煤油燃料超燃发动机燃烧室温度测量与计算分析  

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

作　　者：晏至辉[1] 肖保国[1] 何粲[1] 刘彧 李国华[2] 叶景峰[2] YAN Zhihui;XIAO Baoguo;HE Can;LIU Yu;LI Guohua;YE Jingfeng(Science and Technology on Scramjet Laboratory,Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China;State Key Laboratory of Laser Interaction with Matter,Northwest Institute of Nuclear Technology,Xi'an 710024,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室,四川绵阳621000 [2]西北核技术研究所激光与物质相互作用国家重点实验室,西安710024

出　　处：《航空动力学报》2019年第3期521-528,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(91641126;91441204)

摘　　要：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1 100K,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。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 1100 Kand stagnation pressure 1.0 MPa.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 40 K and 150 Kbelow the simulated values,respectively and the relative errors were 4.2% and13%,respectively.In the recirculation flow of the cavity,the measured temperature was 140 K below the simulated value at equivalence ratio of 0.6,with a relative error of 11.7% and170 Kbelow 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.

关 键 词：超燃发动机 温度测量 相干反斯托克斯拉曼散射 并行计算 煤油燃料 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]