不同压比下冷却剂流量对塞锥再生冷却换热的影响  

Compare of plug nozzle's heat transfer characteristics in different opertoin condition and with different coolant flow rate

作　　者：韩非[1] 刘宇[1] 李军伟[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《航空动力学报》2006年第4期778-783,共6页Journal of Aerospace Power

基　　金：国家863基金资助(863-2-1-3-1)

摘　　要：为了解塞式喷管发动机高低空不同的再生冷却换热特性,分别对二维型面内喷管和塞锥建立计算模型,采用数值模拟的方法,得出内喷管的冷却换热结果和出口参数,重点研究了塞锥在地面和设计点工作时的不同换热特性及其冷却剂流量的影响。计算过程中采用二阶迎风格式离散控制方程。计算结果表明:地面工况下,冷却剂流量的改变对塞锥和塞锥底部壁面的压强、热流密度和温度的影响较大,高空环境下,冷却剂流量的改变对塞锥和塞锥底部壁面的压强、热流密度的影响较小;在冷却剂流量相同的情况下,塞锥和塞锥底部在地面工况下的壁面温度要远高于在高空环境下的温度;在相同工况和相同冷却剂流量的情况下,塞锥壁面上的温度要远高于塞锥底部壁面上的温度。To understand the different heat transfer characteristics of regenerative cooling in plug nozzle at different operating conditions, computational model of two dimensional plug nozzle and internal nozzle were established and numerical simulation was employed. Heat transfer results of the internal nozzle and the parameter distribution at the outlet were obtained. Flowfield and heat transfer characteristics of the plug at different operating conditions with different coolant flow rates were investigated. For calculation, governing equations were discretized with second order upstream scheme. The results show that at sea level, coolant flow rate affects the plug pressure, heat flux and temperature; at design operating condition, coolant flow rate has no effect on pressure and heat flux on the plug wall. With the same coolant flow rate, plug temperature at sea level is higher than that at design operating condition; under the same operating condition, ramp temperature is higher than the plug base temperature.

关 键 词：航空 航天推进系统 液体推进剂火箭发动机 塞式喷管 再生冷却 数值模拟 热流密度 

分 类 号：V434.14[航空宇航科学与技术—航空宇航推进理论与工程]