空气动力学学报2025，Vol.43Issue(4)：20-29,10.DOI:10.7638/kqdlxxb-2024.0084
推进剂微射流冷却对高温非平衡气动热的影响机理
Mechanism of propellant micro-jet cooling effects on high-temperature non-equilibrium aerodynamic heating
摘要
Abstract
During high-speed flight,the aircraft can utilize its own propellant to cool through the micro-hole jet to achieve active thermal protection.However,under high-temperature non-equilibrium conditions,the interaction between the compressible external flow and micro-jets involves complex processes including jet extrusion,mixing,and reactions,making the dominant mechanisms and influencing factors of micro-jet cooling highly intricate.In this study,a viscous wall boundary model for micro-jets was established,and numerical simulations of high-temperature non-equilibrium flow fields under micro-jet effects were conducted.The influence of jet hole diameter,velocity,and spacing on cooling performance were investigated.The simulations reveal the impact mechanisms of micro-jets on chemical reaction boundary layers,wall heterogeneous catalysis,and aerodynamic heating characteristics.The findings indicate that propellant micro-jet cooling under high-temperature non-equilibrium flow conditions is dominated by two key processes:boundary layer crowding and heterogeneous catalytic weakening.Specifically,the low-temperature micro-jet ejection crowds the boundary layer,altering its profile and reducing the temperature gradient near the wall,thus decreasing wall-normal heat conduction and achieving cooling.Additionally,the crowding-out effect of the low-temperature micro-jet promotes the outward displacement of near-wall O atoms,weakening the oxygen catalytic effect and reducing catalytic heat.Further parametric study shows that when the mass flow rate is constant,the heat reduction rate and cooling range decrease with the increase of jet hole size.When the area of the jet hole is constant,the micro-jet velocity is increased,and the heat reduction rate and cooling range are increased.When the mass flow rate is constant and the hole spacing is reduced,the peak value of the spanwise average heat reduction rate decreases,but the cooling range downstream of the hole increases,showing a more uniform cooling effect.These findings provide crucial theoretical support and technical guidance for the design and optimization of active thermal protection systems utilizing micro-jet cooling in future high-speed vehicles.关键词
微射流冷却/非平衡流动/气动热/壁面催化/数值模拟Key words
micro-jet cooling/non-equilibrium flow/aerodynamic heating/wall catalysis/numerical simulation引用本文复制引用
邢旭雯,杨肖峰,刘磊,杜雁霞..推进剂微射流冷却对高温非平衡气动热的影响机理[J].空气动力学学报,2025,43(4):20-29,10.基金项目
国家重点研发计划项目(2019YFA0405202) （2019YFA0405202）
国家自然科学基金(12072361) （12072361）
