摘要
在来流温度773~1 073K、来流马赫数0.20~0.32及常压条件下,试验研究了来流温度及马赫数对一体化凹腔支板稳定器(ICBSF)贫油熄火(LBO)性能的影响。结果表明:由于凹腔结构有利于燃油的蒸发与雾化,一体化凹腔支板稳定器的贫油熄火油气比为0.001 3~0.002 7,具有较宽的贫油熄火边界;与传统钝体火焰器类似,一体化支板稳定器的贫熄油气比随着来流马赫数的增加而增大,随着来流温度的升高而减小。此外,当来流温度显著增高时,来流马赫数对一体化支板稳定器贫油熄火油气比的影响变弱;同样,当来流马赫数显著增高时,来流温度的影响也变弱。
The incoming air temperature was within the range of 773-1 073 K.The incoming flow Mach number ranged from 0.20-0.32.The results showed that,the lean blow-off(LBO)fuel/air ratio of integrated cavity-based strut flameholder(ICBSF)was within the range of 0.001 3-0.002 7 and had a wide lean blow-off limit because of the cavity structure favorable for evaporation and atomization of fuel.LBO fuel/air ratio of ICBSF increased with the increase of incoming flow Mach number and decreased with the increase of flow temperature,similar to that of conventional bluff-body stabilizers.When the temperature of incoming flow was significantly increased,the influence of the incoming Mach number on fuel/air ratio of ICBSF was weakened;similarly,when the incoming Mach number was significantly increased,the influence of the inflow temperature was also weakened.
作者
刘玉英
周春阳
谢奕
刘广海
LIU Yuying;ZHOU Chunyang;XIE Yi;LIU Guanghai(School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2020年第1期75-80,共6页
Journal of Aerospace Power
关键词
加力燃烧室
一体化凹腔支板稳定器
贫油熄火
熄火油气比
燃烧试验
afterburner
integrated cavity-based strut flameholder
lean blow-off
blow-off fuel/air ratio
combustion experiment
