碳粉燃料在火箭冲压发动机补燃室内燃烧特性的分析  

Analysis of the powdered carbon combustibility in secondary combustion chamber for rocket ramjet engine

作　　者：赵春宇[1] 李斌[1] 鞠玉涛[2] 

机构地区：[1]北京航天试验技术研究所,北京100074 [2]南京理工大学,江苏南京210094

出　　处：《火箭推进》2007年第5期37-41,49,共6页Journal of Rocket Propulsion

摘　　要：采用概率密度函数(PDF)及确定轨道模型数值模拟一种环向进气的固体火箭冲压发动机补燃室气固两相流的掺混燃烧,考虑固体颗粒直径大小和补燃室长度对燃烧效率的影响。结果表明:增大固体颗粒直径,燃料的燃烧效率明显减小;增大补燃室长度,燃料的燃烧效率增大。By using the probability density function （PDF） an.d particle fixed trajectory model, the numerical simulation of two phases combustion in secondary combustion chamber for ringedpropellant rocket ramjet engine was conducted in this paper. The influences of the diameter and the length of the chamber on the combustion efficiency were considered in the model. The result indicates that with the increase of the diameter of the solid particles, the combustion efficiency evidently decreases and with the increase of the length of the chamber, the combustion efficiency increases.

关 键 词：冲压发动机 补燃室 气固两相 燃烧效率 数值模拟 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]