摘要
固体火箭发动机中声波振荡是引起不稳定燃烧的一个重要原因。通过对固体火箭发动机不同药型燃烧室压力填充瞬态过程进行数值模拟,得出在燃烧室压力填充瞬间,燃烧室会产生较高频率的纵向声振。加堵盖和不同的喷喉大小以及燃烧室长度变化等因素会对声振产生不同的影响。计算结果表明,这些影响包括了声振的强度、阻尼和频率,发动机点火后喷管喉部尺寸和堵盖打开的时间影响到振荡波的发展和消失。
Numerical simulations for different grain models show that the high frequency longitudinal acoustic oscillations could be generated at the moment of pressure filling. The factors affecting the acoustic oscillations have bccn studied. The results indicate that these factors include the intensity, damping and frequency of the acoustic oscillations. The development and disappearance of the acoustic oscillations are influenced by the nozzle throat size and open-time of the plug.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2006年第6期484-487,共4页
Journal of Propulsion Technology
关键词
固体推进剂火箭发动机
数值仿真
燃烧室
压力填充
声振动
Solid propellant rocket engine
Numerical simulation
Combustion chamber
Pressure filling
Acoustic vibration
