固体燃料冲压发动机内部套管结构数值分析  

Numerical analysis on tube-in-hole structure for solid fuel ramjet

作　　者：刘巍[1] 杨涛[1] 程兴华[1] 李理[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2010年第2期152-155,共4页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(50376072)

摘　　要：为了研究固体燃料冲压发动机内部套管结构调节燃料流量的特性,对某模型发动机的湍流燃烧流场进行了数值分析。研究发现,套管开口靠近有效载荷末端与燃烧室入口收缩段时,燃料流量的变化速度较快,而在二者之间的位置基本保持不变;套管开口紧贴有效载荷末端时,燃烧室出口燃烧效率较无套管有所提高,套管向下游移动,将使燃烧室出口燃烧效率降低;套管壳体的最高温度出现在套管出口位置,应适当加强套管末段的热防护。In order to study the fuel mass flow rate regulation characteristics of tube-in-hole for solid fuel ramjet,the flow field of turbulent combustion was numerically analyzed.The results show that while the fuel mass flow rate changes rapidly with the tube inlet near the end of the payload and the inlet of combustion chamber,the position between them is nearly unchanged.The combustion efficiency at combustion chamber outlet of SFRJ with tube-in-hole is higher than that without it,and the combustion efficiency decreased with the tube moving downstream.The hottest position of the tube is at the exit,so the heat protection is needed at the downstream part of the tube.

关 键 词：固体燃料冲压发动机 套管 燃料流量调节 数值分析 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]