液体火箭发动机径向不稳定燃烧数值分析模型

推进技术 ›› 1997, Vol. 18 ›› Issue (6): 5-9.

液体火箭发动机径向不稳定燃烧数值分析模型

刘卫东,王振国,周进,庄逢辰

国防科技大学航天技术系!长沙;410073;国防科技大学航天技术系!长沙;410073;国防科技大学航天技术系!长沙;410073;国防科技大学航天技术系!长沙;410073

发布日期:2021-08-15

NUMERICAL ANALYSIS MODEL OF RADUL COMBUSTION INSTABILTY IN LIQUID PROPELLANT ROCKET ENGINE

Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073

Published:2021-08-15

摘要/Abstract

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。

关键词: 振荡燃烧;液体推进剂火箭发动机;数值分析

Abstract: 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.

Key words: Vibrational combustion;Liquid propellant rocket engine;Numerical analysis

刘卫东,王振国,周进,庄逢辰. 液体火箭发动机径向不稳定燃烧数值分析模型[J]. 推进技术, 1997, 18(6): 5-9.