扇形脉冲爆震燃烧室起爆过程数值模拟  

Numerical Simulation of Detonation Initiation in Sector Pulse Detonation Combustor

作　　者：张佳博 郑龙席[1] 卢杰[1] 彭辰旭 罗振坤 ZHANG Jia-bo;ZHENG Long-xi;LU Jie;PENG Chen-xu;LUO Zhen-kun(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129

出　　处：《航空发动机》2024年第3期53-57,共5页Aeroengine

摘　　要：为了探究不同障碍物结构对扇形脉冲爆震燃烧室起爆过程的影响,对采用3种典型孔板障碍物的扇形脉冲爆震燃烧室,截取其中间截面进行了起爆过程的数值模拟,研究了障碍物型式、障碍物堵塞比及障碍物间距对扇形脉冲爆震燃烧室爆燃转爆震(DDT)距离的影响规律。结果表明:障碍物堵塞比对扇形脉冲爆震燃烧室DDT距离的影响最大,且在堵塞比为0.35~0.70时,堵塞比越高DDT距离越短;在3种型式的障碍物中,在低堵塞比下,截面为前掠三角形的障碍物缩短DDT距离的效果最好,在高堵塞比下,截面为后掠三角形的障碍物缩短DDT距离的效果最好;在3种障碍物间距中,当间距分别等于1倍和1.2倍的爆震室当量直径时,扇形脉冲爆震燃烧室的DDT距离相差不大,且均短于障碍物间距等于0.8倍爆震室当量直径时的DDT距离。In order to investigate the influence of different obstacle structures on the initiation process of a sector pulse detonation combustor,numerical simulations of the initiation processes in the middle cross-section of the sector pulse detonation combustor with three types of typical orifice plate obstacles were carried out,and the influences of the type,blockage ratio,and spacing of the obstacles on the deflagration to detonation transition(DDT)distance of the sector pulse detonation combustor were studied.The results show that the obstruction blockage ratio has the greatest influence on DDT distance,and the higher the blockage ratio,the shorter the DDT distance within the blockage ratio range of 0.35~0.70.Among the three types of obstacles,the obstacles with a swept-forward triangle section have the best effect on shortening DDT distance at a low blockage ratio and those with a swept-back triangle section have the best effect on shortening DDT distance in the case of high blockage ratio.Among the three spacings,the DDT distances have little difference when the obstacle spacings are 1 and 1.2 times the equivalent diameter of the detonation combustor,and both of them are shorter than the DDT distance when the obstacle spacing is 0.8 times the equivalent diameter of detonation combustor.

关 键 词：扇形脉冲爆震燃烧室 爆燃转爆震 障碍物 堵塞比 数值模拟 航空发动机 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]