氢在超音速气流中的燃烧过程  

COMBUSTION PROCESSES OF HYDROGEN IN A SUPERSONIC AIR FLOW

作　　者：杨爱国 刘陵[2] 王宏基[2] 

机构地区：[1]西安航空航天部计算技术研究所 [2]西北工业大学

出　　处：《航空动力学报》1991年第3期271-272,共2页Journal of Aerospace Power

基　　金：国家自然科学基金资助项目

摘　　要：According to the implicit numerical integration method proposed by Tyson.J,an improved computer program for pseudo one dimensional flow of combustion kinetics is developed with the aid of a chemical kinectic model with 12 species and 31 reaction.Variations of temperature,prssure,Mach number and mass fraction of chemical species in a supersonic combustion model are studied in detail.The results of scramjet combustor conditions corresponding to flight Mach numbers 6,10 and 15 show that chemical reaction rates decrease at rather low temperature and pressure at a combustor inlet and there is not enough time to ignite the mixture gas in the combustor at very high Mach number,in result the performance limits of scramjet kinetic combustion occur.According to the implicit numerical integration method proposed by Tyson.J,an improved computer program for pseudo one dimensional flow of combustion kinetics is developed with the aid of a chemical kinectic model with 12 species and 31 reaction.Variations of temperature,prssure,Mach number and mass fraction of chemical species in a supersonic combustion model are studied in detail.The results of scramjet combustor conditions corresponding to flight Mach numbers 6,10 and 15 show that chemical reaction rates decrease at rather low temperature and pressure at a combustor inlet and there is not enough time to ignite the mixture gas in the combustor at very high Mach number,in result the performance limits of scramjet kinetic combustion occur.

关 键 词：氢 超音速流 燃烧过程 航空 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]