摘要
基于Fluent平台,采用有限速率/涡破碎燃烧模型和组分输运模型对分布式进气道补充燃烧装置进行了数值仿真,研究了不同飞行攻角下发动机推力的变化,以及关闭进气道进行推力矢量控制的方法。结果表明,随着飞行攻角的增大,推力和进气道阻力先增大后减小,实际推力略大于标准推力且先增大后减小;关闭某个进气道后,该进气道出口下游二次燃烧区域消失,在喷管壁面上产生压力分布不均,产生侧向力。
Based on Fluent platform,the numerical simulation of distributed supplement combustion of diverted inlet was carried out by using the finite-rate/eddy-dissipation combustion model and the component transport model.The thrust variation of the engine at different flight angles of attack and the method of thrust vector control by closing the intake port were studied.The results show that with the increase of the angle of attack,the thrust and the resistance of the inlet increase first and then decrease,and the actual thrust is slightly larger than the standard thrust and increases first and then decreases.After closing an inlet,the secondary combustion area downstream of the inlet expansion disappears,resulting in uneven pressure distribution on the nozzle wall,resulting in lateral force
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