Characterizing combustion of a hybrid rocket using laser absorption spectroscopy

doi:10.1016/j.expthermflusci.2021.110411

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

	Characterizing combustion of a hybrid rocket using laser absorption spectroscopy
	Fang SH(方思晗)2,3; Wang ZZ(王泽众)2,3; Lin X(林鑫)3; Li F(李飞)3; Li RJ(李仁杰)2,3; Li, Jing 1,2; Zhang, Zhedian 1,2; Liu, Yan 1,2; Yu XL(余西龙)2,3
刊名	EXPERIMENTAL THERMAL AND FLUID SCIENCE
	2021-09-01
卷号	127 页码:9
关键词	Tunable diode laser absorption spectroscopy Hybrid rocket motor Temperature Partial pressure Combustion efficiency
ISSN号	0894-1777
DOI	10.1016/j.expthermflusci.2021.110411
通讯作者	Lin, Xin(linxin_bit@imech.ac.cn) ; Li, Fei(lifei@imech.ac.cn)
英文摘要	The combustion of an oxygen/paraffin hybrid rocket motor was experimentally characterized. Firing tests were conducted for different oxidizer mass fluxes ranging from 2.47 to 3.40 g/ (cm2.s). Variations in temperature and H2O partial pressure at the nozzle exit were diagnosed using mid-infrared tunable diode laser absorption spectroscopy (TDLAS) based on H2O absorption near 2.5 mu m. Three H2O absorption lines were simultaneously covered by only one distributed feedback (DFB) laser using scanned-wavelength direct absorption (DA) mode with 2.0 kHz repetition rate. Measurement uncertainty was analyzed in detail considering line-strength uncertainty and Voigt fitting residuals. A two-dimensional (2D) model of the nozzle was constructed using the ANSYS FLUENT CFD software package. The combustion efficiency of the hybrid rocket motor was evaluated from the perspectives of chemical reaction and heat release, respectively, based on TDLAS results and CFD simulations. The effectiveness of the evaluation was validated by comparing its results with characteristic velocity (C*)-based combustion efficiency. Finally, comparisons of combustion efficiencies among different cases show that increasing the oxidizer mass flux or oxidizer-to-fuel ratio improves the combustion efficiency of the hybrid rocket motor under our experimental conditions.
分类号	二类/Q1
资助项目	National Natural Science Foundation of China[11802315] ; National Natural Science Foundation of China[11872368] ; National Natural Science Foundation of China[12072355] ; National Natural Science Foundation of China[11927803] ; Equipment Preresearch Foundation of National Defense Key Laboratory[6142701190402] ; Equipment Preresearch Foundation of National Defense Key Laboratory[BM2019001]
WOS关键词	H2O CONCENTRATION ; TEMPERATURE ; SENSOR ; PERFORMANCE ; PRESSURE ; MOTOR ; FLOW ; TOMOGRAPHY ; PARAMETERS ; STRATEGY
WOS研究方向	Thermodynamics ; Engineering ; Physics
语种	英语
WOS记录号	WOS:000654338800001
资助机构	National Natural Science Foundation of China ; Equipment Preresearch Foundation of National Defense Key Laboratory
其他责任者	Lin, Xin ; Li, Fei
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/86916]
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.Chinese Acad Sci, Inst Engn Thermophys, Key Lab Adv Energy & Power, Beijing 100190, Peoples R China 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, 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	Fang SH,Wang ZZ,Lin X,et al. Characterizing combustion of a hybrid rocket using laser absorption spectroscopy[J]. EXPERIMENTAL THERMAL AND FLUID SCIENCE,2021,127:9.
APA	方思晗.,王泽众.,林鑫.,李飞.,李仁杰.,...&余西龙.(2021).Characterizing combustion of a hybrid rocket using laser absorption spectroscopy.EXPERIMENTAL THERMAL AND FLUID SCIENCE,127,9.
MLA	方思晗,et al."Characterizing combustion of a hybrid rocket using laser absorption spectroscopy".EXPERIMENTAL THERMAL AND FLUID SCIENCE 127(2021):9.