摘要
针对液氧/煤油补燃发动机液膜冷却过程,建立了超临界条件下的液膜冷却模型,分析了冷却环带喷注结构对局部流动和冷却效果的影响.在超临界条件下,煤油和周围燃气为同种流体,用同一组方程来描述其流动与传热过程,对3种典型冷却环喷注结构的流动进行了数值模拟.结果表明:冷却环带的出口角度、台阶结构和喷射角对局部流动和传热有显著影响,出口角度小于90°的台阶式结构可减小局部回流从而有利于推力室的热防护.
A kerosene supercritical film cooling model for the thrust chamber of liquid oxygen LOX/kerosene staged combustion cycle engine was established, and the effect of the film local injection structure on the local flow and cooling effect near the outlet of film cooling slot was analyzed. Under the supercritical condition, kerosene and its surrounding gas are in same phase, and can be described by the same equation for flow and heat transfer. Numerical simulations for 3 typical injection structures were carried out in this paper. The resuits show that： the step and angle of the film ring outlet and injection have great influence on the local flow and heat transfer, the step structure with outlet angle less than 90 degree will could reduce the local recirculation in favor of heat protection of the thrust chamber.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第2期336-341,共6页
Journal of Aerospace Power
关键词
航空、
航天推进系统
液体火箭发动机
推力室
超临界流体
膜冷却
传热
aerospace propulsion system
liquid rocket engine
thrust chamber
supercritical fluid
film cooling
heat transfer
