摘要
针对液氧煤油发动机高室压推力室冷却技术,讨论了多条内冷却环带、人为粗糙度、内壁铣槽结构和隔热镀层等主要技术措施。对带人为粗糙度的平直通道内流动进行了二维和三维时均流数值模拟,分析了人为粗糙度局部强化换热机理。对多条液气膜冷却环带进行了数值模拟,分析了内冷却流量对冷却的影响。研究结果表明,合理设置人为粗糙度和采用冷却环带技术可有效降低推力室局部气壁温,以煤油为冷却剂的高压推力室冷却方案应以再生冷却结合多条液气膜冷却技术为主,综合采取人为粗糙度、高导热材料、隔热镀层等技术措施。
The primary available cooling techniques for high pressure thrust chamber of the LOX/kerosene rocket engine,such as multi-film cooling slot,artificial roughness,milled wall structure and thermal barrier were discussed,while the effects of the artificial roughness and multi-film cooling slot in chamber were analyzed by the numerical simulation.The results show that the proper use of artificial roughness in the cooling channel and multi-film cooling in the inner wall will play the important roles to reducing ...
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第1期242-245,259,共5页
Journal of Astronautics
关键词
液氧煤油发动机
推力室
液膜冷却
强化换热
再生冷却
人为粗糙度
LOX/kerosene engine
Thrust chamber
Film cooling
Heat transfer enhancement
Regeneratively cooling
Artificial roughness
