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

doi:10.3390/aerospace10090759

CORC > 力学研究所 > 中国科学院力学研究所 > 高温气体动力学国家重点实验室

	Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets
	Wang, Ruoyan 1,2; Lin, Xin 2; Wang, Zezhong 2; Wu, Kun 2; Zhang, Zelin 2; Luo, Jiaxiao 1,2; Li, Fei 2; Yu, Xilong 1,2
刊名	AEROSPACE
	2023-09-01
卷号	10 期号:9 页码:19
关键词	hybrid rocket engine swirl-radial injection regression rate flame images combustion efficiency
DOI	10.3390/aerospace10090759
通讯作者	Lin, Xin(linxin_bit@imech.ac.cn) ; Wang, Zezhong(wangzezhong@imech.ac.cn)
英文摘要	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.
WOS研究方向	Engineering
语种	英语
WOS记录号	WOS:001072464500001
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/93102]
专题	力学研究所_高温气体动力学国家重点实验室
通讯作者	Lin, Xin; Wang, Zezhong
作者单位	1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China 2.Chinese Acad Sci, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Wang, Ruoyan,Lin, Xin,Wang, Zezhong,et al. Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets[J]. AEROSPACE,2023,10(9):19.
APA	Wang, Ruoyan.,Lin, Xin.,Wang, Zezhong.,Wu, Kun.,Zhang, Zelin.,...&Yu, Xilong.(2023).Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets.AEROSPACE,10(9),19.
MLA	Wang, Ruoyan,et al."Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets".AEROSPACE 10.9(2023):19.