EXPERIMENTAL INVESTIGATION ON THE REGIMES OF HYDROCARBON SUPERSONIC COMBUSTION
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摘要: 高保真度空天发动机数值模拟通常基于快速化学反应火焰面假设, 即超声速燃烧反应的特征尺度小于湍流Kolmgorov尺度, 该模型方法对于氢气燃料仿真计算结果较好, 但对于乙烯等碳氢燃料仍需进一步研究. 受限于极端环境特种非接触测量技术, 目前尚未见超声速燃烧火焰分区判别的实验研究, 导致目前超声速燃烧火焰面模型适用性以及分区燃烧物理模型认识不清, 进而也制约了数值发动机技术发展. 本工作基于自主研发的MHz发动机内窥光纤传感器, 针对单边扩张双模态冲压发动机超声速燃烧火焰分区开展实验研究, 通过化学自发光信号的最小香农熵定义超声速燃烧的特征时间
${\tau _{sc}}$ , 根据理论方法和来流工况估算了超声速燃烧的流动特征时间, 结合分区燃烧理论分析了双模态超燃冲压发动机内碳氢燃料燃烧的分区情况. 通过燃烧分区情况以及与泰勒尺度的比较结果, 验证了碳氢燃料超燃冲压发动机典型飞行条件下燃烧室内超声速燃烧处于旋涡小火焰区域(Re$ \cong $ 50000; Da∈1.80~2.60, B区 ), 多尺度湍流涡结构发挥重要作用, 并随着相对于泰勒尺度的不同大小, 分别对应了不同尺度的涡结构主导该过程. 同时给出了当量比、通量比以及来流马赫数对燃烧特征时间的影响规律. 实验发现, 在一定范围内随着当量比增加燃烧逐渐增强, 并且增强效果明显强于通量比的影响; 而通量比的变化会使得燃烧出现分岔等情况; 来流马赫数的变化对于燃烧的影响效果更为明显, 也表明了宽域来流影响作用机制是未来宽域湍流燃烧理论研究的重要方向.Abstract: Numerical simulations of high-fidelity aerospace engines are usually based on the rapid chemical reaction flame surface assumption, that is, the characteristic scale of supersonic combustion reaction is smaller than the turbulent Kolmogorov scale. This model method has good simulation results for hydrogen fuel, but further research is needed for hydrocarbon fuels such as ethylene. Limited by the extreme environment special nonintrusive measurement techniques, experimental investigations on the discrimination of supersonic combustion flame mode have not been presented in literature. The applicability of the supersonic combustion flame surface model and understandings of the regimes of supersonic combustion restricts the development of high fidelity numerical simulation methods. Based on the in house designed MHz endoscope optical fiber sensor, experiments are designed to study the regimes of supersonic combustion of a dual-mode scramjet combustor. The minimum Shannon entropy of the chemiluminescence signal is used to define the characteristic time of supersonic combustion. The flow characteristic time of supersonic combustion is estimated according to the theoretical method and the incoming flow conditions. Combined with the partition combustion theory, the partition situation of hydrocarbon fuel combustion in a dual-mode scramjet is analyzed. Through combustion zoning and comparison with Taylor scale .The data presented in this paper suggests the supersonic combustion in the vortex framelet regime in a typical flight envelope (Re$\cong $ 50000; Da∈1.80-2.60, B zone), suggesting the strong influence of turbulence,With different sizes relative to the Taylor scale, vortex structures corresponding to different scales dominate the process. In addition, parametric evaluation on the influence of equivalence ratio, flux ratio and Mach number during a simulated acceleration is presented in this paper. The experiment found that the combustion gradually increased with the increase of the equivalence ratio within a certain range, and the enhancement effect was obviously stronger than that of the flux ratio; the change of the flux ratio would cause the combustion to bifurcate; the change of the incoming Mach number was important for The effect of combustion is more obvious, and it also shows that the effect mechanism of incoming flow is an important direction for future research on turbulent combustion theory. -
图 2 直连式超声速燃烧实验台示意图
Figure 2. Schematic diagram of direct connected supersonic combustion test bench
图 3 当量比变化时沿程压力分布
Figure 3. Pressure distribution along the model of different stoichiometric ratios
图 4 当量比变化时一维沿程马赫数分布
Figure 4. One-dimensional Mach number distribution along model of different stoichiometric ratios
图 5 动量通量比变化时沿程压力分布
Figure 5. Pressure distribution along the model of different momentum flux ratios
图 6 动量通量比变化时一维沿程马赫数分布
Figure 6. One-dimensional Mach number distribution along model of different momentum flux ratios
图 7 加速上行飞行轨迹沿程压力分布
Figure 7. Pressure distribution along the model of acceleration experiment
图 8 加速上行飞行轨迹一维沿程马赫数分布
Figure 8. One-dimensional Mach number distribution along the model of acceleration experiment
图 9 被动式内窥镜火焰传感器测试系统示意图
Figure 9. Schematic diagram of passive endoscope flame sensor test system
图 13 工况1中P1测点自发光
$\rm C{H^*}$ 信号Figure 13. Self-luminous
$\rm C{H^*}$ signal of P1 point in experimental condition 1
图 14
$ N = 2 $ 时$\rm C{H^*}$ 信号离散化示意图Figure 14.
$\rm C{H^*}$ signal discretization diagram when$ N = 2 $ 
图 15
$T{\text{ = }}5\;{\rm{ ms}}$ 时工况1下 P1测点测得的香农熵Figure 15. Shannon entropy measured at P1 point under experimental condition 1 when
$T{\text{ = }}5\;{\rm{ ms}}$ 
图 17 采样时长敏感性变化的标准差分析
Figure 17. Standard deviation analysis of sensitivity variation in sampling duration
图 19 工况1下不同测点燃烧特征时间
Figure 19. Combustion characteristic time of different points under condition 1
图 20 工况1下不同测点燃烧特征时间标准差
Figure 20. Combustion characteristic time standard deviation at different points under condition 1
图 21 不同当量比下火焰质心分布
Figure 21. Flame centroid distribution of different stoichiometric ratios
图 22 不同当量比下燃烧特征时间
Figure 22. Combustion characteristic time of different stoichiometric ratios
图 23 不同当量比下燃烧特征时间标准差
Figure 23. Combustion characteristic time standard deviation of different stoichiometric ratios
图 24 不同通量比下火焰质心位置分布
Figure 24. Distribution of flame centroid positions with different momentum flux ratios
图 25 不同通量比下燃烧特征时间
Figure 25. Combustion characteristic time of different momentum flux ratios
图 26 不同通量比下燃烧特征时间标准差
Figure 26. Combustion characteristic time standard deviation of different momentum flux ratios
图 27 加速上行实验火焰质心的分布
Figure 27. Distribution of flame centroid positions with acceleration
图 28 加速上行实验不同测点的燃烧特征时间
Figure 28. Combustion characteristic time of different points under acceleration experiment
图 29 加速上行实验不同测点燃烧特征时间标准差
Figure 29. Combustion characteristic time standard deviation at different points under acceleration experiment
图 31 全部工况的
$Da$ 概率密度分布Figure 31.
$Da$ probability density distribution of all experiment conditions表 1 实验工况
Table 1. Experimental conditions
Number Ф J Ma 1 0.10 2.94 2.8 2 0.13 3.82 2.8 3 0.17 4.92 2.8 4 0.17 5.04 2.8 5 0.17 4.01 2.8 6 0.10~0.17 3.27~4.47 2.5~3.0 
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