【作者】 范学军； 仲峰泉； 王晶； 俞刚； 李建国；

【Author】 Xuejun Fan,Fengquan Zhong,Jing Wang,Gang Yu,and Jianguo Li (Institute of Mechanics,Chinese Academy of Sciences,15 Beisihuanxi Road,Beijing,100190,China)

【机构】 中国科学院力学研究所；

【摘要】 本文针对单路燃料喷注在当量比较高时容易引起边界层分离,从而导致燃烧静压向上游迅速传播这一问题,分别采用马赫数2.5与3.0超声速模型燃烧室,开展了一系列超临界态煤油喷注的超声速燃烧特性研究,并针对不同的燃料流量、喷油位置、燃烧室入口马赫数等条件,详细比较了单路与双路喷油的超声速燃烧性能,并获得了相应的燃烧室性能优化方法。更多还原

【Abstract】 To avoid the upstream propagation of boundary layer separation due to excessive heat release when a high mass flow of fuel was injected into the supersonic combustor,the concept of two-staged fuel injection has been implemented in the present study.Combustion of supercritical kerosene was experimentally investigated and compared in both Mach 2.5 and Mach 3.0 model combustors.Combustor performances with different fuel mass flow rates,injection locations,and combustor entry Mach numbers were investigated systematically and discussed based on the measured static pressure distributions and the specific thrust increments due to combustion.With two-staged fuel injections the overall performance of the combustors was shown to be improved maximally 23%and fuel injections at equivalence ratio higher than unity could be reached without the upstream propagating of the static pressure rise.更多还原