| 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
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| Corresponding Author | Lin, Xin([email protected]) |
| Source Publication | ACTA ASTRONAUTICA
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| 2021-11-01 | |
| Volume | 188Pages:110-120 |
| ISSN | 0094-5765 |
| Abstract | 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. |
| Keyword | Hybrid rocket engine Fuel mass flow rate Tunable diode laser absorption spectroscopy Temperature Partial pressure |
| DOI | 10.1016/j.actaastro.2021.07.028 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:000693831100011 |
| WOS Keyword | REGRESSION RATE ; PERFORMANCE ; TEMPERATURE ; ENHANCEMENT ; MOTOR |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Funding Project | 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] |
| Funding Organization | National Natural Science Foundation of China |
| Classification | 二类/Q1 |
| Ranking | 1 |
| Contributor | Lin, Xin |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/87427 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 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 |
| Recommended Citation 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.Rp_Au:Lin, Xin |
| 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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| Jp2021F408.pdf（6496KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
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