文氏管对脉冲爆轰火箭发动机工作过程影响实验研究  

Experimental study on venturi effect on working process of pulse detonation rocket engine

作　　者：蒋弢[1] 翁春生[1] 

机构地区：[1]南京理工大学瞬态物理国家重点实验室,江苏南京210094

出　　处：《南京理工大学学报》2014年第2期241-245,251,共6页Journal of Nanjing University of Science and Technology

基　　金：国防预研基金;中央高校基本科研业务专项资金(3092013011200);高等学校博士学科点专项科研基金(20093219110037);南京理工大学自主科研专项计划(2011XQTR05)

摘　　要：为了研究文氏管对脉冲爆轰火箭发动机雾化混合和燃烧转爆轰过程的影响,对不安装文氏管和安装3种喉部半径(10 mm,20 mm,30 mm)文氏管的脉冲爆轰火箭发动机进行了实验研究。实验结果表明:安装文氏管时,雾化混合效果更好;如果满足爆轰管内填充系数为1,应该选取喉部尺寸较小的文氏管来改善雾化混合效果;改善雾化混合效果有利于提高发动机的工作频率和爆轰波压力峰值。To study the venturi effect on the process of the atomization,mixing and deflagration to detonation transition（DDT）of pulse detonation rocket engine（PDRE）,the experiment is carried out by installing venturis with three throat radius（ 10 mm,20 mm,30 mm） and without venturi in PDRE. The experimental results show that the gasoline-air distribution performance of PDRE with venturis is better than that of PDRE without venturis. When PDRE is fully filled with air and gasoline,the venturi with the smaller throat radius can improve the effect of atomization and mixing. The working frequency and the detonation wave peak of PDRE can be increased by improving the effect of atomization and mixing.

关 键 词：脉冲爆轰火箭发动机 文氏管 雾化混合 两相爆轰 燃烧转爆轰 

分 类 号：V235.22[航空宇航科学与技术—航空宇航推进理论与工程]