Scaling study of the combustion performance of gasben gas rocket injectors

To obtain the key subelements that may influence the scaling of gas-gas injector combustor performance, the combustion performance subelements in a liquid propellant rocket engine combustor are initially analysed based on the results of a previous study on the scaling of a gas-gas combustion flowfield. Analysis indicates that inner wall friction loss and heat-flux loss are two key issues in gaining the scaling criterion of the combustion performance. The similarity conditions of the inner wall friction loss and heat-flux loss in a gas-gas combustion chamber are obtained by theoretical analyses. Then the theoretical scaling criterion was obtained for the combustion performance, but it proved to be impractical. The criterion conditions, the wall friction and the heat flux are further analysed in detail to obtain the specific engineering scaling criterion of the combustion performance. The results indicate that when the inner flowfields in the combustors are similar, the combustor wall shear stress will have similar distributions qualitatively and will be directly proportional to p_c^0.8 d_t^-0.2 quantitatively. In addition, the combustion peformance will remain unchanged. Furthermore, multi-element injector chambers with different geometric sizes and at different pressures are numerically simulated and the wall shear stress and combustion efficiencies are solved and compared with each other. A multi-element injector chamber is designed and hot-fire tested at several chamber pressures and the combustion performances are measured in a total of nine hot-fire tests. The numerical and experimental results verified the similarities among combustor wall shear stress and combustion performances at different chamber pressures and geometries, with the criterion applied.     

高频感应等离子体流动模型与微型电推进器流场特性分析

微型射频离子推力器具有结构简单、工作寿命长、推力动态范围大、性能调节响应灵敏等特点,是国际微电推进领域的研究热点之一.射频离子推力器电离室内的感性耦合放电等离子体特性和推力器的性能密切相关.为此,文章建立了低气压、小尺寸微型射频离子推力器电离室内感性耦合等离子体流体模型,开展了电磁场、流场、化学反应浓度场的多物理场耦合仿真分析,并研究了等离子体放电特征参数随推进剂工质气压、放电吸收功率、射频频率以及线圈匝数等因素的变化规律.结果表明,推进剂工质气压、放电吸收功率是调节微型射频离子推力器性能的主要因素,该研究为综合调控微型射频离子推力器的工作性能奠定了良好的基础.      

Flow characterization and dilution effects of N_2 and CO_2 on premixed CH_4/air flames in a swirl-stabilized combustor

Numerically-aided experimental studies are conducted on a swirl-stabilized combustor to investigate the dilution effects on flame stability, flame structure, and pollutant emissions of premixed CH4/air flames. Our goal is to provide a systematic assessment on combustion characteristics in diluted regimes for its application to environmentally-friendly approaches such as biogas combustion and exhanst-gas recirculation technology. Two main diluting species, N2 and CO2, are tested at various dilution rates. The results obtained by means of optical diagnostics show that five main flame regimes can be observed for Nz-diluted flames by changing excess air and dilution rate. CO2-diluted flames follow the same pattern evolution except that all the domains are shifted to lower excess air. Both N2 and CO2 dilution affect the lean blow- out （LBO） limits negatively. This behavior can be counter-balanced by reactant preheating which is able to broaden the flammability domain of the diluted flames. Flame reactivity is degraded by increasing dilution rate. Meanwhile, flames are thickened in the presence of both diluting species. NOx emissions are significantly reduced with dilution and proved to be relevant to flame stability diagrams： slight augmentation in NOx emission profiles is related to transitional flame states where instability occurs. Although dilution results in increase in CO emissions at certain levels, optimal dilution rates can still be proposed to achieve an ideal compromise.     

双锥/双楔流动中的高温气体效应仿真模拟

在高超声速飞行和再入地球大气过程中, 气体分子的振动、电子态激发, 伴随离解、电离反应, 从而产生高温真实气体效应。不同数值方法对高温真实气体效应的模化会造成气体热物性参数的差异, 从而对流场模拟引入不确定度。以高超声速的双锥/双楔流动为例, 通过计算流体力学方法和直接模拟Monte Carlo (DSMC)方法, 研究高温真实气体模型对复杂干扰流动的预测能力。结果表明, 有别于量热完全气体, 若考虑真实物理过程的热化学非平衡过程带来气体热力学性质、输运特性的变化, 会导致激波角、边界层厚度、分离区尺寸等流动结构的改变。因此, 在研究高超声速模拟中应注意数值模型的正确应用。      

氢、碳氢燃料对向扩散火焰

对氢、正烷烃碳氢燃料与氧的对向扩散火焰,其中正烷烃包含了在工业用燃料中广泛应用的C_nH_2n+2正烷烃CH₄～C1₆H₃₄,对这些燃料的火焰结构进行了分析和比较,系统地分析了压力和拉伸率对火焰行为和热释放率等的影响,其中包含了2115个组分8157个可逆反应．研究结果表明,所有燃料的火焰厚度和热释放率与压力和拉伸率的乘积的平方根成线性关系．在相同工况下,氢的火焰厚度总是大于所有的碳氢燃料,而CH₄～C1₆H₃₄所有的碳氢燃料在相同工况下总是具有几乎相同的燃烧温度分布、燃烧产物分布、火焰厚度和热释放率,该结果表明由这些碳氢燃料组成的混合燃料具有同样的火焰特性.     

电喷雾推力器锥射流形成的电流体力学仿真

以G往关于电喷雾过程仿真研究对象多局限于低电导率液体,而电喷雾推力器使用的工质主要为高电导率离子液体,推力器工作时,离子液体在强电场作用下形成锥形,并在末端发射出锥形等离子体荷电喷雾。但离子液体受空间电荷、液体内部电流及液面电流的影响较大,电流体力学过程更为复杂,相关仿真研究极为匮乏。本文通过加入未简化的电荷守恒方程,考虑空间电荷及电流对锥射流形成与演化的影响,并耦合高斯定律和Navier-Stokes(N-S)方程求解流场及电荷分布,使用volume of fluid(VOF:流体体积)方法追踪液-气界面的变化,对高电导率液体的电喷雾锥射流形成过程开展了仿真研究。本次仿真工作以庚烷为工质模拟了锥射流形成与演化过程,得到电荷、电势和流场的分布,并与未考虑空间电荷的理想电介质模型进行对比。仿真结果表明,在低电导率情况下,本文模型与理想电介质模型的结果相近;高电导率情况下,本文模型得到的结果与相关实验更加吻合。     

氢、碳氢燃料对向扩散火焰

A comprehensive analysis of hydrogen/oxygen and hydrocarbon/oxygen counterflow diffu-sion flames has been conducted using corresponding detailed reaction mechanisms. The hydrocarbon fuels contain n-alkanes from CH₄ to C₁₆H₃₄. The basic diffusion flame struc-tures are demonstrated, analyzed, and compared. The effects of pressure, and strain rate on the flame behavior and energy-release rate for each fuel are examined systematically. The de-tailed chemical kinetic reaction mechanisms from Lawrence Livermore National Laboratory(LLNL) are employed, and the largest one of them contains 2115 species and 8157 reversible reactions. The results indicate for all of the fuels the flame thickness and heat release rate correlate well with the square root of the pressure multiplied by the strain rate. Under the condition of any strain rate and pressure, H₂ has thicker flame than hydrocarbons, while the hydrocarbons have the similar temperature and main products distributions and almost have the same flame thickness and heat release rate. The result indicates that the fuels composed with these hydrocarbons will still have the same flame properties as any pure n-alkane fuel.     

中段弹头表面温度及辐射特性的计算研究

为研究中段弹头的表面温度及辐射特性,利用Lowtran7计算太阳和地球大气的红外与可见光辐射,依据粗糙表面光散射理论计算弹头对太阳、地球大气和地球反照辐射的吸收和散射。采用控制容积法发展了圆柱坐标系下三维非稳态导热的隐式离散方程,迭代求解得到弹头表面的温度。以一射程4000km的中段弹头为例,计算了发动机关机点后2000s内,弹头表面的温度和辐射的变化。     

中段目标的可见光辐射特性计算研究

中段目标的可见光辐射特性对目标的探测、跟踪与打击具有重要的指导意义。提出计算中段目标可见光辐射特性的方法,计算了目标表面的二向性反射,并考虑太阳的可见光辐射和云层背景反射太阳的可见光辐射情况下,计算了白天从同步卫星、低轨卫星和中轨卫星观测中段目标在可见光波段的辐射特性。研究结果表明：在可见光波段,目标对同步卫星辐射的光谱变化规律与太阳直射辐射的光谱变化一致,低轨卫星上观测目标的光谱辐射热流比同步卫星上观测的结果大3个数量级,中轨卫星上观测目标的光谱辐射热流比同步卫星上观测的结果大1个数量级。     

Numerical and experimental study on shear coaxial injectors with hot hydrogen-rich gas/oxygen-rich gas and GH2 /GO2

The influences of the shear coaxial injector parameters on the combustion performance and the heat load of a combustor are studied numerically and experimentally. The injector parameters, including the ratio of the oxidizer pressure drop to the combustor pressure (DP ), the velocity ratio of fuel to oxidizer (R V ), the thickness (WO ), and the recess (HO ) of the oxidizer injector post tip, the temperature of the hydrogen-rich gas (TH ) and the oxygen-rich gas (TO ), are integrated by the orthogonal experimental design method to investigate the performance of the shear coaxial injector. The gaseous hydrogen/oxygen at ambient temperature (GH2 /GO2 ), and the hot hydrogen-rich gas/oxygen-rich gas are used here. The length of the combustion (LC ), the average temperatures of the combustor wall (TW ), and the faceplate (TF ) are selected as the indicators. The tendencies of the influences of injector parameters on the combustion performance and the heat load of the combustor for the GH2 /GO2 case are similar to those in the hot propellants case. However, the combustion performance in the hot propellant case is better than that in the GH2/GO2 case, and the heat load of the combustor is also larger than that in the latter case.