迹法分别获得了爆轰波传播速度和胞格结构,探究了不同角度管道分叉对爆轰传播的影响。结果表明:氢气-空气爆轰在经过分叉三通时受分叉口稀疏波影响导致爆轰波衰减解耦,但随着入射激波与下游管道壁面碰撞,逐渐由规则反射向马赫反射转变,最终完成重起爆过程。其中,直通支管内爆轰衰减主要受支管入口面积的影响,随着分叉角度增大,入口面积减小,爆轰衰减程度和重起爆距离也随之减小;而分叉支管内,爆轰衰减受支管入口面积与入口渐扩程度共同影响,但随着分叉角度的增大,入口面积变为主要影响因素。不同角度分叉管内的实验结果均表明,初始压力升高能显著提高爆轰稳定性,从而削弱分叉几何结构的影响。     

斜爆轰发动机的推力性能理论分析

爆轰燃烧具有释热快、循环热效率高的特点. 斜爆轰发动机利用斜爆轰波进行燃烧组织, 在高超声速吸气式推进系统中具有重要地位. 以往研究主要关注斜爆轰波的起爆、驻定以及波系结构等, 缺少从整体层面出发对斜爆轰发动机开展推力性能分析. 本文将斜爆轰发动机内的流动和燃烧过程分解成进气压缩、燃料掺混、燃烧释热和排气膨胀4个基本模块并分别进行理论求解, 建立了斜爆轰发动机推力性能的理论分析模型. 在斜爆轰波系研究成果的基础上, 选取了过驱动斜爆轰、Chapman?Jouguet斜爆轰、过驱动正爆轰和斜激波诱导等容燃烧等4种燃烧模式来描述燃烧室内的燃烧释热过程, 并对比分析了不同燃烧模式对发动机比冲性能的影响. 此外, 还获得了不同来流参数、燃烧室参数和进排气参数等对发动机推力的影响规律, 发现来流马赫数和尾喷管的膨胀面积比是发动机理论燃料比冲的主要影响因素. 最后, 结合以往关于受限空间内斜爆轰波驻定特性等方面的研究成果, 提出了斜爆轰发动机燃烧室的设计方向.      

气体爆轰波在声学吸收壁下游的再加强过程

实验研究了爆轰波在声学吸收段下游发生的再恢复过程。利用声学吸收段首先将一个稳定的爆轰波衰减,于是产生一个非稳定爆轰波,速度降为 45% ~60?J。该非稳定爆轰波传出声学吸收段后再次加强,并在距声学吸收段出口端一定距离处突然发展成超驱动爆轰。实验利用烟迹技术捕捉了爆轰波从发生衰减到再次加强的全过程,获得了爆轰波再加强距离随初压变化的实验规律。由此,本文建立了再加强段内加速传播火焰的理论模型,称为激波 -爆燃波复合态,并解释了火焰加速和超驱动爆轰形成的机理。     

Combined effects of vortex flow and the Shchelkin spiral dimensions on characteristics of deflagration-to-detonation transition

The objective of this investigation was to achieve the shortest possible distance for the deflagration-to-detonation transition (DDT) for a pulse detonation engine without losing the engine’s simplicity. The effects of rapid flame propagation, rotating velocity, and Shchelkin spiral dimensions in the vortex flow (VF) on DDT characteristics were examined. A VF field was established in the ignition and transition domains of a detonation tube using a VF-type injector. The flame propagation in the ignition domain was observed by a high-speed video camera and the detonation propagation process was observed by measuring the pressure and ionization current in the detonation tube. The DDT distance in the VF could be shortened by 50–57 % of that in the counterflow by optimizing the VF and the Shchelkin spiral dimensions. The shortening effect became remarkable as the rotating velocity increased. The governing factors for this effect are considered to be the formation of an area of higher energy density in the ignition domain of the tube, as well as flame acceleration due to rapid flame propagation in the VF and turbulence promotion near the tube wall by the rotating velocity and the Shchelkin spiral in the transition domain of the tube. However, the combined effects of VF and the Shchelkin spiral on the shortening of the DDT distance were deteriorated in very strong turbulence. It is necessary to optimize the rotating velocity and dimensions of the Shchelkin spiral to achieve the shortest possible distance of DDT in the VF.     

Explosive-driven shock wave and vortex ring interaction with a propane flame

Experiments were performed to analyze the interaction of an explosively driven shock wave and a propane flame. A 30 g explosive charge was detonated at one end of a 3-m-long, 0.6-m-diameter shock tube to produce a shock wave which propagated into the atmosphere. A propane flame source was positioned at various locations outside of the shock tube to investigate the effect of different strength shock waves. High-speed retroreflective shadowgraph imaging visualized the shock wave motion and flame response, while a synchronized color camera imaged the flame directly. The explosively driven shock tube was shown to produce a repeatable shock wave and vortex ring. Digital streak images show the shock wave and vortex ring propagation and expansion. The shadowgrams show that the shock wave extinguishes the propane flame by pushing it off of the fuel source. Even a weak shock wave was found to be capable of extinguishing the flame.     

A high-speed photographic study of the transition from deflagration to detonation wave

Experiments were conducted to investigate the DDT process of the oxyhydrogen gas in the rectangular detonation tube of 3 m long. The repeated obstacle was installed near the ignition plug and the effects of the obstacle on the DDT process were investigated. The behaviour of the combustion and detonation wave were visualized utilizing Imacon high-speed camera with the aid of Schlieren optics. As a result, DDT process was visualized, i.e. (i) multiple shock waves were induced by the expanding combustion wave, because the combustion flame played a role as a piston and compressed the unburned gases. (ii) The acceleration of the combustion wave was occurred and the distance between the shock wave and the combustion flame became shorter. (iii) Eventually, the local explosion was occurred and cause overdriven detonation wave to propagate at the velocity of about 3 kms⁻¹. An abridged version of this paper was presented at the 15th Int. Colloquium on the Dynamics of Explosions and Reactive Systems at Boulder, Colorado, from July 30 to August 4, 1995     

粒状火药床燃烧转爆轰的研究

以多－４５火药为研究对象，采用离子探针测速和应变片测压的技术，对强约束（钢管）条件下火药颗粒床燃烧转爆轰全过程中的火焰烽和压缩波进行了测量。提出了粒状火药燃烧转爆轰的机理。还研究了不同实验条件下火药燃烧转爆轰的敏感性。     

氢燃料缓燃向爆震转捩过程中波与火焰的匹配特性

为了解氢燃料爆震过程中压力波与火焰之间相互匹配的特性,在60mm60mm2000mm 方 爆震管内,用氢气和空气混合物进行了单爆震性能研究。在爆震转捩区内布置压力传感器与离子探针,用来 监控压力波和火焰的信号,同时利用高速摄影仪集中拍摄转捩区域。根据压力波和火焰面在爆震管不同时刻 的强度特性、速度特性及位置特性来分析爆震过程中波与火焰匹配的规律。结果表明:压力波和火焰的强度 呈现为相互正反馈匹配性质;缓燃向爆震转捩(DDT)过程中,压力波和火焰的速度表现为相互交替的变化过 程,且缓燃阶段中火焰速度的增幅大于压力波速度的增幅;当火焰面追赶上激波时,产生过爆,火焰面会临时 位于激波前面;在过爆衰减为正常爆震波的过程中,激波在火焰前面。     

Mechanism of deflagration-to-detonation transitions above repeated obstacles

Experiments are carried out to investigate the mechanism of the deflagration-to-detonation transition (DDT). Because, this mechanism has relevance to safety issues in industries, where combustible premixed gases are in general use. A stoichiometric gas of oxygen and hydrogen (oxy-hydrogen) is ignited in a tube, repeated obstacles are installed, and the DDT behaviours are visualized using a high-speed video camera. The pitch and height of the repeated obstacles and the initial pressure of the oxy-hydrogen premixed gas are varied in an attempt to obtain the optimum conditions that cause DDT a short distance from the ignition source. The experiments identified DDT as being essentially caused by one of the following mechanisms: (1) A deflagration wave is accelerated in terms of a vortex, which is generated behind the obstacle, and the flame acceleration induces a secondary shock wave. Eventually, the shock–flame interaction ahead of the obstacle causes DDT via a very strong local explosion. (2) Each shock wave generated by relatively weak local explosions between the obstacles is not sufficient to cause DDT directly, but DDT results from an accumulation of shock waves. The detonation induction distance is also examined, taking into account the physical and chemical parameters of the obstacles and the oxy-hydrogen premixed gas.     

气流特征对水平长管内石松子粉尘爆炸火焰结构的影响

为探索气流特征对水平长管内粉尘爆炸火焰结构的影响, 对采用加压送气传输方式形成的石松子粉尘云经静电引燃后其火焰在水平长管内的传播特性进行实验。利用热线风速仪测量不同气流条件下沿管径方向的速度分布和湍流强度分布, 采用高速摄像系统记录了火焰在水平管道内的传播过程。实验观察到, 即使管内石松子粉尘质量分数相同, 仍然会出现2种不同类型的火焰结构:一种类型火焰轮廓规则、清晰, 火焰中心为连续的黄色发光区并由红色边缘火焰包裹; 另一种类型火焰空间离散, 火焰发光区局部存在, 散乱地呈现不规则状态。详细分析不同气流条件对火焰结构的影响。     

Effects of boundary layer on flame propagation generated by forced ignition behind an incident shock wave

To study the effects of the boundary layer on the deflagration to detonation transition (DDT) process, the mixture behind an incident shock wave was ignited using laser breakdown. Ignition timing was controlled so that the interaction of the resulting flame with a laminar or turbulent boundary layer could be examined. In the case of the interaction with a laminar boundary layer, wrinkling of the flame was observed after the flame reached the corner of the channel. On the other hand, interaction with the turbulent boundary layer distorted the flame front and increased the spreading rate of the flame followed by prompt DDT. The inner structure of the turbulent boundary layer plays an important role in the DDT process. The region that distorted the flame within the turbulent boundary layer was found to be the intermediate region \(0.01< y/\delta < 0.4\), where y is the distance from the wall and \(\delta \) is the boundary layer thickness. The flame disturbance by the turbulent motions is followed by the flame interaction with the inner layer near the wall, which in turn generates a secondary-ignition kernel that produced a spherical accelerating flame, which ultimately led to the onset of detonation. After the flame reached the intermediate region, the time required for DDT was independent of the ignition position. The effect of the boundary layer on the propagating flame, thus, became relatively small after the accelerating flame was generated.     

DDT in fuel–air mixtures at elevated temperatures and pressures

An experimental study was carried out to investigate flame acceleration and deflagration-to-detonation transition (DDT) in fuel–air mixtures at initial temperatures up to 573 K and pressures up to 2 atm. The fuels investigated include hydrogen, ethylene, acetylene and JP-10 aviation fuel. The experiments were performed in a 3.1-m long, 10-cm inner-diameter heated detonation tube equipped with equally spaced orifice plates. Ionization probes were used to measure the flame time-of-arrival from which the average flame velocity versus propagation distance could be obtained. The DDT composition limits and the distance required for the flame to transition to detonation were obtained from this flame velocity data. The correlation developed by Veser et al. (run-up distance to supersonic flames in obstacle-laden tubes. In the proceedings of the 4th International Symposium on Hazards, Prevention and Mitigation of Industrial Explosions, France (2002)) for the flame choking distance proved to work very well for correlating the detonation run-up distance measured in the present study. The only exception was for the hydrogen–air data at elevated initial temperatures which tended to fall outside the scatter of the hydrocarbon mixture data. The DDT limits obtained at room temperature were found to follow the classical d/λ = 1 correlation, where d is the orifice plate diameter and λ is the detonation cell size. Deviations found for the high-temperature data could be attributed to the one-dimensional ZND detonation structure model used to predict the detonation cell size for the DDT limit mixtures. This simple model was used in place of actual experimental data not currently available. PACS 47.40.-x; 47.70.Fw This paper was based on work that was presented at the 19th Interna-tional Colloquium on the Dynamics of Explosions and Reactive Sys-tems, Hakone, Japan, July 27 - August 1, 2003     

DDT in a smooth tube filled with a hydrogen–oxygen mixture

Results of experimental study on DDT in a smooth tube filled with sensitive mixtures having detonation cell size from 1 to 3 orders of magnitude smaller than the tube diameter are presented. Stoichiometric hydrogen–oxygen mixtures were used in the tests with initial pressure ranging from 0.2 to 8 bar. A dependence of the run-up distance to DDT on the initial pressure is studied. This dependence is found to be close to the inverse proportionality. It is suggested that the flow ahead of the flame results in formation of the turbulent boundary layer. This boundary layer controls the scale of turbulent motions in the flow. A simple model to estimate the maximum scale of the turbulent pulsations (boundary layer thickness) at flame positions along the tube is presented. The largest scale of the turbulent motions at the location of the onset of detonation is shown to be 1 order of magnitude greater than the detonation cell widths, λ, in all the tests. It is suggested that the onset of detonation is triggered during flame acceleration as soon as the maximum scale of the turbulent pulsations increases up to about 10 λ. The model to estimate the maximum size of turbulent motions, δ, and the correlation δ≈ 10λ, give a basis for estimations of the run-up distances to DDT in tubes with internal diameter D > 20λ. PACS 47.40.-x; 47.27.Nz This paper was based on work that was presented at the 19th Inter-national Colloquium on the Dynamics of Explosions and Reactive Systems, Hakone, Japan, July 27 - August 1, 2003