CAJ | 학술논문

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ReaxGen,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.
통과대RP-3항공매유성분적분석,이급대8조체대모형적대비실험,선취료73.0%(질량분수)정십이완, 14.7%1,3,5-삼갑기배기완, 12.3%정병기분작위RP-3항공매유적체대모형.사용본과제조자주연발적궤리자동생성정서ReaxGen,구건료RP-3체대연료적고온연소상세궤리,용해궤리모의료격파관점화연시,병여실험수거진행비교.용물질산솔분석화근사궤적우화산법(ATOA)간화방법간화료상세궤리.최후대연소궤리재불동화학계량비급압력조건하적점화연시주료민감도분석,고찰료연소궤리재불동화학계량비하관건반응적이동.결과표명,해체대모형적연소궤리능흔호지묘술RP-3매유적고온점화특성.
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. Final y, 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.