超燃冲压发动机中不同燃烧模态下乙烯燃烧释热的敏感因素  

Sensitive factors of ethylene combustion heat release under different combustion modes in scramjet engine

作　　者：李凡 刘铭江 孙明波[1] 赵国焱[1] 马光伟 赵晨翔 LI Fan;LIU Mingjiang;SUN Mingbo;ZHAO Guoyan;MA Guangwei;ZHAO Chenxiang(Laboratory of Science and Technology on Scramjet,College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院高超声速冲压发动机技术重点实验室,长沙410073

出　　处：《航空学报》2025年第4期94-106,共13页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11925207,92252206);湖南省自然科学基金(2023JJ30624);湖南省研究生创新基金(CX20220028)。

摘　　要：在马赫数2.52、总压1.34 MPa和总温1650 K的超声速来流条件下,对超燃冲压发动机燃烧室中乙烯燃烧释热的敏感因素开展实验研究。系统分析和对比了发动机中隔离段长度、喷注距离、凹腔深度、喉部大小等关键构型参数对乙烯燃烧释热的影响,结果表明乙烯燃烧释热对构型参数的敏感度与燃烧模态紧密相关。当燃烧处于纯超燃模态时,燃烧释热对构型参数的变化不敏感,而当燃烧处于双模态超燃(超燃模态)时则相反,之后随着当量比增加,燃烧逐渐过渡为双模态亚燃(亚燃模态)时,燃烧释热对构型参数变化的敏感度逐渐下降。总的来说,不同构型参数对燃烧释热的影响程度从高到低依次是喉部大小>隔离段长度>喷注距离>凹腔深度。An experimental study is conducted to investigate the sensitive factors affecting ethylene combus⁃tion heat release in a scramjet combustion under supersonic flow conditions with of Mach number 2.52,total pressure 1.34 MPa and total temperature 1650 K.The effects of key configuration parameters such as the isolator length,injection distance,cavity depth,and throat size on the ethylene combustion heat release are systematically analyzed and compared.The results show that the sensitivity of ethylene combustion heat release to configuration pa⁃rameters is closely related to the combustion mode.When the combustion is in the completely scramjet mode,the combustion heat release is insensitive to changes in configuration parameters,while the opposite is true when the combustion is in the dual-mode scramjet operation(scramjet mode).Later,as the equivalence ratio increases,the combustion gradually transitions to the dual-mode ramjet operation(ramjet mode),and the sensitivity of the heat re⁃lease to changes in configuration parameters gradually decreases.Overall,the order of the influence of different con⁃figuration parameters on combustion heat release from high to low is as follows:throat size>isolator length>injection distance>cavity depth.

关 键 词：超燃冲压发动机 凹腔 超声速流动 燃烧释热 燃烧模态 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]