摘要
针对空气涡轮火箭冲压发动机马赫数1.5~4.5工作范围的设计要求,提出了一种唇口平移的曲面轴对称进气道变几何方案及其新型调节机构,并通过数值仿真方法对其总体性能和流动特性进行研究。结果表明:采用曲面压缩的轴对称变几何进气道总体性能较高,尤其是流量捕获能力良好,可以满足整个工作范围的需求。此外,新型调节机构简单可行,利于工程实现。
In view of the design requirements for the air turbine-rocket and ramjet（ ATRR） engines with Mach number from 1. 5 to 4. 5,a variable geometry scheme of curved symmetrical inlet with cowl translation is proposed as well as its new adjustment mechanism. The overall performances and flow characteristics are studied by numerical simulation. The results show that overall performances of the axisymmetric variable-geometric inlet with curved surface compression is high,especially the flow capture ability is good,which can meet requirements of the entire operating range. In addition,the new mechanism is simple and feasible,which is beneficial to the engineering realization.
作者
李永洲
李光熙
刘晓伟
马元
LI Yongzhou;LI Guangxi;LIU Xiaowei;MA Yuan(Xi＇ an Aerospace Propulsion Institute,Xi＇ an 710100,China)
出处
《火箭推进》
CAS
2018年第4期30-35,共6页
Journal of Rocket Propulsion
基金
国家自然科学基金(11702205)
关键词
组合发动机
变几何进气道
调节机构
马赫数分布
弯曲激波
combined cycle engine
variable-geometry inlet
adjustment mechanism
Mach numberdistribution
curved shock
