CFD Simulation of Kerosene-Fueled Supersonic Combustion Ramjet Combustor Experiments

摘要：

The kerosene-fueled scramjet combustor experiments are numerically simulated, for the purpose of code validation and better understanding of flow structure. Full chemically reacting Navier-Stokes equation is numerically solved, and a global reaction mechanism and a reduced 12 species 12 step reaction mechanism are used for kerosene combustion. Computational results using different level of grid refinement and wall boundary conditions are compared with the experimentally measured data. In addition, computed results with different reaction mechanisms are compared. The computed and experimental results agree well. Three dimensional flow structures of different fuel injection scheme are compared. The results show that the subsonic region of the in-cavity fuel injection is located near the sidewall, whereas for the case with upstream single-hole fuel injection, the subsonic region is located near the symmetry plane.

关键词： kerosene fuel scramjet combustor CFD parallel computation

作者: Wan Tian Chen Lihong Wang Jing Fan Xuejun Chang Xinyu

作者单位: Key Laboratory of High Temperature Gas Dynamics (LHD), Institute of Mechanics,Chinese Academy of Sciences, Beijing, 100190, China

会议类型: 国际会议

会议名称: 2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)

会议地点: 西安

会议语种:英文

页码: 1156-1159

在线出版日期: 2010-09-01（万方平台首次上网日期，不代表论文的发表时间）