航空学报2025，Vol.46Issue(8)：21-53,33.DOI:10.7527/S1000-6893.2024.31189
高超声速进气道预喷注技术研究进展与关键问题
Research progress and key issues of inlet pre-injection at hypersonic condition
摘要
Abstract
Air-breathing hypersonic propulsion technology is a core foundation for the of hypersonic vehicles develop-ment.As the flight Mach number of hypersonic vehicles continues to increase,the internal flow of air-breathing hyper-sonic engine faces extreme conditions such as high enthalpy,high velocity,and extremely short residence times.These conditions present significant challenges in combustion organization,performance improvement,and upper flight Mach number extension.Inlet pre-injection,as a novel active fuel injection and mixing enhancement technology,has been proposed and introduced into hypersonic propulsion systems.It provides a new potential controllable factor for the internal flow and combustion organization,performance matching and control,and integrated design optimiza-tion of higher Mach number engines,and has garnered attention and research interests in the field.Considering the needs for high Mach number hypersonic propulsion,this paper systematically reviews and analyzes the research prog-ress and key issues of hypersonic inlet pre-injection technology.First,the concept of hypersonic inlet pre-injection is introduced,and the basic aerodynamic and thermodynamic processes and coupling effects are analyzed.Second,a brief overview of the research status of high Mach number engines is provided,highlighting the key development direc-tions and their common requirements for inlet pre-injection.Then,the fundamental understanding of supersonic inflow injection and mixing is summarized,pointing out the current lack of comprehensive understanding of injection and mix-ing under complex hypersonic inflow conditions.Finally,the research progress on hypersonic inlet pre-injection at home and abroad is systematically summarized,with a discussion and analysis of the main key issues that need to be addressed.The research prospects and suggestions are proposed to promote the application and development of inlet pre-injection technology in high Mach number hypersonic propulsion systems.关键词
高超声速推进/超燃冲压发动机/斜爆震发动机/进气道/预喷注/燃料掺混Key words
hypersonic propulsion/scramjet engine/oblique detonation engine/inlet/pre-injection/fuel mixing分类
航空航天引用本文复制引用
罗飞腾,杨甫江,程强,孔武斌,渠镇铭,李海涛,李新珂,姚达豪,陈文娟,龙垚松,韦宝禧,满延进..高超声速进气道预喷注技术研究进展与关键问题[J].航空学报,2025,46(8):21-53,33.基金项目
冲压发动机技术全国重点实验室基金(WDZC6142703202202) （WDZC6142703202202）
