摘要
为研究双模态超燃冲压发动机的燃烧室-隔离段共同工作过程,分析不同模态下燃烧室对隔离段的性能需求,在基于集总参数方程的超燃冲压发动机性能计算模型的基础上,提出计算燃烧室-隔离段流量平衡的临界能量法,并编制相应的计算程序,实现双模态超燃冲压发动机各种模态的隔离段和燃烧室的流量平衡计算,计算在不同的模态下隔离段和燃烧室的一维流动参数,进而获得隔离段的性能需求,计算飞行马赫数4.0到7.0时的临近堵塞边界的最大供油量与隔离段最大激波链长度。结果表明:临界能量法正确有效,能完成燃烧室-隔离段流量匹配计算;高飞行马赫数下的堵塞模态的隔离段激波链长度较长,应作为隔离段的工程设计中所参考的重要因素。
For studying combustor-isolator matching of dual-mode Scramjet and analyzing the performance re- quirement of isolator in different mode, based on lumped parameter equations for performance computation of scramjet, the critical energy method is presented for computation of mass flow balance between isolator and combustor, the computation model of Scramjet is built, and the corresponding computer program is developed, the dual-mode Scramjet performance and mass flow balance in different mode are computed and analyzed, one dimension flow parameters of isolator and combustor are gained and studied in different mode, and the isolator performance requirement of Scramjet are found. The maximum fuel mass flow and isolator separate length near choking margin is computed when flight Mach number Mao ~ 4. O~ 7. O. The computation results show that critical energy method is correct and effective and it can be used for computation of mass flow balance between isolator and combustor, the isolator shock wave chain length is much longer when the Scramjet operates in choking mode at high flight Mach number, and it should be taken into consideration for engineering design of isolator.
出处
《航空工程进展》
2013年第3期369-375,共7页
Advances in Aeronautical Science and Engineering
