火箭推进2026，Vol.52Issue(4)：68-77,10.DOI:10.3969/j.issn.1672-9374.2026.04.007
旋转爆震波对液膜铺展影响的数值仿真研究
Numerical investigation on liquid film spreading under rotating detonation waves
摘要
Abstract
To investigate the effect of rotating detonation waves in hypergolic propellants on liquid film spreading,numerical simulations were conducted for a rotating detonation combustion chamber utilizing nitrogen tetroxide/monomethyl hydrazine as the propellant and equipped with liquid film cooling.The spatial distributions of pressure and temperature within the rotating detonation combustion chamber were obtained from a case without liquid film.By assigning a User-Defined Function(UDF)to the liquid film spreading case,changes in the liquid film morphology were compared under conditions with and without rotating shock wave disturbance.The computational results indicate that three wave propagation modes of the rotating detonation wave for hypergolic propellants were obtained.The gas flow velocity inside the rotating detonation combustion chamber is relatively high,with velocities in most regions near the walls reaching over 400 m/s,which is detrimental to liquid film spreading.Under the disturbance of the rotating detonation wave,the maximum reduction in the effective width of the liquid film reaches 81.97％and the minimum 27.69％,whilst the maximum reduction in the effective length reaches 82.93％and the minimum 37.58％.As the liquid film flow rate increases,the reduction rates for both the effective width and length of the liquid film show a decreasing trend.When the liquid film flow rate is 10％,the cooling effect of the liquid film in the rotating shock combustion chamber can be considered to have essentially failed.关键词
旋转爆震/液膜/自燃推进剂Key words
rotating detonation/liquid film/hypergolic propellants分类
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杨博,赵明皓,王致程,严宇,杨宝娥,胡洪波..旋转爆震波对液膜铺展影响的数值仿真研究[J].火箭推进,2026,52(4):68-77,10.基金项目
国家重点实验室基金(2024JJ015001) （2024JJ015001）
