摘要
应用数值模拟分析方法对液体火箭发动机径向不稳定燃烧完成了初步分析，并分析了声腔的阻尼特性。数值方法采用一步隐式预测、两步显式校正进行非定常流动计算的PISO算法。建立了不稳定燃烧声腔分析模型及压力挑动模型，通过模拟计算压力扰动波的传播过程考察发动机的燃烧稳定性。
Numerical methods is employed to simulate the radial combustion instability in liquid propellant rocket engine The PISO algorithm is used to calculate the unsteady combustion flowDamping characteristics of acoustic resonator in pressure disturbance is analyzed by numerical models.Based on the steady flow field, numerical pressure bomb is imPosed for analyzing the combustion stability of rocket engine' The numerical calculation shows that acoustic resonator has evident damping effects only when the frequency of disturbance nearly equals to the intrinsic frequency of the acoustic resonator.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1997年第6期5-9,共5页
Journal of Propulsion Technology
关键词
振荡燃烧
液体推进剂
火箭发动机
数值分析
Vibrational combustion, Liquid propellant rocket engine, Numerical analysis
