摘要
本文采用热力学分析方法，从熵和的概念出发，论证了理想情况下爆轰发动机的有效性，并定量比较了在同样入口压缩条件下，采用爆轰、等压、等Ｍ数等三种燃烧模式的发动机的性能，证明Ｃ─Ｊ斜爆轰是最佳超声速燃烧模式。
This paper attempts to demonstrate universally that the C-Joblique detonation is the most efficient supersonic combustion modes amongall non-convergent area supersonic combustion modes. The parameters comp-ared here are the total pressure, entropy and Exergy (availability) atcombustor outlets. Finally, as an example, the propulsive efficiency,specific impulse (hydrogen feul) and the temperature at the nozzle outletof an idealized, integrated and geometry fixed Scramjet are comparedamong C-J ODW, dp=0 and dM=0 supersonic combustion modes versusflight Mach numbers. The results show that the performance of C-J ODWmodes is the best. The temperature of ODW modes at the nozzle outletis the lowest.
出处
《空气动力学学报》
CSCD
北大核心
1995年第1期48-56,共9页
Acta Aerodynamica Sinica
基金
国家自然科学基金
关键词
斜爆轰波
超声速燃烧
航空发动机
热力循环
oblique detonation wave,supersonic combustion,airbreathing engine,thermodynamic cycle.
