Experimental investigation on effects of injection distribution on combustion instability in a model rocket combustor

被引：10
|
作者：
Guo, Kangkang [1 ]
Ni, Lei [1 ]
Ren, Yongjie [1 ]
Lin, Wei [1 ]
Tong, Yiheng [1 ]
Nie, Wansheng [1 ]
机构：
[1] Space Engn Univ, Dept Aerosp Sci & Technol, Beijing 101416, Peoples R China
来源：
PHYSICS OF FLUIDS | 2022年 / 34卷 / 01期
基金：
中国国家自然科学基金;
关键词：
Combustors;
D O I：
10.1063/5.0080810
中图分类号：
O3 [力学];
学科分类号：
08 ; 0801 ;
摘要：
Self-excited combustion instabilities of transverse modes were experimentally investigated in a rectangular multi-injector model combustor, operating with the bipropellants O-2/CH4. The propellants were injected through a linear array of five oxidizer-centered shear coaxial injectors into the combustor. High-amplitude limit cycles obtained in hot-fire tests were analyzed in detail. Different combustion instability modes, including first and second width modes, were observed in cases with three different injection distribution schemes. Hence, the injection distribution strongly determined the combustion dynamics. One insight can be gained that the stable combustion could be achieved by properly designing the propellants' injection distributions.
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收藏
页数：6
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