凹腔支板火焰稳定器自燃点火性能初步试验  

Preliminary experiment on spontaneous ignition performances of cavity-based strut flameholder

作　　者：刘玉英[1] 谢奕[1] 柳杨[1] 金捷[1] LIU Yuying;XIE Yi;LIU Yang;JIN Jie(School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空动力学报》2018年第6期1298-1304,共7页Journal of Aerospace Power

基　　金：航空科学基金(2013ZB51014)

摘　　要：以凹腔支板火焰稳定器为研究对象,在进口温度为750~900℃、马赫数为0.20~0.28、氧气体积分数为13.4%~15.8%、喷嘴距支板前缘5~50mm及常压的条件下,开展自燃点火性能的试验研究。试验表明:凹腔支板火焰稳定器在进口温度为850℃以上可成功实现自燃点火。自燃点火性能随进口温度的升高而提高;随着进口马赫数的提高,火焰稳定器自燃点火成功的温度范围越窄;随着燃油喷射距离的增大,稳定器自燃点火性能有所提高。稳定器的凹腔结构能够稳定火焰。The spontaneous ignition performances of a cavity-based strut flameholder were preliminarily investigated with spray distances of 5-50 mm at atmospheric pressure,the air temperature and oxygen volume fraction were within the range of 750-900℃ and 13.4%-15.8%,Mach number ranged from 0.20-0.28.Results showed that the flameholder could be autoignited when the inlet temperature was above 850℃.As the inlet temperature increased,the performances of spontaneous ignition improved.When the inlet Mach number became larger,the temperature range for successful spontaneous ignition became narrower.With the increase of fuel injection distance,the autoignition performances of the stabilizer were improved.The cavity structure of the stabilizer could stabilize the flame.

关 键 词：自燃 点火 支板火焰稳定器 钝体 凹腔 

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]