超声速补燃的三维数值模拟和实验研究  

Three-dimensional numerical and experimental investigation on supersonic secondary combustion

作　　者：马朝恺[1] 徐旭[1] 刘明昊[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《推进技术》2004年第4期289-293,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金(10072010);航空基金(00A51070)。

摘　　要：利用贫氧固体推进剂燃烧产生的高温燃气与侧喷空气混合进行了超声速补燃实验。运用有限体积法求解三维N S方程和组分连续方程组,对实验所涉及的化学反应流场进行了数值模拟。通过考察两种掺混器的穿透深度、流向涡强度等参数,比较了二者的混合及燃烧增强效果,分析了原因。结果表明在所研究的工况下,桶型掺混器性能更优。Supersonic secondary combustion of fuel-rich gases enhanced by air injection was experimentally investigated. Numerical solutions of the finite-volume discretized full Navier-Stokes equations, coupled with chemical reaction species continuum equations, were obtained for the experimental flow fields. By examining the injection boundary, streamwise vortex etc., the mixing and combustion efficiencies of two mixers were compared, and the results show that the performance of the barrel mixer is predominated over that of the cone mixer.

关 键 词：冲压火箭发动机 超音速燃烧 化学反应 流动分布 实验 数值仿真 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]