Effects of swirl injection on the combustion of a 11el composite hybrid rocket fuel grain

doi:10.1016/j.actaastro.2022.07.027

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	Effects of swirl injection on the combustion of a 11el composite hybrid rocket fuel grain
	Zhang ZL(张泽林); Lin X(林鑫); Wang ZZ(王泽众); Wu K(吴坤); Luo JX(罗家枭); Fang SH(方思晗); Zhang CY ; Li F(李飞); Yu XL(余西龙)
刊名	ACTA ASTRONAUTICA
	2022-10
卷号	199 页码:174-182
关键词	Hybrid rocket engine Swirl injection 11el composite fuel grain Regression rate Oxidizer-to-fuel ratio
ISSN号	0094-5765
DOI	10.1016/j.actaastro.2022.07.027
英文摘要	The combustion characteristics obtained from the coupling effect between swirl injection and a 11el composite hybrid rocket fuel grain were investigated. The 11el composite fuel grain was composed of a three-dimensional printed acrylonitrile-butadiene-styrene (ABS) helical substrate with an embedded paraffin-based fuel. Two swirl flow injectors with opposite injection directions were designed: one with the same injection direction as the swirling direction induced by the ABS helical substrate and the other having the opposite direction. Axial injection trials were also performed as a baseline for comparison. Firing tests were carried out using a lab-scale hybrid rocket engine with oxygen as the oxidizer at average mass flux values in the range of 2.1-4.5 g/ (s.cm(2)). When combined with either swirl flow injector, the 11el composite fuel grain exhibited excellent combustion properties. Compared with the axial flow injector, both swirl injectors greatly improved the regression rate of the 11el composite fuel grain, by 82.4% and 50.6% respectively, at an oxygen mass flux of approximately 4.25 g/(s.cm(2)). Three-dimensional imaging of the inner surface of the 11el composite fuel grain and cold flow numerical simulations were employed to assess the mechanism by which the regression rate was increased. The results of these analyses elucidated the effects of different injection methods on the oxidizer-tofuel ratio distribution during combustion of the 11el composite fuel grain.
学科主题	Engineering, Aerospace
分类号	二类/Q1
语种	英语
WOS记录号	WOS:000858845300008
资助机构	National Natural Science Foundation of China [11802315, 12072355, 11872368, 11927803] ; Key-Area Research and Development Program of Guangdong Province [2021B0909060004] ; National Key Project [GJXM92579] ; Youth In11ation Promotion Association of CAS [2022018]
其他责任者	Lin, X (corresponding author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/90135]
专题	力学研究所_高温气体动力学国家重点实验室
作者单位	1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China 2.North Univ China, Coll Mechatron Engn, Taiyuan 030051, Peoples R China 3.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Zhang ZL,Lin X,Wang ZZ,et al. Effects of swirl injection on the combustion of a 11el composite hybrid rocket fuel grain[J]. ACTA ASTRONAUTICA,2022,199:174-182.
APA	张泽林.,林鑫.,王泽众.,吴坤.,罗家枭.,...&余西龙.(2022).Effects of swirl injection on the combustion of a 11el composite hybrid rocket fuel grain.ACTA ASTRONAUTICA,199,174-182.
MLA	张泽林,et al."Effects of swirl injection on the combustion of a 11el composite hybrid rocket fuel grain".ACTA ASTRONAUTICA 199(2022):174-182.