一种RBCC二元进气道变几何方案研究  

Investigation of a RBCC 2D variable-geometry inlet scheme

作　　者：刘晓伟[1] 何国强[1] 刘佩进[1] 

机构地区：[1]西北工业大学燃烧流动和热结构国家级重点实验室,西安710072

出　　处：《固体火箭技术》2010年第4期409-413,418,共6页Journal of Solid Rocket Technology

摘　　要：对工作于引射和亚燃模态的RBCC发动机进气道来说,宽马赫数工作的要求显得尤为突出,使得二元进气道应采用变几何结构。针对内压段收缩比对二元混压式进气道性能的影响,文中开展了理论分析和数值模拟研究,并由此提出了一种将内收缩比调节和边界层流动控制相结合的变几何二元进气道方案。研究发现,该方案以低马赫数小范围内较少的流量损失为代价,实现了进气道起动马赫数、阻力的降低和出口总压的增加,改善了进气道的综合性能。In ejector and ramjet modes,working over a wide Mach number range is very important for the RBCC inlet,so the 2D RBCC inlet should be variable-geometry.In this paper,the effect of internal convergent ratio on performance of the mixed-compression inlet is investigated by theretical analysis and numerical simulation,then an variable-geometry 2D inlet scheme,combining the internal contraction ratio adjustment and the boundary layer flow control,is presented.Results show that the variable-geometry scheme attains the improvement of inlet intergrated performance,including decreases of starting Mach number and drag force,and the increase of total pressure recovery coefficient,on the premise of smaller flow loss during a narrow lower Mach number range.

关 键 词：RBCC发动机 二元进气道 变几何进气道 边界层流动控制 数值模拟 

分 类 号：V448.15[航空宇航科学与技术—飞行器设计]