爆震波传播速度同阻力和热损失的一般关系

本文采用－维稳态ＺＮＤ模型，从理论分析和数值计算上详细研究了爆震波的结构和非绝热粗糙管中摩擦阻力和热损失对爆震波传播的影响．推导了爆震波的传播方程，揭示了多种爆震机制和爆震极限的存在及其机理。对低速爆震的发生给出了理论解释．     

Experimental investigations of detonation initiation by hot jets in supersonic premixed flows

<正>A new method to initiate and sustain the detonation in supersonic flow is investigated.The reaction activity of coming flow may influence the result of detonation initiation.When a hot jet initiates a detonation wave successfully, there may exist two types of detonations.If the detonation velocity is greater than the velocity of coming flow,there will be a normal detonation here.Because of the influence of boundary layer separation,the upstream detonation velocity is much greater than the Chapman-Jouguet(CJ) detonation velocity.On the other hand,if the detonation velocity is less than the velocity of coming flow,an oblique detonation wave(ODW) will form.The ODW needs a continuous hot jet to sustain itself.If the jet pressure is lower than a certain value,the ODW will decouple.In contrast,the normal detonation wave can sustain itself without the hot jet.     

Experimental study of detonation in a cryogenic two-phase H2–O2 flow

Direct initiation and propagation of detonation through a cryogenic two-phase flow constituted by liquid oxygen droplets in gaseous hydrogen at 100 K are experimentally investigated. The influence of droplet size distribution is characterized in a cryogenic gaseous helium and liquid oxygen two-phase flow. Droplet sizing and detonation experiments are conducted by varying different parameters: distance from the injector, helium and hydrogen mass flow rates, global equivalence ratio and addition of gaseous nitrogen. Droplet size distributions reveal quick vaporization of the smallest droplets of the cryogenic jet. Results in terms of wave velocity, pressure, and detonation cells show that a detonation wave can be directly initiated, with a propagation wave velocity of 20% higher than the Chapman–Jouguet value. Cell size measurements show that the mixture sensitivity is not affected by the presence of droplets. Addition of gaseous nitrogen reduces only slightly the peak pressure, but the detonation velocity is reduced by about 30%.     

A flame technique to isolate the detonation/product interface relevant to rotating detonation engines

A novel experimental technique is proposed to study the detonation propagation in a layer of non-reacted gas weakly confined by combustion products. This problem is relevant to rotating detonation engines, where transverse detonations are confined by products of a previous rotation cycle, and other applications such as industrial safety. The experimental technique utilizes a flame ignited along the top wall in a long channel. The preferential growth of the flame along the long direction of the channel creates a finger flame and permits to create a narrow layer of unburned gas. A detonation ignited outside of this layer then propagates through the layer. This permits to conduct accurate observations of the detonation interaction with the inert gas and determine the boundary condition of the interaction. The present paper provides a proof-of-concept demonstration of the technique in a 3.4 m by 0.2 m channel, in which long finger flames were observed in ethylene-oxygen mixtures. The flame is visualized by high-speed direct luminosity over its entire travel, coupled with pressure measurements. A direct simulation of the flame growth served to supplement the experiments and evaluate the role of the induced flow by the flame growth, which gives rise to a non-uniform velocity distribution along the channel length. Detonation experiments were also performed at various layer heights in order to establish the details of the interaction. The structure was visualized using high speed Schlieren video. It was found that an inert shock always runs ahead of the detonation wave, which gives rise to a unique double shock reflection interaction.     

凝聚炸药爆轰波在高声速材料界面上的折射现象分析

凝聚炸药爆轰在边界高声速材料约束下传播时,爆轰波会在约束材料界面上产生复杂的折射现象.本文针对凝聚炸药爆轰波在高声速材料界面上的折射现象展开理论和数值模拟分析.首先通过建立在爆轰ZND模型上的改进爆轰波极曲线理论给出爆轰波折射类型,然后发展一种求解爆轰反应流动方程的基于特征理论的二阶单元中心型Lagrange计算方法来数值模拟典型的爆轰波折射过程.从改进爆轰波极曲线理论和二阶Lagrange方法数值模拟给出的结果看出,凝聚炸药爆轰波在高声速材料界面上的折射类型有四种:反射冲击波的正规折射、带束缚前驱波的非正规折射、带双Mach反射的非正规折射、带λ波结构的非正规折射.     

Detonation propagation across a stratified layer with a diffuse interface

A study was conducted to examine detonation propagation in a stratified layer of hydrogen-oxygen-nitrogen above an inert gas in a horizontal narrow channel. The stratified layer was produced by a gravity current, generated by retracting a door initially separating a hydrogen-oxygen-nitrogen mixture in the predetonator and a heavier inert gas in the test-section. A steady detonation wave generated in the predetonator was transmitted into the stratified layer. The reactivity of the predetonator mixture was varied via the hydrogen-oxygen equivalence ratio and the amount of nitrogen dilution. Schlieren photography was used to visualize the detonation front in the test-section, and soot foils were used to obtain the cellular structure. Schlieren imaging showed a curved detonation front that decoupled at about mid channel height, into a shock wave and trailing contact surface. Both the hydrogen-oxygen-nitrogen reactivity and the type of inert gas initially in the test-section affected the distance travelled by the detonation wave in the stratified layer. The mixture composition distribution within the test-section before ignition was obtained via a three-dimensional CFD simulation. The lateral extent of the cellular structure captured on the soot foil, coincided with the calculated inert gas mole fraction contour that corresponds to a sharp increase in the ZND induction zone length, e.g., 70% argon dilution for a stoichiometric hydrogen-oxygen predetonator mixture.     

Propagation of gaseous detonation across inert layers

In rotating detonation engines and explosion accidents, detonation may propagate in an inhomogeneous mixture with inert layers. This study focuses on detonation propagation in a stoichiometric H₂/O₂/N₂ mixture with multiple inert layers normal to the detonation propagation direction. One- and two-dimensional simulations considering detailed chemistry are conducted. The emphasis is placed on assessing the effects of inert layer on detonation reinitiation/failure, detonation propagation speed, detonation cell structure and cell size. Specifically, the inert layer thickness and the spacing between two consecutive inert layers are varied. Either detonation reinitiation or failure across the inert layers is observed. It is found that successful detonation reinitiation occurs only at relatively small values of the inert layer thickness and spacing. For each given value of the inert layer spacing, there is a critical inert layer thickness above which detonation fails after crossing the inert layers. This critical inert layer thickness is found to decrease as the inert layer spacing increases. The detailed process of detonation reinitiation across the inert layers is analyzed. The interaction between the transverse shock waves is shown to induce local autoignition/explosion and eventually over-driven detonation development in the reactive layer. The averaged detonation propagation speed in the inhomogeneous mixture is compared to the CJ speed and very good agreement is achieved. This indicates that the inert layer does not affect the detonation propagation speed once successful detonation reinitiation happens. Unlike the detonation speed, the detonation cell structure and cell size are greatly affected by the inert layer results. For the first time, large cellular structure with size linearly proportional to the inert layer spacing is observed for detonation propagation across inert layers. Besides, a double cellular structure is observed for relatively large spacing between inert layers. The formation of double cellular structure is interpreted.     

Dynamics of detonation waves in a channel with variable cross section and filled with bubbly fluid

The flow of bubbly fluid comprising a mixture of bubbles filled with explosive and inert gases, which is driven through a converging channel, was studied. Depending on the velocity of the hummer hitting the bubbly fluid boundary, the flow may be accompanied by the development of detonation waves which compress the bubbles with inert gas.     

Initiation and propagation of detonation waves in combustible high speed flows

The initiation and propagation of detonation waves in combustible high speed flows were studied experimentally. A planar detonation wave traveling in an initiation tube was transmitted into a test section where a combustible high speed flow was induced by an incident shock wave generated in a shock tube. In this study, the flow Mach numbers were obtained as 0.9 and 1.2. The experimental results show that depending on the flow velocity, the apparent propagation velocity of a detonation wave is higher in the upstream and lower in the downstream direction than the CJ velocity. Smoked plate records reveal cellular patterns deformed in the flow direction, and the calculated aspect ratios of the cell were found to agree well with the experimental ones on the basis of the assumption that the velocity of the transverse wave is not affected by the flowing mixture. By analyzing the shock-wave diffraction at the position where there is an abrupt change in the area, on the basis of Whitham’s theory, it was deduced that in the present experimental set-up, the detonation was initiated by the reflection of the diffracted shock waves on the sidewalls of the test section. The agreement between the experimental and calculated results regarding the position of the cellular patterns on the smoked plate record indicated that the position of detonation initiation in high speed flows is shifted downstream due to the flow velocity.     

Initiation of detonation by conical projectiles

Initiation of detonation by a hypersonic conical projectile launched into a combustible gas mixture is investigated. From analytic considerations of the flowfield, energetic and kinetic limits are proposed to predict the conditions required to initiate an oblique detonation wave in the mixture. To experimentally investigate these limits, projectiles with cone half angles varying from 15° to 60° were launched into a stoichiometric mixture of hydrogen/oxygen with 70% argon dilution at initial pressure between 10 and 200 kPa. The projectiles were launched from a combustion-driven gas gun at velocities as great as 2.5 km/s (corresponding to 150% of the Chapman Jouguet velocity). Pictures of the flowfields generated by the projectiles were taken via schlieren photography. Five combustion regimes could be observed about the projectile ranging from a prompt and delayed oblique detonation wave formation, combustion instabilities, a wave splitting, and an inert shock wave. The two theoretical limits provide a means to interpret the observed flowfield regimes and are in satisfactory agreement with the experimental results.     

Transformation of detonation waves at the interface between bubble media

The passage of detonation waves through the interface between bubble media is studied experimentally. Data are obtained for the structure, velocity, and pressure of an incident detonation wave and a wave transmitted through the interface.     

超压爆轰产物声速以及热力学CJ点的实验研究

超压爆轰产物声速是建立超压爆轰产物状态方程的基础性实验数据,而CJ点数据是反映炸药爆轰性能的重要参数。利用稀疏波追赶技术,通过光纤探针监测三氯甲烷中稀疏波追赶向前冲击波的过程,测量了不同压力点下JB-9014炸药超压爆轰产物的声速,得到了拉格朗日声速随粒子速度的变化曲线,由Lc线与稳定爆速D的交点确定了热力学CJ点,对JB-9014炸药所得到的CJ压力为28.8 GPa,与通常测量值28.5 GPa仅相差0.3 GPa。介绍了应用光纤探针测量爆轰驱动飞片的速度和平面性的方法,应用该方法得到了飞片的击靶速度和形状,此方法具有较高的测量精度。     

Nonequilibrium Zeldovich-von Neumann-Doring theory and reactive flow modeling of detonation

This paper discusses the Nonequilibrium Zeldovich-von Neumann-Doring (NEZND) theory of self-sustaining detonation waves and the Ignition and Growth reactive flow model of shock initiation and detonation wave propagation in solid explosives. The NEZND theory identified the nonequilibrium excitation processes that precede and follow the exothermic decomposition of a large high explosive molecule into several small reaction product molecules. The thermal energy deposited by the leading shock wave must be distributed to the vibrational modes of the explosive molecule before chemical reactions can occur. The induction time for the onset of the initial endothermic reactions can be calculated using high pressure-high temperature transition state theory. Since the chemical energy is released well behind the leading shock front of a detonation wave, a physical mechanism is required for this chemical energy to reinforce the leading shock front and maintain its overall constant velocity. This mechanism is the amplification of pressure wavelets in the reaction zone by the process of de-excitation of the initially highly vibrationally excited reaction product molecules. This process leads to the development of the three-dimensional structure of detonation waves observed for all explosives. For practical predictions of shock initiation and detonation in hydrodynamic codes, phenomenological reactive flow models have been developed. The Ignition and Growth reactive flow model of shock initiation and detonation in solid explosives has been very successful in describing the overall flow measured by embedded gauges and laser interferometry. This reactive flow model uses pressure and compression dependent reaction rates, because time-resolved experimental temperature data is not yet available. Since all chemical reaction rates are ultimately controlled by temperature, the next generation of reactive flow models will use temperature dependent reaction rates. Progress on a statistical hot spot ignition and growth reactive flow model with multistep Arrhenius chemical reaction pathways is discussed. The text was submitted by the authors in English.     

Structure of detonation waves in pressed 2′,2′,2′-trinitroethyl-4,4,4-trinitrobutyrate

The reaction zones of steady detonation waves in pressed 2′,2′,2′-trinitroethyl-4,4,4-trinitrobutyrate (TNETB) charges with densities within 1.23–1.79 g/cm³ and initial powder dispersities of 5 and 80 μm were studied with the use of a VISAR interferometer. It was demonstrated that the boundaries of the initial density range within which a pressure growth is observed instead of a chemical spike, predicted by the theory, are determined by the HE dispersity. The measured dependence of the detonation velocity on the initial HE density exhibits features suggestive of an underdriven detonation wave without a chemical spike. The peculiarities observed are accounted for by the heterogeneous structure of pressed HEs, the decomposition of which is of hot-spot character, occurring partly in the compression wave front.     

矩形管内临界爆轰动力学数值分析

 对矩形管内临界爆轰动力学特征进行了数值分析。采用基元反应描述爆轰化学反应过程，采用二阶附加半隐的龙格-库塔法和5阶WENO格式求解二维反应欧拉方程。对于25%氩稀释化学计量比的氢氧预混气体，当管道宽度为30 mm、初温为300 K时，产生临界爆轰的预混气体初压为3.5 kPa。在此临界条件下，获得了临界爆轰胞格结构、沿壁面的速度和峰值压力曲线及流场波系演变特征。着重对比分析了矩形管内临界爆轰与普通爆轰在爆轰波速度、平均速度、胞格宽长比、横波结构、未反应气囊及旋涡结构之间的差异，深入认识了临界爆轰的不稳定性和化学反应动力学特征。     

悬浮RDX炸药粉尘爆轰的数值模拟

用两相流模型对悬浮RDX炸药粉尘爆轰波进行了数值模拟。RDX炸药颗粒在爆轰波阵面后的高温高速气流中加速并升温,颗粒表面发生熔化。参考液滴在高速气流作用下剥离的效应,假设炸药熔化部分在高速气流的作用下发生剥离,破碎成极小的颗粒,瞬时发生分解反应,释放出能量支持爆轰波传播。数值模拟了在不同粒径和浓度的悬浮RDX炸药粉尘中爆轰波的发展与传播过程,得到了爆轰波流场中气-固两相的物理量分布,并确定了爆轰波参数。在较低的RDX粉尘浓度条件下,爆轰波阵面压力的峰值曲线出现振荡。当RDX粉尘浓度在80~150 g/m3时,数值模拟得到的爆轰波阵面压力峰值曲线的振荡是规则的;当RDX粉尘浓度为70 g/m3时,爆轰波阵面压力峰值曲线出现不规则振荡。     

旋转爆震燃烧室与涡轮导向器组合实验研究

旋转爆震涡轮发动机正获得广泛的关注,但旋转爆震燃烧室出口存在着高频的压力波动,压力波动会降低涡轮的工作效率并减小涡轮的工作寿命.基于旋转爆震波的传播特点,开展了旋转爆震燃烧室与涡轮导向器组合结构的实验研究.燃料为H₂,由位于燃烧室前端的120个小孔喷入燃烧室;氧化剂为空气,由径向环缝喷入燃烧室.在燃烧室内起爆旋转爆震波后,爆震产物直接流入导向器内.研究结果表明,随当量比的增加,燃烧室内爆震波的传播速度呈先增大后减小的趋势.在导向器出口仍存在与燃烧室内旋转爆震波同主频的振荡压力,但相对于导向器前的振荡压力,出口压力振幅减小了约64%.旋转爆震波传播速度的相对偏差先减小后增大,并且爆震波传播越稳定,其速度损失越小.      

Detonation properties of stoichiometric gaseous n-heptane/oxygen/argon mixtures

A study of detonation velocity and cellular structure for stoichiometric heptane/oxygen and for some stoichiometric heptane/oxygen/argon mixtures is carried out in a shock tube at low initial pressure. The critical conditions for the detonation onset and for the propagation of a self-sustained detonation wave are determined. A simplified form of the ZND model used in conjunction with a validated detailed kinetic model leads to the determination of the proportionality factor, A, between the detonation cell width, λ, and the induction distance, Δ, in the detonation wave. This A factor is of practical importance to estimate the detonation properties of n-heptane based mixtures including n-heptane/air. The prediction of detonation cell size λ for n-heptane based mixtures is discussed according to the recent semi-empirical detonation model of Gavrikov et al. The cell sizes predicted according to this detonation model are underestimated by a factor of about 8. The limitations of this model are underlined when applied to n-heptane based mixtures.     

Detonation of supersonic propane-air mixture by high-voltage plasma discharge

The detonation combustion of a supersonic flow of propane-air mixture, initiated by a pulsed discharge of a magnetoplasma compressor, is obtained in experiment. A backward wave of supersonic combustion propagating with a velocity of 450 m/s against the flow is observed.     

Mixing and detonation structure in a rotating detonation engine with an axial air inlet

High-fidelity simulations of an experimental rotating detonation engine with an axial air inlet were conducted. The system operated with hydrogen as fuel at globally stoichiometric conditions. Instantaneous data showed that the detonation front is highly corrugated, and is considerably weaker than an ideal Chapman–Jouguet wave. Regions of deflagration are present ahead of the wave, caused by mixing with product gases from the previous cycle, as well as the injector recovery process. It is found that as the post-detonation high pressure flow expands, the injectors recover unsteadily, leading to a transient mixing process ahead of the next cycle. The resulting flow structure not only promotes mixing between product and reactant gases, but also increases likelihood of autoignition. These results show that the detonation process is very sensitive to injector design and the transient behavior during the detonation cycle. Phase-averaged statistics and conditionally averaged data are used to understand the overall reaction structure. Comparisons with available experimental data on this configuration show remarkable good agreement of the predicted reacting flow structure.