Spray Combustion Dynamics in A Supersonic Propulsion System
The purpose of this research is to investigate the spray combustion dynamics in an axisymmetric supersonic propulsion system. The combustion dynamics of the system is related to interactions between inlet terminal shock oscillation and flame oscillation which significantly affects engine performance, since the entire supersonic propulsion system has no mechanical component to compensate oscillatory pressure and acoustic waves occurred in the system. Therefore, a unified numerical analysis from intake to exhaust nozzle was conducted. Two flight conditions such as low altitude and high altitude are concerned. The detail flow structures such as shock train, shock/boundary layer interaction, and flame fluctuation are observed. To calculate the governing equations within reasonable computing time in engineering sense, parallel computing scheme using MPI (Massage Passing Interface) library is implemented.
supersonic propulsion system combustion dynamics a unified numerical analysis spray combustion
Kim Seongjin Yeom Hyowon Sung Honggye
School of Space Technology Korea Aerospace University, Gyeonggi-do, 412 - 791,Republic of Korea School of Aerospace and Mechanical Engineering Korea Aerospace University,Gyeonggi-do, 412-791, Repu
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
1123-1126
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）