摘要
为了分析隔板片数量对液体火箭发动机燃烧不稳定性的影响,在验证仿真模型有效性的基础上,采用欧拉-拉格朗日方法对液体火箭发动机燃烧室内的两相燃烧过程进行了数值模拟。结果表明:试车工况下气氧煤油发动机燃烧流场仿真结果与实验结果的误差仅为3%,符合较好,数值仿真模型是有效的;在1轮毂3径向、1轮毂4径向及1轮毂6径向工况下,均能对无隔板工况下燃烧室中存在的高频不稳定燃烧进行抑制,其中1轮毂3径向工况下,抑制效果最佳。在影响燃烧室内压力振荡剧烈程度的3种因素中,压力扰动是否全部处于隔板影响区域之内起到的作用最大,压力振荡与释热波动之间的相位耦合程度起到的作用次之,压力扰动的强度起到的作用最小。
In order to analyze the influence of baffle number to the combustion instability of liquid rocket engine,the two-phase reacting process in liquid rocket engine combustion chamber is numerically simulated by using Eulerian-lagrangian method after verifying the validity of the model.The results indicate that the error of simulation result and the experiment result of the GOX/Kerosene rocket engine is only 3%,and conformes well to each other.The model is valid.The high frequency combustion instability can be restrained when there is baffle of radial 3,radial 4 and radial 6,the effect of 3 radial baffle is best.In the three factors which influence the pressure vibration degree,the effect of whether the pressure disturbance is in the influence region is greatest,the effect of the phase coupling degree between pressure oscillation and heat release takes second place,the effect of pressure disturbance intensity is the least.
作者
马列波
聂万胜
Ma Lie-bo;Nie Wan-sheng(China Aerodynamics Research and Development Center,Mianyang,621000;Aerospace Engineering University of PLA,Beijing,101416)
出处
《导弹与航天运载技术》
CSCD
北大核心
2020年第6期27-32,共6页
Missiles and Space Vehicles
基金
国家自然科学基金项目(51206185,91441123)。
