烧蚀支板对超燃冲压发动机燃烧室性能的影响

为了提高超燃冲压发动机燃烧室的性能,本文提出了燃料喷注支板与烧蚀支板组合的燃烧室新方案,并研究了新方案对超燃冲压发动机燃烧室性能的影响。相比于单燃料喷注支板方式而言,加入烧蚀支板后,虽然燃烧室内的总压恢复系数有所下降,但燃烧室内燃料与空气的混合效率、燃烧效率均有显著提高,燃烧效率的提高弥补了燃烧室内总压损失所带来的机械能损失,使得燃料喷注支板和烧蚀支板组合方式下的燃烧室比冲高于单燃料喷注支板时的比冲。     

基于PDF-LES模型的凹腔支板火焰稳定器模拟

航空发动机加力燃烧室有进口气体温度高、速度高、湍流度大的特点,是极为典型的湍流与燃烧相互耦合的工况。大涡模拟(LES)兼具高精度与合理计算量两个特点,概率密度函数模型(PDF)适用于湍流与复杂化学反应相互耦合的问题。本文在基于PDF-LES的Aero Engine Combustor Simulation Code(AECSC)程序基础上,对凹腔支板火焰稳定器进行数值模拟。使用气相版本对有无凹腔支板结构分别进行三个速度入口条件下的甲烷湍流燃烧模拟,并用两相版本对带凹腔支板结构进行设计工况下煤油喷雾的模拟。结果表明:凹腔结构的火焰稳定性要优于无凹腔结构;凹腔支板结构对于液相燃料的控制能力较气相更强。     

基于凹腔驻涡的无焰燃烧室数值模拟

无焰燃烧的关键在于高温烟气与新鲜空气燃料的充分掺混。本文设计了一种基于凹腔驻涡的无焰燃烧室,并对其进行了零维和三维数值计算。零维数值计算运用简单的化学反应网络模型预测了燃烧室NO_x排放,凹腔当量比为0.5时,NO_x排放低于5 mg/m³（@15%O₂）。凹腔产生的高温烟气,可以使燃烧室后部温度分布均匀,消除了温度峰值,燃烧室实现了无焰燃烧。双凹腔结构有利于改善燃烧室出口温度分布。     

基于乙烯或氢气的吸气式旋转爆轰发动机实验

基于氢气的旋转爆轰发动机研究较多,而碳氢燃料与空气混合较为困难,导致基于乙烯的旋转爆轰发动机燃烧技术难度很高.使用宽视野范围的可视化燃烧室观察旋转爆轰波的研究在国内尚未开展.在同一燃烧室内进一步开展了乙烯或氢气的吸气式旋转爆轰实验,来流总温为283~284 K,燃烧室壁面有140°石英玻璃观察窗,便于观察旋转爆轰波运动过程.空筒燃烧室爆轰环腔外径为100 mm,轴向长度为151 mm.燃料通过150个直径0.8 mm圆柱孔进入燃烧室,空气通过喉部1 mm宽的收敛扩张环缝流入环腔.高速摄影和低高频压力传感器均验证了旋转爆轰波的存在和速度值.以氢气为燃料的旋转爆轰波速度最高可达理论值的101%,爆轰波增压效应可达40%左右,乙烯旋转爆轰波速度可达理论值的89%.旋转爆轰波结构容易发生变化,不规则.氢气旋转爆轰的维持对燃烧室的结构要求比碳氢燃料要低,比乙烯旋转爆轰波更加稳定.      

进口条件对超燃冲压发动机氢气燃烧流场特性的影响分析

对不同进口条件下的超燃冲压发动机燃烧室内氢气喷流超声速燃烧流动特性进行了数值模拟与分析.宽范围超燃冲压发动机是吸气式高超声速飞行器推进系统设计中的热点问题之一,受实验设备硬件条件及实验技术限制,数值模拟技术仍然是超燃冲压发动机燃烧室内燃气燃烧特性及流场特性的主要研究手段.采用基于混合网格技术的多组元N-S方程有限体积方法求解器,在不同进口Mach数及压强条件下,对带楔板/凹腔结构的燃烧室模型氢气喷流燃烧流场进行了数值模拟,对比分析了氢气喷流穿透深度、喷口前后回流区结构、掺混效率及燃烧效率等流场结构与典型流场参数的变化特性及影响规律.研究成果可为宽范围超燃冲压发动机喷流燃烧流动特性分析提供参考.      

吸气式高超声速飞行器机体/推进一体化内外流非定常耦合方法

基于吸气式高超声速飞行器机体/推进一体化的气动布局设计方式,文章提出了一种内外流一体化流场的耦合求解方法,其中燃烧室内流场采用考虑有限速率化学反应动力学模型的一维非稳态方法求解,进气道和尾喷管外流场采用二维CFD软件计算,进气道与燃烧室在耦合界面处通过一维平均方法实现静温、静压和Mach数等参数传递.并分别以日本国家航空与航天实验室（NAL）的氢燃料燃烧室模型作为内流场验证算例,以某典型高超声速飞行器一体化模型作为内外耦合流场验证算例.研究结果表明:有限速率化学反应准一维方法能较为准确地模拟燃烧室内燃烧流场,提出的内外流场耦合方法能够有效地计算出内外流耦合效应,计算后体压力分布与理论值较接近.该方法可为超燃冲压发动机的性能快速分析和吸气式高超声速飞行器机体/推进一体化的初步分析设计提供重要参考.      

超燃火焰稳定凹腔自激振荡特性的数值研究

对超声速冷流条件下用于超燃冲压发动机的凹腔火焰稳定器的自激振荡特性进行研究.采用混合RANS/LES方法对非定常流场进行数值模拟,考虑了凹腔的长深比和后缘角度两个关键参数.混合RANS/LES方法很好的捕捉到流场非定常大尺度结构并揭示了凹腔自由剪切层的演化过程.对凹腔压力振荡历程进行幅频分析,所得到的频率和理论分析结果与文献计算结果符合的很好.结果表明,凹腔的长深比和后缘角度对凹腔自激振荡特性都有很大的影响.随着凹腔长深比的减小,振荡能量趋于集中到某些频率对应的振荡模式上.随着凹腔后缘倾角的减小,大部分频率对应的振荡很快的被削弱;相对于陡后缘凹腔,小角度后缘凹腔只有较高频率对应的振荡模式存在.     

JF12激波风洞高Mach数超燃冲压发动机实验研究

针对高Mach数（Ma ≥ 7）超燃冲压发动机高气动阻力下的燃烧组织问题,提出一种双突扩燃烧室结构方案.使用数值模拟方法考察了射流与双突扩燃烧室组合方式的混合燃烧特性.设计了双突扩超燃冲压发动机模型,在力学研究所JF12长试验时间激波风洞内,开展了Ma=7.0和Ma=9.5的氢燃料点火和燃烧试验对比.在风洞有效试验时间100 ms内,实现了Ma=7.0和Ma=9.5超燃冲压发动机的成功点火与稳定燃烧.在Ma=7.0情况下,进气道采用三维压缩,燃烧室入口设计Mach数Ma_c=2.5,壁面压力分布实验结果显示燃烧放热靠近燃烧室扩张段上游;在Ma=9.5情况下,进气道采用二维压缩,燃烧室入口设计Mach数Ma_c=3.5,由于燃烧室流动速度特别高,燃烧放热靠近燃烧室扩张段下游.      

某支板式超音速剪切流燃烧的数值研究

针对某支板火焰稳定结构数值研究了二维超音速流动和燃烧规律,提出不同燃料供给方案,比较了采用全氢气、全甲烷和不同比例的混合燃气等情况下的燃烧性能.结果表明:单一燃料时,氢气超燃性能很好,但会出现热量雍塞,而甲烷无法燃烧,两种混合燃料方案均在燃烧室内出现了稳定的火焰,但氧气消耗率不理想,基于上述结论给出了一些提高超燃性能的改进措施.     

OTTO-Ⅱ燃料液滴的着火简化模型法和数值计算法

OTTO-II燃料系一种液体单元推进剂,目前已在某些特种发动机中予以应用.有关这种燃料的燃烧室设计,作者曾提出过一种计算方法,但在应用该方法前还必须判断燃料液滴是否已经着火.本文即解决这一课题.     

基于N-S方程的支撑机翼高亚声速气动外型设计

相对常规悬臂梁布局飞机，支撑机翼飞机允许有更大的展弦比、更薄的机翼及较小的后掠角，从而可以减小诱导阻力、波阻，并增加层流范围，是未来飞机的一个可供选择方案.文章基于N-S方程对高亚声速支撑机翼构型进行了气动外型设计，在巡航Mach数为0.7，设计升力系数为0.6的条件下，支撑机翼构型相对无支撑构型升阻比仅减小6.3%，而初始无支撑翼身组合体构型相较常规悬臂梁翼身组合体构型最大升阻比提高了约35%，设计结果表明支撑机翼构型是可明显提高飞行性能的未来高亚声速飞机的一种新型外型.文章也对支撑外型、位置参数及机翼内翼下翼面外型修型对支撑机翼构型的干扰影响进行了研究，研究结果表明:支撑上翼面外型、支撑弦长、相对厚度、展向位置、扭转角分布及机翼下翼面外型对支撑机翼构型气动影响较大.      

Simulation Investigation of Millimeter Wave Varactor-tuned Transmission Cavity-stabilized Oscillator

A new circuit configuration for millimeter wave varactor-tuned transmission cavity-stabilized oscillator has been proposed in this paper. Compared to conventional varactor-tuned reflection cavity-stabilized oscillator, in this configuration, a high quality factor transmission cavity directly coupled to varactor diode is employed to improve the performances of the oscillator. The operation frequency of this oscillator can be tuned by varying the resonant frequency of the transmission cavity through changing bias voltage of the varactor diode. An equivalent circuit model for the oscillator has been presented in order to theoretically investigate the performance characteristics of the oscillator. On the basis of this model, electrical tuning characteristics have been studied. Mode jumping phenomena during electrical tuning process have been analyzed for obtaining stable operations of the oscillator. The analytical formulae of quality factor and efficiency have been derived in terms of relevant circuit parameters. Particular emphasis has been paid on several circuit parameters which have a substantial impact on circuit performance. Some design considerations have been pointed out according to the simulation results, which are useful to the design and fabrication of this type of oscillators.     

An investigation on the improved performance of shared cavity optical parametric oscillators

It has been demonstrated that shared cavity optical parametric oscillator (OPO) could improve power stability in comparison with that of coupled cavity OPO. By theoretically calculating the spectral transmissions induced by the etalon effect, it has been found that the shared cavity OPO had much wider transmission bandwidth than that of coupled OPO. The corresponding experimental results agreed with the theoretical analysis. Furthermore, the OPO and fundamental laser resonator have nearly the same longitudinal mode spacing in the shared cavity configuration. The above two factors can account for the improved performance of the shared OPO operation.     

Effect of cavity location on combustion flow field of integrated hypersonic vehicle in near space

Abstract  

The cavity has been widely employed as the flame holder to prolong the residence time of fuel in supersonic flows since it improves the combustion efficiency in the scramjet combustor, and also imposes additional drag on the engine. In this paper, the two-dimensional coupled implicit Reynolds Average Navier–Stokes equations, the RNG k–ε turbulence model and the finite-rate/eddy-dissipation reaction model have been employed to numerically simulate the combustion flow field of an integrated hypersonic vehicle. The effect of cavity location on the combustion flow field of the vehicle has been investigated, and the fuel, namely hydrogen, was injected upstream of the cavity on the walls of the first stage combustor. The obtained results show that the viscous lift force, drag force and pitching moment of the vehicle are nearly unchanged by varying the cavity location over the location range and designs considered in this article, namely the configurations with single cavity, double cavities in tandem and double cavities in parallel. The variation of the fuel injection strategy affects the separation of the boundary layer, and the viscous effect on the drag force of the vehicle is remarkable, but the viscous effects on the lift force and the pitching moment are both small and they can be neglected in the design process of hypersonic vehicles. In addition to varying the location of the cavities, three fuel injection configurations were considered. It was found that one particular case can restrict the inlet unstart for the scramjet engine.     

Investigation on the flameholding mechanisms in supersonic flows: backward-facing step and cavity flameholder

Abstract  

As effective devices to extend the fuel residence time in supersonic flow and prolong the duration time for hypersonic vehicles cruising in the near-space with power, the backward-facing step and the cavity are widely employed in hypersonic airbreathing propulsive systems as flameholders. The two-dimensional coupled implicit RANS equations, the standard k-ε turbulence model, and the finite-rate/eddy-dissipation reaction model have been used to generate the flow field structures in the scramjet combustors with the backward-facing step and the cavity flameholders. The flameholding mechanism in the combustor has been investigated by comparing the flow field in the corner region of the backward-facing step with that around the cavity flameholder. The obtained results show that the numerical simulation results are in good agreement with the experimental data, and the different grid scales make only a slight difference to the numerical results. The vortices formed in the corner region of the backward-facing step, in the cavity and upstream of the fuel injector make a large difference to the enhancement of the mixing between the fuel and the free airstream, and they can prolong the residence time of the mixture and improve the combustion efficiency in the supersonic flow. The size of the recirculation zone in the scramjet combustor partially depends on the distance between the injection and the leading edge of the cavity. Further, the shock waves in the scramjet combustor with the cavity flameholder are much stronger than those that occur in the scramjet combustor with the backward-facing step, and this causes a large increase in the static pressure along the walls of the combustor.     

Recent advances in single-chamber fuel-cells: Experiment and modeling

Single-chamber fuel cells (SCFC) are ones in which the fuel and oxidizer are premixed, and selective electrode catalysts are used to generate the oxygen partial pressure gradient that in a conventional dual-chamber design is produced by physical separation of the fuel and oxidizer streams. SCFCs have been shown capable of generating power densities above 700 mW/cm² with appropriate catalysts, making them potentially useful in many applications where the simplicity of a single gas chamber and absence of seals offsets the expected lower efficiency of SCFCs compared to dual-chamber SOFCs.SCFC performance is found to depend sensitively on cell microstructure, geometry, and flow conditions, making experimental optimization tedious. In this paper, we describe recent work focused on developing a quantitative understanding the physical processes responsible for SCFC performance, and the development of an experimentally-validated, physically-based numerical model to allow more rational design and optimization of SCFCs. The use of the model to explore the effects of fuel/oxidizer ratio, anode thickness, and flow configuration is discussed.     

Experimental study of a high-power CW side-pumped Nd:YAG laser

The paper reports on the characterization of a side-pumped 40 W CW Nd:YAG laser. A side-pumping configuration with six laser diodes is used for the laser. We show the comparison between the calculated and measured pump energy distributions in the laser crystal. The birefringence and the thermal lens effect of the Nd:YAG crystal have been experimentally investigated, and their influence on the performance of the laser are discussed. Output power and beam quality of the laser under different output couplings, cavity lengths, types of cavity and different temperatures of the cooling water have been experimentally studied.     

质子交换膜燃料电池及其发电系统模拟

本文通过质子交换膜燃料电池单电池子模型、布气管子模型、流场子模型相互耦合,对电池堆传热传质过程加以数值模拟,得到单电池及电池堆的流场、温场、当地电流密度分布、过电位分布;给定平均电流密度下单电池及电池堆输出电压等参数;并比较了平均电流密度、布气管尺寸对电池输出电压、堆内反应物分配的影响;在此基础上,对整个ＰＥＭＦＣ发电系统进行流程模拟和参数分析,得到平均电流密度、重整器Ｓ／Ｃ等主要参数对系统性能影响．