RP-3替代燃料自点火燃烧机理构建及动力学模拟

Construction of Autoignition Mechanisms for the Combustion of RP-3 Surrogate Fuel and Kinetics Simulation

通过对RP-3航空煤油成分的分析,以及对8组替代模型的对比实验,选取了73.0%(质量分数)正十二烷,14.7%1,3,5-三甲基环己烷,12.3%正丙基苯作为RP-3航空煤油的替代模型.使用本课题组自主研发的机理自动生成程序Reax Gen,构建了RP-3替代燃料的高温燃烧详细机理,用该机理模拟了激波管点火延时,并与实验数据进行比较.用物质产率分析和近似轨迹优化算法(ATOA)简化方法简化了详细机理.最后对燃烧机理在不同化学计量比及压力条件下的点火延时做了敏感度分析,考察了燃烧机理在不同化学计量比下关键反应的异同.结果表明,该替代模型的燃烧机理能很好地描述RP-3煤油的高温点火特性.

According to a component analysis of RP-3 aviation kerosene and eight surrogate models＇ comparative data, a surrogate model comprising n-dodecane/1,3,5-trimethylcyclohecane/n-propylbenzene （73.0%/14.7%/12.3%, mass fraction） was obtained. A detailed mechanism for the combustion of RP-3 surrogate fuel at high temperature was developed using an automatic generation software package, ReaxGen. Ignition delay times simulated using this mechanism were compared with experimental data. A detailed mechanism was reduced by adopting rate-of-production analysis and approximate trajectory optimization algorithm （ATOA） reduced methods. Finally, the sensitivity of ignition delay time was analyzed under conditions of different equivalent ratios and pressures using the reduced mechanism. Differences in key reactions contributing to the ignition delay time were identified at different equivalent ratios. The results indicate that our mechanisms can characterize the ignition delay time during combustion of RP-3 kerosene at high temperature.