Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets

doi:10.3390/aerospace10090759

	Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets
	Wang RY(王若岩); Lin X(林鑫); Wang ZZ(王泽众); Wu K(吴坤); Zhang ZL(张泽林); Luo JX(罗家枭); Li F(李飞); Yu XL(余西龙)
通讯作者	Lin, Xin(linxin_bit@imech.ac.cn) ; Wang, Zezhong(wangzezhong@imech.ac.cn)
发表期刊	AEROSPACE
	2023-09-01
卷号	10 期号:9 页码:19
摘要	The combustion characteristics of a swirl-radial-injection composite fuel grain were experimentally and numerically investigated. This composite grain permits swirl-radial oxidizer injection based on three hollow helical blades, each having a constant hollow space allowing uniform oxidizer injection into the main chamber along the axial direction. The oxidizer enters from channel inlets located along a hollow outer wall. This wall, together with the three blades, is fabricated as one piece from acrylonitrile-butadiene-styrene using three-dimensional printing. Paraffin-based fuel is embedded in the spaces between adjacent blades. Firing tests were conducted with gaseous oxygen as the oxidizer, using oxidizer mass flow rates ranging from 7.45 to 30.68 g/s. Paraffin-based fuel grains using conventional fore-end injection were used for comparison. Regression rate boundaries were determined taking into account the erosion of the oxidizer channels. The data show that the regression rate was significantly increased even at the lower limit. Images of the combustion chamber flame and of the exhaust plume were also acquired. The flame was found to be concentrated in the main chamber and a smoky plume was observed, consistent with the high regression rate. A three-dimensional simulation was employed. The present design was found to improve fuel/oxidizer mixing and combustion efficiency compared with a fuel grain using fore-end injection. Both the experimental results and numerical simulations confirmed the potential of this swirl-radial-injection fuel grain.
关键词	hybrid rocket engine swirl-radial injection regression rate flame images combustion efficiency
DOI	10.3390/aerospace10090759
收录类别	SCI
语种	英语
WOS记录号	WOS:001072464500001
WOS研究方向	Engineering
WOS类目	Engineering, Aerospace
论文分区	二类/Q1
力学所作者排名	1
RpAuthor	Lin, Xin ; Wang, Zezhong
引用统计
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/93103
专题	高温气体动力学国家重点实验室
推荐引用方式 GB/T 7714	Wang RY,Lin X,Wang ZZ,et al. Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets[J]. AEROSPACE,2023,10,9,:19.
APA	王若岩.,林鑫.,王泽众.,吴坤.,张泽林.,...&余西龙.(2023).Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets.AEROSPACE,10(9),19.
MLA	王若岩,et al."Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets".AEROSPACE 10.9(2023):19.

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