Ignition and combustion characteristics of supersonic combustor under flight Mach number 2.6–3.8
J Li, K Wang, G Jiao, Z Liao, W Song - Fuel, 2021 - Elsevier
This paper simulated the flying conditions of flight Mach number 2.6~ 3.8. Under the inflow
state of the total temperature of 507 K~ 820 K, the ignition test under low total temperature …
state of the total temperature of 507 K~ 820 K, the ignition test under low total temperature …
基于双向耦合的燃烧室与冷却通道的传热研究
赵超凡， 董昊， 朱剑琴， 程泽源， 戎毅 - 北京航空航天大学学报, 2022 - bhxb.buaa.edu.cn
为研究超燃冲压发动机燃烧室与再生冷却通道的耦合传热特性, 采用双向弱耦合迭代计算方法,
研究燃烧室和冷却通道的特征参数对耦合传热特性的影响规律. 结果表明 …
研究燃烧室和冷却通道的特征参数对耦合传热特性的影响规律. 结果表明 …
Study on heat transfer of combustor and regenerative cooling channel based on two-way coupling
C ZHAO, H DONG, J ZHU, Z CHENG… - 北京航空航天大学 …, 2022 - bhxb.buaa.edu.cn
In order to investigate the heat transfer characteristics of regenerative cooling channels and
scramjet combustors, a two-way weak-coupling iterative calculation method is adopted. The …
scramjet combustors, a two-way weak-coupling iterative calculation method is adopted. The …