环形爆震室引射增推试验研究  

Experimental Study on Thrust Augmentation of Toroidal Detonative Chamber Ejector Systems

作　　者：秦亚欣 高歌[2] 

机构地区：[1]中国航空研究院新技术研究所,北京100012 [2]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《科学技术与工程》2016年第6期117-120,128,共5页Science Technology and Engineering

摘　　要：对爆震室的填充比、引射喷管的种类、轴向位置、长度等参数对环形爆震室引射推力增量的影响进行了试验研究分析。研究发现直引射喷管和直-扩引射喷管都是在轴向位置X=0 mm处时增推效果最好;直-扩引射喷管对爆震室的引射推力增量比直引射喷管的推力增量大;直引射喷管长度为590 mm时推力增量最大,直-扩引射喷管长度为690 mm时推力增量最大,推力增量最大值分别为25.9%和40.1%。The effects of variable parameters, including detonative chamber fill-fraction, structure of ejector, axial location of ejector, and ejector length, on thrust augmentation of toroidal detonative chamber ejector systems were experimental investigated separately. The maximum thrust augmentation was found to occur at the axial location X = 0 mm in the straight and straight-diverging ejector system driven by the toroidal detonative chamber. It was found that the straight-diverging ejector produced larger thrust augmentation than the straight ejector. The maximum thrust augmentation was achieved 40. 1% , which was observed to occur at the straight-diverging ejector overall length of 690 mm ; For the straight ejector, the maximum thrust augmentation was obtained 25.9% at the length of 590 mm.

关 键 词：脉冲爆震发动机 环形 引射喷管 推力增量 试验研究 

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]