摘要
为研究燃油喷雾特性对某小发环形回流燃烧室主燃区燃烧特性的影响,采用数值模拟的方法,对环涡形燃烧室内燃油喷嘴伸入火焰筒的深度和喷雾偏转角度对燃烧室内的三维两相喷雾、燃烧特性进行了研究。结果表明:喷嘴位置和角度的变化,会导致燃油雾化性能的变化,从而引起燃烧特性的变化;随着喷嘴伸入火焰筒的深度变短,会导致高温区变窄且靠近火焰筒外壁,深度变长则会导致主燃区高温区减小且燃烧不充分;喷雾偏转角度顺时针旋转可使燃油在主燃区燃烧得更加充分。
In order to study the effect of fuel spray on the combustion characteristics of primary combustion zone of a small engine annular reverse flow combustor,numerical simulation method was used to study the three-dimensional two-phase spray and combustion characteristics of the annular reverse flow combustor by the insertion depth of the nozzle into the flame tube and spray deflection angle in the combustor.The results showed that:the change of nozzle position and angle caused the change of fuel atomization performance,which caused the change of combustion characteristics;as the depth of nozzle extending into the flame tube became shorter,it could make the high temperature zone narrow and close to the outer wall of the flame tube.The longer depth could lead to reduction of the high temperature zone of primary combustion zone and insufficient combustion;the clockwise rotation of the spray deflection angle can make the fuel burning more fully in the primary combustion zone.
作者
杨宇东
刘爱虢
王鑫慈
惠蕾
陈雷
YANG Yudong;LIU Aiguo;WANG Xinci;XI Lei;CHEN Lei(Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System,School of Aero-Engine,Shenyang Aerospace University,Shenyang 110136,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2023年第4期830-839,共10页
Journal of Aerospace Power
基金
辽宁省自然科学基金(20180550358)
航空科学基金(20170354001)。
关键词
小型航空发动机
燃油喷雾方向
环形回流燃烧室
两相喷雾燃烧
燃烧特性
small aeroengine
fuel spray direction
annular reverse flow combustor
two-phase spray combustion
combustion characteristic