Determining the time-resolved mass flow rates of hybrid rocket fuels using laser absorption spectroscopy

doi:10.1016/j.actaastro.2021.07.028

	Determining the time-resolved mass flow rates of hybrid rocket fuels using laser absorption spectroscopy
	Wang ZZ(王泽众)1,2 ; Lin X(林鑫)1 ; Li F(李飞)1 ; Peng JL(彭锦龙)1; Liu, Yan2,3 ; Zhang ZL(张泽林)1; Fang SH(方思晗)1,2; Yu XL(余西龙)1,2
通讯作者	Lin, Xin(linxin_bit@imech.ac.cn)
发表期刊	ACTA ASTRONAUTICA
	2021-11-01
卷号	188 页码:110-120
ISSN	0094-5765
摘要	A non-intrusive method for determining the time-resolved fuel mass flow rate in a hybrid rocket engine is proposed based on tunable diode laser absorption spectroscopy (TDLAS). The present work performed experimental tests using oxygen/paraffin as the propellant in a laboratory-scale hybrid rocket engine, applying oxidizer-to-fuel ratios in the range of 2.5-2.9 corresponding to combustion chamber pressures of 1.68-2.46 MPa. Variations in temperature and H2O partial pressure at the nozzle outlet were determined adopting TDLAS based on H2O absorption near 2.5 Three H2O absorption lines at 4029.5, 4030.6 and 4030.7 cm(-1) were simultaneously measured using only one diode laser at 2.0 kHz repetition rate and adopting a scanned-wavelength direct absorption strategy. The airflow velocity at the nozzle outlet was ascertained in two-dimensional numerical simulations. In this manner, the time-resolved fuel mass flow rate participating in combustion can be derived from the ideal state equation. A detailed discussion of the measurement uncertainty was provided herein considering the influence from determination of temperature, H2O partial pressure and velocity. The effectiveness of the novel method was validated by comparing its results with that acquired with the traditional weightloss technique. Finally, it is initially analyzed that the combustion efficiency of pure paraffin fuel gradually increases during the combustion process according to the measurement results.
关键词	Hybrid rocket engine Fuel mass flow rate Tunable diode laser absorption spectroscopy Temperature Partial pressure
DOI	10.1016/j.actaastro.2021.07.028
收录类别	SCI ; EI
语种	英语
WOS记录号	WOS:000693831100011
关键词[WOS]	REGRESSION RATE ; PERFORMANCE ; TEMPERATURE ; ENHANCEMENT ; MOTOR
WOS研究方向	Engineering
WOS类目	Engineering, Aerospace
资助项目	National Natural Science Foundation of China[11802315] ; National Natural Science Foundation of China[11872368] ; National Natural Science Foundation of China[11927803] ; National Natural Science Foundation of China[12072355] ; [BM2019001]
项目资助者	National Natural Science Foundation of China
论文分区	二类/Q1
力学所作者排名	1
RpAuthor	Lin, Xin
引用统计	被引频次：9[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/87427
专题	高温气体动力学国家重点实验室
作者单位	1.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China; 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China; 3.Chinese Acad Sci, Key Lab Adv Energy & Power, Inst Engn Thermophys, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Wang ZZ,Lin X,Li F,et al. Determining the time-resolved mass flow rates of hybrid rocket fuels using laser absorption spectroscopy[J]. ACTA ASTRONAUTICA,2021,188:110-120.
APA	王泽众.,林鑫.,李飞.,彭锦龙.,Liu, Yan.,...&余西龙.(2021).Determining the time-resolved mass flow rates of hybrid rocket fuels using laser absorption spectroscopy.ACTA ASTRONAUTICA,188,110-120.
MLA	王泽众,et al."Determining the time-resolved mass flow rates of hybrid rocket fuels using laser absorption spectroscopy".ACTA ASTRONAUTICA 188(2021):110-120.

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