火箭推进2026，Vol.52Issue(4)：42-55,14.DOI:10.3969/j.issn.1672-9374.2026.04.005
液氧煤油同轴离心喷注器超临界燃烧特性分析
Analysis on combustion characteristics of LOX/kerosene bi-swirl injectors at supercritical pressures
摘要
Abstract
This study investigated a coaxial swirl injector for liquid oxygen(LOX)/kerosene rocket engines using the stress-blended eddy simulation(SBES)method.The effects of recess length,lip thickness,and operating pressure on supercritical combustion characteristics were systematically analyzed.Under supercritical and near-critical pressure conditions,the thermophysical properties of the fluid vary sharply and nonlinearly with temperature,which poses significant challenges to numerical accuracy and convergence.The Soave-Redlich-Kwong(SRK)real-gas equation of state was adopted to describe the thermodynamic behavior of the fluid.Analysis based on the vorticity transport equation shows that increasing the recess length enhances the vortex-stretching mechanism within the confined region and promotes the formation of organized streamwise vortex trains.This process helps resist downstream disturbances and anchors the flame root in the recess region.In contrast,reducing the lip thickness causes earlier nonlinear interaction between the inner and outer shear layers,intensifies viscous dissipation of vorticity,and disrupts the integrity of large-scale coherent structures in the wake region,resulting in a pulsating flame root.Further analysis under lower supercritical pressure conditions reveals the thermodynamic effects of near-critical fluids.The baroclinic torque induced by the misalignment between density and pressure gradients is significantly enhanced and acts as an additional source of vorticity generation.关键词
液氧煤油/超临界燃烧/同轴离心喷注器/涡动力学/斜压效应Key words
liquid oxygen/kerosene/supercritical combustion/coaxial swirl injector/vorticity dynamics/baroclinic effect分类
航空航天引用本文复制引用
武桢干,王龙飞,周明烁,于涵,杨宝娥,王兴建..液氧煤油同轴离心喷注器超临界燃烧特性分析[J].火箭推进,2026,52(4):42-55,14.基金项目
国家重点实验室基金(2024JJ015002) （2024JJ015002）
