双模态超音速燃烧室的实验研究  

EXPERIMENTAL STUDY OF A DUAL MODE SUPERSONIC COMBUSTOR

作　　者：胡欲立[1] 钱志博[1] 刘敬华[2] 刘陵[3] 

机构地区：[1]西北工业大学三系 [2]航天工业总公司31所 [3]西北工业大学

出　　处：《宇航学报》1998年第2期55-60,共6页Journal of Astronautics

基　　金：国家自然科学基金

摘　　要：本文设计了由等截面段、扩张段和等截面段构成的超音速燃烧室，并进行了燃烧实验。用一维计算分析实验结果，表明由等截面段、扩张段和等截面段构成的超音速燃烧室，通过一定的喷油方式，能按飞行状态可分别实现超音速燃烧和亚音速燃烧，从而达到把超燃冲压发动机的工作范围下限扩大到飞行马赫数为３。In this paper,a supersonic combustor formed of a segment with constant cross section,a divergent segment and a segment with constant cross section is designed,and do combustion tests with it It is indicated by one dimensional calculation that supersonic combustion or subsonic combustion can be realized as flight speeds with the supersonic combustor formed of a segment with constant cross section,and by different fuel supplied ways,which makes the flight lower limit of Scramjet engine extended up to flight Mach number 3

关 键 词：双模态 超燃 冲压发动机 超音速燃烧 燃烧室 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]