结构特性对燃烧室压强振荡的影响研究  

The Effect of Structure Characteristics on Pressure Oscillation in Combustion Chamber

作　　者：许团委[1,2] 田维平[1] 王建儒[2] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国航天科技集团公司第四研究院第41所,西安710025

出　　处：《弹箭与制导学报》2013年第1期117-120,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了揭示结构特性对固体发动机燃烧室压强振荡的影响规律,采用大涡模拟方法以"绝热环"及"潜入式喷管空腔背壁区"为重要结构设计参数,完成了4种不同结构设计条件下的典型VKI发动机流场稳定性数值模拟。最终获得了各工况下的压强-时间曲线及其FFT结果。分析表明:绝热环是引起旋涡脱落的主要因素,背壁区维持并加强了声涡耦合引起的声能增益,对压强振幅有较大的影响。In order to discover the mechanism between structure characteristics and pressure oscillation in solid rocket motor （SRM）, in- hibitor ring and back wall region of submerged nozzle were taken as key parameters, large eddy simulation （LES） was carried on for four different model based typical Von Karman institute（VKI） for fluid dynamics motor. Finally, pressure evolution and its fast Fourier trans- form （FFT） results were gained. It indicates that the inhibitor ring is the main factor of vortex shedding. Back wall region, which deter- mines the pressure oscillation amplitude, maintains and strengthens the acoustics energy gain caused by acoustic vortex coupling.

关 键 词：固体火箭发动机 压强振荡 大涡模拟方法 绝热环 背壁区 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]