固体燃料冲压发动机旋流燃烧特性试验  

Experiment on swirl combustion characteristics of solid fuel ramjet

作　　者：刘巍[1] 杨涛[1] 胡建新[1] 于宁[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2009年第1期5-8,共4页Journal of Propulsion Technology

基　　金：国家自然科学基金(50376072)

摘　　要：为研究固体燃料冲压发动机旋流燃烧特性,进行了直流与旋流对比直连式试验。固体装药内径40mm,长180 mm,成分为HTPB中加入65%的金属粉末。试验发动机采用火炬式点火器点火,空气由燃烧补氧式空气加热器加热至690 K,热空气流量300 g/s。试验测量了压力、推力等参数,使用监控录像对发动机尾焰进行拍摄,通过测量试验前后装药质量差获得固体燃料平均燃速。旋流试验未将旋流器伸入燃烧室即实现了火焰稳定,且旋流燃烧比直流燃烧表现出更好的稳定性,平均燃速较直流提高近50%。旋流燃烧尾焰存在明显的径向扩张,表明尾焰仍有切向动量,损失了部分推力。In order to study the swirl combustion characteristics of solid fuel ramjet,direct/swirl flow contrast experiments were conducted on a direct-connected pipe test bed.The solid fuel contained 65% metal powder based on HTPB.The initial port diameter of the solid fuel was 40 mm,and the length was 180 mm.An ethanol/oxygen spark torch igniter was used for the ignition of solid fuel.Inlet air was heated up to 690 K,and oxygen was mixed with air to ensure that the vitiated air contained 23% oxygen.The flux of the ...

关 键 词：固体燃料冲压发动机 旋流燃烧 直连式试验+ 燃速 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]