等离子体点火对燃烧转爆轰影响的数值计算

采用CE/SE方法对耦合的流体力学方程与麦克斯韦方程求解,对等离子体点火和气液两相爆轰过程进行数值模拟.讨论了3种不同点火位置对燃烧转爆轰(DDT)的影响.结果表明,等离子体点火可以在短时间内点燃爆轰管内汽油/空气混合物,经过一系列复杂的波系与波系、波系与管壁之间的相互作用最终形成稳定的爆轰波.壁面点火比中心点火具有优...     

二维守恒元和求解元方法在两相爆轰流场计算中的应用

应用二维守恒元和求解元方法数值模拟脉冲爆轰发动机内汽油/空气两相燃烧转爆轰的过程.分析了爆轰波从开始产生到形成稳定的全过程.研究了点火能量对燃烧转爆轰过程的影响:点火能量越小,DDT时间越长;若点火能量过小就不能形成DDT.同时研究了液滴半径对爆轰参数的影响:液滴半径增大,爆轰波压力和速度随之减小,DDT时间增加;液滴半径过大,则爆轰波不能形成.爆轰波压力计算值与实验值两者趋势符合得较好.     

浓度梯度对T型管中爆轰波传播特性的影响

针对爆轰波在浓度梯度作用下衍射、熄爆到再起爆过程,基于开源软件OpenFOAM研究了两种不同混合气在3种不同浓度梯度下流场特征.结果表明:随着浓度梯度增大,横向爆轰波强度会减弱,爆轰波更易解耦.前导激波与浓度梯度相互作用会使爆轰波面发生弯曲,并且改变横向爆轰波和马赫杆的传播过程.对于稳定气体(H2/O2/Ar),爆轰波...     

超级爆震中火焰传播转爆轰现象的研究

模拟了一台高压缩比发动机下超级爆震的燃烧过程,分析火焰传播转爆轰(DDT)过程中压力如何影响末端混合气自燃,以及发生爆轰后的自维持过程．结果表明：压力是火焰传播作用于自燃并引发爆轰的主要原因,在短时间内经历压力波两次压缩,这不同于活塞压缩的原因在于这种压缩具有方向性．此外,维持爆轰需要压力波前新自燃点能量释放加速压力波,存在能量释放速度较压力波速度减小和增大两种自燃点状态,整个过程表现为：自燃释放压力波传递引发自燃状态1,压力波缓慢增强引发自燃状态2,自燃状态1下能量释放速度相对压力波速度减小,自燃状态2下能量释放速度相对压力波速度增大．     

管道截面突缩对爆轰波起爆特性的影响

为研究管道截面突缩对爆轰波起爆特性的影响,在突缩比为5:3的截面突缩管道及直管内对不同初始压力下甲烷氧气预混气体的起爆特性进行了实验研究,利用离子探针获得管道内火焰传播速度,并通过二维数值模拟探究了3种不同突缩比的截面突缩管道内火焰及压力的传播特性.实验结果表明,截面突缩管道内爆轰波起爆距离随着初始压力的降低而逐渐增加...     

烈性爆震下活塞材料破坏实验

已有研究表明,乙炔/氧气混合气在燃烧室内产生的爆轰波会发生汇聚现象并且容易破坏活塞材料.为了揭示烈性爆震下影响爆轰波破坏力的关键因素,通过改变活塞试件的厚度和混合气的初始状态来进行活塞材料破坏实验.结果表明,对于烈性爆震,活塞顶部中心厚度的选择存在最佳值.当初始压力超过一定的安全值之后,试件的中心挠度会急剧增大.当量比从1.0增加到1.5时,混合气变浓,爆轰波破坏力并不会减弱.当混合气当量比从1降低到0.5时,爆轰波的破坏力明显减弱.     

高压缩比甲醇发动机中爆轰现象研究

甲醇发动机在压缩比过度提高后会出现烈性爆震,甚至造成对活塞的破坏.为了揭示这种烈性爆震现象,本研究进行了数值模拟计算,分析了末端混合气的化学反应过程,揭示了压力波导致自燃、自燃又反过来影响压力波的机理.研究结果表明,有两种方式导致了爆轰波的形成,第一种是爆燃转爆轰,该过程发生在正常火焰面上;第二种是直接起爆,该过程发生在自燃点上.早期形成的压力波在缸内振荡,促进了末端混合气的低温反应,为爆轰的形成积累了充足的自由基.     

多循环喷雾爆震的特性研究

在无阀式脉冲爆震发动机模型机上进行了多循环喷雾两相爆震的实验研究．点火后爆震管内压力上升需要一定的延迟时间,但是迅速增压过程是在火焰传播到一定区域后开始的,在该区域形成向两个方向传播的压缩波,向未燃区传播的压缩波不断加强,形成爆震波,向已燃区传播的压缩波不断衰减;爆震峰值压力沿流向不断增加,压力上升速度加快,峰值随机差异放大;通过对压力历程的分析,用两种方法估算了两相爆震波诱导区的长度．实验中发现,两相爆震的点火延迟时间远大于爆燃向爆震转变的时间,两者之和相对于高频爆震循环非常可观,是限制两相脉冲爆震发动机频率提高的关键因素,并分析了多循环工作时的吸气和排气过程．     

掺混臭氧对微圆管内甲烷/氢气/氧气爆轰特性的影响

为研究掺混O3对2CH4-2H2-5O2混合气火焰、由缓燃向爆震转捩(DDT)过程及爆轰波传播特性的影响,使用高速摄像机(CCD)观测了不同O3浓度(0％,0.44％,0.95％,1.4％,2％)下,2CH4-2H2-5O2混合气在不同内径的毫米级(3mm、5mm、7mm)管道内的火焰传播情况,进而分析了掺混O3对2CH4-2H2-5O2DDT过程及爆轰波传播特性的影响。实验结果表明,添加臭氧可以显著加速火焰的传播速度,从而加快爆燃向爆轰(DDT)过程,缩短起爆距离。在相同管径下,随着混合臭氧浓度的增加,火焰的传播速度增加,起爆距离减小。而当添加的臭氧比率相同时,随着管道直径的减小,起爆距离缩短。     

微尺度细管内热损失对火焰动力学的影响

针对微尺度细管内火焰传播问题,通过数值模拟研究了点火能量和壁面热损失对火焰传播模式的影响.数值模拟中观察到熄火现象和低速稳定传播的火焰,但并未观察到爆燃向爆轰转变.在以二维管道高度和初始已燃区长度构成的坐标图中,低速稳定火焰传播模式呈现半岛形,具有上、下两个熄火极限,其中熄火下极限位于由初始点火区域面容比决定的双曲线上方．对于低速稳定火焰传播模式,火焰尖端的传播速度与层流火焰速度较为接近．火焰面前方的气体几乎静止,火焰面后方有一个回流区,已燃气体向闭口端运动．     

Numerical investigation on H2/Air non-premixed rotating detonation engine under different equivalence ratios

In this paper, three-dimensional numerical simulations are performed to investigate the formation and propagation characteristics of rotating detonation wave in a non-premixed engine. By changing the mass flow rate of H₂ and fixing air mass flow rate, the effects of equivalence ratio involving fuel lean and rich operating conditions are mainly discussed. Numerical results show that equivalence ratio plays a very critical role in the formation process and propagation mode, which further affects the propulsion performance of rotating detonation engine significantly. For current numerical geometry and operating conditions, the lean limit of equivalence ratio for formatting a stable RDW is about 0.4, dual-wave mode (at equivalence ratio of 0.6, 0.8, 1.0 and 1.4) and single-wave mode (at equivalence ratio of 1.2) are obtained, respectively. When equivalence ratio is 1.0, rotating detonation engine can exhibit excellent operating performance with the shortest formation time, best propagation stability, middling class thrust and specific impulse. Besides, the pressure contour analysis indicates that the effects of equivalence ratio and mass flow rate of H₂ on the collision strength and times during the re-initiation process are the main mechanisms for determining the formation possibility and propagation mode of rotating detonation wave. Besides, the intensity of accumulated pressure wave and distributions of equivalence ratio are two important factors for the generation of new detonation wave front. Furthermore, it is also detected from the comparisons of the propulsion performance that the effects of equivalence ratio on thrust and specific impulse under fuel lean conditions are more significant than those under fuel-rich conditions.     

Direct observations of reaction zone structure in propagating detonations

We report experimental observations of the reaction zone structure of self-sustaining, cellular detonations propagating near the Chapman-Jouguet state in hydrogen-oxygen-argon/nitrogen mixtures. Two-dimensional cross sections perpendicular to the propagation direction were imaged using the technique of planar laser induced fluorescence (PLIF) and, in some cases, compared to simultaneously acquired schlieren images. Images are obtained which clearly show the nature of the disturbances in an intermediate chemical species (OH) created by the variations in the strength of the leading shock front associated with the transverse wave instability of a propagating detonation. The images are compared to 2-D, unsteady simulations with a reduced model of the chemical reaction processes in the hydrogen-oxygen-argon system. We interpret the experimental and numerical images using simple models of the detonation front structure based on the “weak” version of the flow near the triple point or intersection of three shock waves, two of which make up the shock front and the third corresponding to the wave propagating transversely to the front. Both the unsteady simulations and the triple point calculations are consistent with the creation of keystone-shaped regions of low reactivity behind the incident shock near the end of the oscillation cycle within the “cell.”     

Numerical simulation on the operating characteristics of rotating detonation ramjet engines at high flight mach number

For high-Mach-number incoming flow circumstances, a rotating detonation ramjet engine configuration is proposed in this research. By installing supporting blocks at the rear of the combustor, this configuration achieves continuous rotating detonation operation. Based on the Comparison of the flow structures obtained from the engine configuration with and without the supporting block before and after detonation ignition respectively, we obtain the intrinsic mechanism of detonation wave's propagation and re-initiation under the action of the supporting block. The supporting block creates a deflagration wave that is almost stationary before detonation ignition. In the detonation-ignited state, the deflagration wave is continually formed and traveling upstream under the influence of the supporting block, which is analogous to the periodical before detonation ignition of a transverse wave structure. The dynamic deflagration wave will cause the incomplete reactants behind the detonation wave to burn as the intensity of the detonation wave decreases. As a result, the incident shock wave is transformed into a Mach stem to achieve the re-initiation of the detonation wave.     

Coupling characteristic analysis and propagation direction control in hydrogen–air rotating detonation combustor with turbine

Two-dimensional numerical simulations are performed to investigate the interactions between a rotating detonation combustor (RDC) and turbine. The flowfield structure and coupling characteristics are analyzed under different equivalent ratios. Furthermore, the formation mechanism of the detonation wave direction is illustrated. Results show that although RDCs increase the average turbine work, they enhance the flowfield oscillation and maintain the quasi-periodic fluctuation in the turbine work. Compared to counter-clockwise propagation, the pressure oscillation attenuation and total pressure loss through the turbine guide vane increase when the detonation wave propagates clockwise. When the detonation wave height is low, RDCs are more prone to quenching due to the impact of reflected waves. After re-ignition, the detonation wave direction is unrelated to the initial ignition direction and is random. Introduction of deflecting wedges into RDCs enables the automatic control of the detonation wave direction but causes extra total pressure loss of at least 3.6%.     

Self-organized generation of transverse waves in diverging cylindrical detonations

Self-organized generation of transverse waves associated with the transverse wave instabilities at a diverging cylindrical detonation front was numerically studied by solving two-dimensional Euler equations implemented with an improved two-step chemical kinetic model. After solution validation, four mechanisms of the transverse wave generation were identified from numerical simulations, and referred to as the concave front focusing, the kinked front evolution, the wrinkled front evolution and the transverse wave merging, respectively. The propagation of the cylindrical detonation is maintained by the growth of the transverse waves that match the rate of increase in surface area of the detonation front to asymptotically approach a constant average number of transverse waves per unit length along the circumference of the detonation front. This cell bifurcation phenomenon of cellular detonations is discussed in detail to gain better understanding on detonation physics.     

Experimental and numerical research on rotating detonation combustor under non-premixed conditions

In order to investigate the formation process and propagation characteristics of detonation wave, developing process of detonation wave from initiation to stable detonation formation under non-premixed conditions has been studied by experiments and numerical simulation. The results show that when mass flow rates of air and hydrogen are 158.957 g/s and 2.728 g/s respectively, stable detonation can be formed in the combustor. Due to the lower inlet pressure, there is an unstable stage in combustor before the stable detonation is formed. Reducing the air pressure will increase the lowest detonation limit of combustor and lead to flame-out and re-initiation in the combustor. The propagation direction of detonation wave may change after re-initiation. Non-premixed intake structure lead to the inconsistency of rotating detonation combustion fluid in the radial direction. Moreover, peak pressure appears near the outer wall, while peak temperature appears near the inner wall.     

Studies in the transition from deflagration to detonation in granular explosives—II. Transitional characteristics and mechanisms observed in 91/9 RDX/Wax

The apparatus and instrumentation described in the previous paper have been used to observe the transitional behavior of burning to detonation for a 91/9 RDX/wax mixture. Transitions to detonation were observed for all densities between 67 and 95% TMD. The sequence of observed events following ignition of the explosives charge was: stable propagation of a convective flame front, compaction of the more porous burning charges, formation of a postconvective (compressive) wave in the ignition region, subsequent coalescence of compressive waves some distance beyond the ignition region, and the formation of a detonation wave 1 to 2 cm beyond the intersection of the convective and postconvective fronts. It is proposed that the shock to detonation sequence starts in the region of coalescence of compressive waves. The velocity of the convective flame front was observed to increase with increasing charge density in agreement with earlier results from ammonium picrate. The predetonation column length as a function of charge compaction exhibited a minimum; such minima have been reported by other workers for PETN, RDX, and HMX.     

Numerical study of acoustic coupling in spinning detonation propagating in a circular tube

Spinning detonations propagating in a circular tube were numerically investigated with a two-step reaction model by Korobeinikov et al. The time evolutions of the simulation results were utilized to reveal the propagation behavior of single-headed spinning detonation. Three distinct propagation modes, steady, unstable, and pulsating modes, are observed in a circular tube. The track angles on a wall were numerically reproduced with various initial pressures and diameters, and the simulated track angles of steady and unstable modes showed good agreement with those of the previous reports. In the case of steady mode, transverse detonation always couples with an acoustic wave at the contact surface of burned and unburned gas and maintains stable rotation without changing the detonation front structure. The detonation velocity maintains almost a CJ value. We analyze the effect of acoustic coupling in the radial direction using the acoustic theory and the extent of Mach leg. Acoustic theory states that in the radial direction transverse wave and Mach leg can rotate in the circumferential direction when Mach number of unburned gas behind the incident shock wave in the transverse detonation attached coordinate is larger than 1.841. Unstable mode shows periodical change in the shock front structure and repeats decoupling and coupling with transverse detonation and acoustic wave. Spinning detonation maintains its propagation with periodic generation of sub-transverse detonation (new reaction front at transverse wave). Corresponding to its cycle, whisker is periodically generated, and complex Mach interaction periodically appears at shock front. Its velocity history shows the fluctuation whose behavior agrees well with that of rapid fluctuation mode by Lee et al. In the case of pulsating mode, as acoustic coupling between transverse detonation and acoustic wave is not satisfied, shock structure of spinning detonation is disturbed, which causes failure of spinning detonation.     

Simulations of detonation wave propagation in rectangular ducts using a three-dimensional WENO scheme

This paper reports high resolution simulations using a fifth-order weighted essentially non-oscillatory (WENO) scheme with a third-order TVD Runge-Kutta time stepping method to examine the features of detonation front and physics in square ducts. The simulations suggest that two and three-dimensional detonation wave front formations are greatly enhanced by the presence of transverse waves. The motion of transverse waves generates triple points (zones of high pressure and large velocity coupled together), which cause the detonation front to become locally overdriven and thus form “hot spots.” The transversal motion of these hot spots maintains the detonation to continuously occur along the whole front in two and three dimensions. The present simulations indicate that the influence of the transverse waves on detonation is more profound in three dimensions and the pattern of quasi-steady detonation fronts also depends on the duct size. For a “narrow” duct (4L×4L where L is the half-reaction length), the detonation front displays a distinctive “spinning” motion about the axial direction with a well-defined period. For a wider duct (20L×20L), the detonation front exhibits a “rectangular mode” periodically, with the front displaying “convex” and “concave” shapes one following the other and the transverse waves on the four walls being partly out-of-phase with each other.     

Knocking combustion in spark-ignition engines

Knocking combustion research is crucially important because it determines engine durability, fuel consumption, and power density, as well as noise and emission performance. Current spark ignition (SI) engines suffer from both conventional knock and super-knock. Conventional knock limits raising the compression ratio to improve thermal efficiency due to end-gas auto-ignition, while super-knock limits the desired boost to improve the power density of modern gasoline engines due to detonation. Conventional combustion has been widely studied for many years. Although the basic characteristics are clear, the correlation between the knock index and fuel chemistry, pressure oscillations and heat transfer, and auto-ignition front propagation, are still in early stages of understanding. Super-knock combustion in highly boosted spark ignition engines with random pre-ignition events has been intensively studied in the past decade in both academia and industry. These works have mainly focused on the relationship between pre-ignition and super-knock, source analyses of pre-ignition, and the effects of oil/fuel properties on super-knock. The mechanism of super-knock has been recently revealed in rapid compression machines (RCM) under engine-like conditions. It was found that detonation can occur in modern internal combustion engines under high energy density conditions. Thermodynamic conditions and shock waves influence the combustion wave and detonation initiation modes. Three combustion wave modes in the end gas have been visualized as deflagration, sequential auto-ignition and detonation. The most frequently observed detonation initiation mode is shock wave reflection-induced detonation (SWRID). Compared to the effect of shock compression and negative temperature coefficient (NTC) combustion on ignition delay, shock wave reflection is the main cause of near-wall auto-ignition/detonation. Finally, suppression methods for conventional knock and super-knock in SI engines are reviewed, including use of exhaust gas recirculation (EGR), the injection strategy, and the integration of a high tumble - high EGR-Atkinson/Miller cycle. This paper provides deep insights into the processes occurring during knocking combustion in spark ignition engines. Furthermore, knock control strategies and combustion wave modes are summarized, and future research directions, such as turbulence-shock-reaction interaction theory, detonation suppression and utilization, and super-knock solutions, are also discussed.