煤油燃料超燃发动机燃烧室温度测量与计算分析

为获得超燃冲压发动机燃烧室流场温度分布特性，深入分析发动机工作特性，对马赫数为2.0，总温为1100K，总压为1.0MPa的来流，利用可调谐的相干反斯托克斯拉曼散射（CARS）技术完成了直连式燃烧室流场温度测量；同时对实验状态进行了三维并行数值模拟，对比分析了计算和实验结果的差异。结果表明，隔离段温度的实验测量值与计算结果的最大相对误差约为0.8%；在燃烧室核心流区域，当量比为0.6和0.8两个状态下，实验测量值分别比计算值偏低约40K和150K，相对差异为4.2%和13%；在凹槽回流区内，当量比为0.6和0.8时实验值则分别比计算值偏低约140K和170K，相对差异为11.7%和7.5%。主喷油位置喷入当量比为0.2的燃料对燃烧室区域的温度和压力分布会产生较大影响，但对扩张段及后部区域的推力性能不会产生显著的改变。 

Temperature measurement and calculation analysis in a kerosene-fueled scramjet combustor

In order to obtain temperature distribution of the scramjet combustor and analyze working characteristics of the engine, temperature measurement was conducted via tunable coherent anti-Stokes Raman scattering (CARS) technique in a direct-connect combustor at the inflow Mach number 2.0, stagnation temperature 1100K and stagnation pressure 1.0MPa. Three-dimensional parallel numerical simulation on the experimental condition was carried out to compare the difference between the experimental and numerical results. Results showed that the temperatures of the incoming flow in the isolator obtained in experiment and numerical simulation had a maximum relative error of 0.8%. In the core flow of the combustor, at equivalence ratios of 0.6 and 0.8, the measured temperatures were 40K and 150K below the simulated values, respectively and the relative errors were 4.2% and 13%, respectively. In the recirculation flow of the cavity, the measured temperature was 140K below the simulated value at equivalence ratio of 0.6, with a relative error of 11.7% and 170K below at equivalence of 0.8, with a relative error of 7.5%. Both the numerical simulation and the experiment show that temperature and pressure distributions in the combustor are significantly influenced when the fuel of equivalence ratio of 0.2 is injected at the main fuel injector, but thrust performance of the expansion section and downstream region will not make much difference.