建立了液体火箭发动机切向不稳定燃烧数值分析模型并进行了初步分析。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，并应用等效矩形燃烧室模型及双参数不稳定燃烧模型，通过模拟计算压力扰动波的传播过程考察了发动机燃烧稳定性。

A numerical model was employed to analyze the tangential combustion instability in liquid rocket engine.The PISO algorithm extended by the author was used to calculate the unsteady combustion flow.The equivalent combustion chamber in conjunction with the two parameter unstable combustion model were assumed in the calculation.A pressure bomb was imposed on the steady flow field for analyzing the combustion stability of rocket engine.

V434.11

“八六三”预研课题