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禹进,余彬彬,于佳佳.RP-3航空煤油综合替代燃料模型构建[J].航空动力学报,2020,(4):673~681
RP-3航空煤油综合替代燃料模型构建
Development of comprehensive surrogate fuel model for RP-3 aviation kerosene
投稿时间:2019-10-30  
DOI:10.13224/j.cnki.jasp.2020.04.001
中文关键词:  RP-3航空煤油  再生冷却  替代燃料  化学反应机理  官能团
英文关键词:RP-3 aviation kerosene  regenerative cooling  surrogate fuel  chemical reaction mechanism  functional group
基金项目:重庆市自然科学基金面上项目(cstc2019jcyj-msxmX0590); 重庆市教委科学技术研究项目(KJQN201800735)
作者单位
禹进 School of Mechatronics and Automobile Engineering,Chongqing Jiaotong Univeristiy,Chongqing 400074,China
 
余彬彬 Department of Oil,Army Logistics University of the People's Liberation Army of China,Chongqing 401331,China
 
于佳佳 School of Energy and Power Engineering,Chongqing University,Chongqing 400044,China 
摘要点击次数: 152
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中文摘要:
      基于直接匹配分子结构和官能基团的思路,选取正十二烷、2,5-二甲基己烷、1,3,5-三甲基苯和十氢化萘作为基础燃料,为RP-3航空煤油构建了替代燃料模型。物理替代验证表明该替代燃料模型能很好地反映RP-3航空煤油在亚临界到超临界状态下的主要物理性质。利用所构建的替代燃料简化机理验证了其化学替代性能,结果表明:该模型不仅在高温区和低温区都能与着火延迟时间的实验值良好吻合,而且也能够良好反映燃料的在低压条件下(0.1~0.01 MPa)的着火延迟现象。模拟的物性参数和着火延迟时间与实验值的良好吻合证明了该替代燃料能同时实现物理替代和化学替代,为深刻认识超燃冲压发动机中燃料再生冷却与燃烧过程耦合机理,实现航空发动机再生冷却系统和推进动力系统等多部件联合仿真奠定基础。
英文摘要:
      A comprehensive surrogate of RP-3 fuel was developed by the methodology of directly matching the molecular structure and functional groups. n-dodecane, 2,5-dimethylhexane, 1,3,5-trimethylbenzene and decalin were selected as the surrogate components. The physical surrogate model can well predict the main physical properties of RP-3 aviation kerosene from subcritical to supercritical pressures. Besides, the performances of chemical surrogate fuel were also validated against experimental data. Present surrogate fuel model was in good agreement with the experimental ignition delay times both at low and high temperature regions. In addition, present surrogate fuel could also well reflect the ignition delay time at low pressures (0.1-0.01 MPa). Results showed that present surrogate fuels could emulate both the physical and kinetic properties well. The success of present surrogate fuel lays a foundation for understanding of the coupling mechanism of fuel regenerative cooling process and combustion process, and achieving co-simulation of aero-engine regenerative cooling system and propulsion power system in scramjet.
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