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超燃冲压发动机加速过程中燃烧不稳定性研究
Authors
孟宇
岳连捷
张新宇
顾洪斌
Publication date
25 August 2019
Publisher
Abstract
本研究在直连式超燃冲压发动机实验台实现了超燃冲压发动机动态连续加速,进行了等当量比和连续递减当量比试验。实验模拟了高超声速飞行器高空加速过程,飞行马赫数Ma 5加速至Ma 6,燃烧室马赫数2.4至2.9。在均匀加速过程中,第一凹腔出现了压力压比的非均匀变化,而第二凹腔压力压比变化均匀。压力是燃烧释热状态的体现。在加速过程中保证当量比不变的同时,燃烧组织会发生不均匀的变化。火焰在低马赫数时主要表现为稳定的剪切层火焰和射流稳焰共存。随着来流马赫数提高,火焰逐渐在射流稳焰和剪切层稳焰切换,是一种不稳定的火焰结构。火焰的不稳定切换,导致了燃烧室压力压比的不稳定。得到了超燃冲压发动机在实际飞行加速过程中的不稳定特性,以及这一不稳定主要由火焰结构转换导致的结论
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Institute Of Mechanics,Chinese Academy of Sciences
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Last time updated on 18/12/2019