液氧/甲烷燃气发生器试验研究  

Research on hot tests of LOX/methane gas generator

作　　者：马冬英[1] 卢钢[1] 张小平[1] 李春红[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2013年第3期21-26,共6页Journal of Rocket Propulsion

基　　金：国家863项目(2007AA705302)

摘　　要：为了研究液氧/甲烷的点火和燃烧特性,进行了液氧/甲烷燃气发生器热试验研究。介绍了液氧/甲烷燃气发生器热试验的试验装置、试验方案和试验情况,分析了试验结果。试验结果表明燃气发生器设计方案和点火方案可行,点火品质较好,能够在较宽的工作条件下稳定工作,燃烧组织合理,燃烧品质良好,温度均匀性较好,积碳轻微。Hot firing tests of LOX/methane gas generator were researched for the characteristic of ignition and combustion of LOX/methane.In this paper,the testing apparatus,scheme and situation of LOX/methane gas generator for hot firing test were described,and the test results were analyzed.The tests results indicate that the design scheme and ignition procedure of the gas generator were feasible.The gas generator can work in a wide range of pressure and mixture ratio,and had rational combustion,good temperature uniformity and a little coking.

关 键 词：液体火箭发动机 液氧 甲烷 燃气发生器 点火 燃烧 积碳 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]