摘要
针对在宽飞行马赫数范围内工作的某串联TBCC可调喷管较高的进口总温易引起壁面材料烧蚀的问题,提出一种适用于飞行包线内不同飞行马赫数且对喷管热防护有明显作用的气膜冷却方案,并基于CFD的方法模拟了不同飞行马赫数的冷却效果.研究表明开设二元缝槽将比开设环形缝槽对附近流场状况产生更明显的影响.采用气膜冷却方案后,喷管壁面平均温度较未经气膜冷却时有超过1 000K的明显下降.壁面二元缝槽下游中心线上的气膜冷却绝热效率在多数飞行马赫数下可达0.9以上.缝槽下游温度在展向上多呈对称分布,向下游发展时温度均匀性逐渐降低.
In view of the problem that the higher inlet total temperature of tandem TBCC nozzle can reduce the ablation of the wall material,a film-cooling scheme adapted to different flight Mach numbers in the flight envelope was presented,showing a significant effect on the thermal protection of the nozzle.The cooling effect for different flight Mach numbers based on the CFD method was calculated.The research indicates that there will be a more noticeable change of the flow field conditions nearby the rhomboid slots than annular slots.After film-cooling,the temperature of nozzle has a 1 000K＇s decline than before.The filmcooling adiabatic efficiency of the downstream wall centerline can reach to 0.9at most flight Mach numbers.The downstream wall temperature of the slot is mainly distributed symmetrically along the span of the nozzle,and the temperature uniformity gradually declines with x＇s increment.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2016年第10期2454-2463,共10页
Journal of Aerospace Power
