滚控发动机燃气引流方案研究  

Investigation of exhaust pipe schemes for rolling control engine

作　　者：付秀文[1] 杨建文[1] 石晓波[1] 周立新[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2014年第2期49-53,66,共6页Journal of Rocket Propulsion

基　　金：国家863项目(2012AA705303)

摘　　要：依据某型滚控发动机实际结构,设计了3种燃气引流方案,方案1采用喷管与引射直筒留有间隙的布局形式,方案2采用喷管嵌入引射筒、引射筒后部接弯管的布局形式,方案3采用喷管直接排入引射筒的布局形式。采用商业软件对3种方案的引流效果进行了数值仿真,仿真结果表明方案1结构简单、易于实施,能够满足燃气顺利排放条件;方案2能够满足燃气引流,但会产生较大轴向力;方案3也可满足燃气引流,但引射筒与喷管间隙较难控制;综合分析得到方案1适合该滚控发动机燃气引流。According to the structure of the rolling control engine, three exhaust pipe schemes were designed for engine test. In scheme 1, a clearance between engine pipe and exhaust pipe is kept. In scheme 2, the end of the engine pipe is put into the entrance of exhaust pipe which is followed by an elbow bend pipe. In scheme 3, the end of the engine pipe was put into the entrance of exhaust pipe. The effect of the three exhaust pipes was numerically simulated by means of a commercial software. The results indicate that structure of exhaust pipe in scheme 1 is simpler and easier to implement than other schemes, and can meet the condition of exhaust drainage; the exhaust pipe in scheme 2 can result in large axial force though it also can meet the requirement of exhaust drainage; the exhaust pipe in scheme 3 can meet the requirement of exhaust drainage, but it is difficult to control the clearance between engine pipe and exhaust pipe. According to the analysis, the result that the exhaust pipe scheme 1 is suitable for the rolling control engine was obtained.

关 键 词：滚控发动机 燃气引流 数值仿真 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]