摘要
在常温常压进口条件下开展点火试验,研究对象为多级旋流空气雾化喷嘴模型燃烧室,在火焰筒压降为1%~6%工况下分别采用20J和12J点火能量的电火花点火器进行点火试验,控制预燃区补氧空气流量比在0~0.04范围内,研究了多级旋流空气雾化喷嘴的点火油气比变化规律.结果表明：在点火油气比足够小的情况下,预燃区补氧流量越高,临界进口速度越大;在相同点火能量和火焰筒压降下,预燃区补氧空气流量比越高,点火油气比越小;随着预燃区补氧空气流量比增大到一个阈值（20J点火能量时为0.01,12J点火能量时为0.015）,点火油气比曲线的发展趋势将发生变化;当预燃区补氧空气流量比继续增大到另一个关键阈值（20J点火能量时为0.025,12J点火能量时为0.03）,点火油气比不再发生明显改变.
The ignition experiments were conducted on atmospheric pressure and normal temperature.The experimental research object was a model combustor with multi-swirl air atomizing nozzle.The systematic parameters for study consist of atmospheric pressure,normal temperature,pressure drop of chamber of 1%-6%,ignition energy of 20Jand 12J, mass flow ratios of oxygen and air in pilot zone of 0-0.04.The change rule of ignition fuelair ratio of multi-swirl air atomizing nozzle.The results indicate that when ignition fuel-air ratio is small enough,maximum ignition air flow velocity at combustor inlet increases with the rising oxygen addition mass flow in pilot zone.On the condition of the same ignition energy and pressure drop of chamber,while the mass flow ratio of oxygen and air in pilot zone increases,the ignition fuel-air ratio reduces.When the mass flow ratio of oxygen and air in pilot zone increases to a threshold value（20J-0.01,12J-0.015）,the trend of ignition fuel-air ratio of curve changes.When it continues rising to another threshold value（20J-0.025,12J-0.03）,the ignition fuel-air ratio will not change.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2014年第5期1086-1090,共5页
Journal of Aerospace Power
关键词
燃烧室
点火
多级旋流
预燃区
补氧
临界进口速度
油气比
combustor
ignition
multi-swirl
pilot zone
oxygen addition
maximum ignition air flow velocity at combustor inlet
fuel-air ratio
