IMECH-IR  > 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)1,2; Wang ZZ(王泽众)1,2; Lin X(林鑫)1; Li F(李飞)1; Li RJ(李仁杰)1,2; Li, Jing2,3; Zhang, Zhedian2,3; Liu, Yan2,3; Yu XL(余西龙)1,2
Corresponding AuthorLin, Xin(linxin_bit@imech.ac.cn) ; Li, Fei(lifei@imech.ac.cn)
Source PublicationEXPERIMENTAL THERMAL AND FLUID SCIENCE
2021-09-01
Volume127Pages:9
ISSN0894-1777
AbstractThe 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.
KeywordTunable diode laser absorption spectroscopy Hybrid rocket motor Temperature Partial pressure Combustion efficiency
DOI10.1016/j.expthermflusci.2021.110411
Indexed BySCI ; EI
Language英语
WOS IDWOS:000654338800001
WOS KeywordH2O CONCENTRATION ; TEMPERATURE ; SENSOR ; PERFORMANCE ; PRESSURE ; MOTOR ; FLOW ; TOMOGRAPHY ; PARAMETERS ; STRATEGY
WOS Research AreaThermodynamics ; Engineering ; Physics
WOS SubjectThermodynamics ; Engineering, Mechanical ; Physics, Fluids & Plasmas
Funding ProjectNational 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]
Funding OrganizationNational Natural Science Foundation of China ; Equipment Preresearch Foundation of National Defense Key Laboratory
Classification二类/Q1
Ranking1
ContributorLin, Xin ; Li, Fei
Citation statistics
Cited Times:3[WOS]   [WOS Record]     [Related Records in WOS]
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/86917
Collection高温气体动力学国家重点实验室
Affiliation1.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, Inst Engn Thermophys, Key Lab Adv Energy & Power, Beijing 100190, Peoples R China
Recommended Citation
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.
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