Numerical Investigation of the Combustion Characteristics of Splash Platelet Injector
Publication: Journal of Aerospace Engineering
Volume 35, Issue 4
Abstract
Platelet injectors are quite different from other injectors because of the specificity of the manufacturing technology and spray characteristics. In this study, a splash platelet injector was designed to obtain its combustion characteristics. Gaseous oxygen and methane were used as the propellants. A three-dimensional (3D) model was used with a reduced mechanism involving 16 species and 41 reactions. The influence of the structural parameters of the splash platelet injector, that is, the nondimensional parameter (), nozzle space (), and scale factor (), on combustion characteristics were analyzed. Results indicate that the temperature was nonuniform near the injector faceplate in all cases, and large corner recirculation zones were formed at the head of the combustion chamber. Combustion length () decreased as increased, and the shortest combustion length was obtained when . The combustion characteristics at slightly differed from those at , and the combustion characteristics in the front part of the combustor at were worse. The scale factor had little effect on component and temperature distribution.
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Data Availability Statement
Most data used or generated in the study are proprietary and cannot be provided in whole. Please address any queries to the corresponding author.
Acknowledgments
The financial support of the Natural Science Foundation of Hunan Province (Support Nos. 2020JJ5395 and 2020JJ4448) and Research Foundation of Education Bureau of Hunan Province (Support No. 19C1271) is gratefully acknowledged.
References
Choi, S., T. Y. Kim, H. K. Kim, I.-S. Jeung, J. Koo, and O. C. Kwon. 2017. “Combustion stability of gaseous and coaxial jet flames in a single-element combustor.” Energy 132 (Aug): 57–64. https://doi.org/10.1016/j.energy.2017.05.057.
Conley, A., A. Vaidyanathan, and C. Segal. 2015. “Heat flux measurements for a single-element, shear injector.” J. Spacecraft Rockets 44 (3): 633–639. https://doi.org/10.2514/1.26678.
Dai, J., and H. Yu. 2020. “Numerical and experimental investigations of geometrical parameters on injector.” Aerosp. Sci. Technol. 106 (10): 106187. https://doi.org/10.1016/j.ast.2020.106187.
Gao, Y., Z. Du, P. Jin, and G. Cai. 2009. “Numerical simulation on the combustion characteristic of shear coaxial injector.” J. Rocket Propul. 35 (5): 18–23. https://doi.org/10.3969/j.issn.1672-9374.2009.05.004.
GuoBiao, C., D. Jian, Z. Yang, and Y. NanJia. 2016. “Combustion behaviors of GO2/GH2 swirl-coaxial injector using non-intrusive optical diagnostics.” Acta Astronaut. 123 (Jun/Jul): 181–187. https://doi.org/10.1016/j.actaastro.2016.03.008.
Kahl, R. C., R. J. Labotz, and L. B. Bassham. 1974. “Platelet injectors for space shuttle orbit maneuvering engine.” In Proc., 10th AIAA/ASME/SAE/ASEE Jt. Propulsion Conf. Exhibition. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.1974-1108.
Kim, T. Y., S. Choi, Y. H. Kim, Y. J. Ahn, H. K. Kim, and O. C. Kwon. 2018. “Combustion characteristics of gaseous inverse coaxial jet flames in a single-element model combustor.” Energy 155 (Jul): 262–271. https://doi.org/10.1016/j.energy.2018.05.031.
Mueggenburg, H. H., and G. A. Repas. 1990. “A highly durable injector faceplate design concept for propellants.” In Proc., 10th AIAA/ASME/SAE/ASEE Jt. Propulsion Conf. Exhibition. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.1990-2181.
Perakis, N., J. Strauss, and O. J. Haidn. 2019. “Heat flux evaluation in a multi-element rocket combustor using an inverse heat transfer method.” Int. J. Heat Mass Transfer 142 (Sep): 118425. https://doi.org/10.1016/j.ijheatmasstransfer.2019.07.075.
Prakash, S., V. Raman, C. F. Lietz, W. A. Hargus Jr., and S. A. Schumaker. 2021. “Numerical simulation of a methane-oxygen rotating detonation rocket engine.” Proc. Combust. Inst. 38 (3): 3777–3786. https://doi.org/10.1016/j.proci.2020.06.288.
Wang, X., G. Cai, Y. Gao, and H. Huo. 2011. “High flowrate injector with gaseous hydrogen and gaseous oxygen.” Sci. China Technol. Sci. 11 (Sep): 2958–2973. https://doi.org/10.1007/s11431-011-4538-2.
Wang, X., G. Cai, and H. Huo. 2012a. “Numerical study of high-pressure combustion of a single-element injector.” Sci. China Technol. Sci. 55 (2): 2757–2768. https://doi.org/10.1007/s11431-012-4945-z.
Wang, X., G. Zhang, G. Cai, and H. Huo. 2012b. “Pressure and geometry scaling of gaseous hydrogen/gaseous oxygen shear-coaxial injectors.” J. Propul. Power 28 (6): 1368–1378. https://doi.org/10.2514/1.B34508.
Xiang, J., B. Sun, T. Wang, and J. Yuan. 2019. “Effects of angled film-cooling on cooling performance in a subscale thrust chamber.” Appl. Therm. Eng. 166 (Mar): 114627. https://doi.org/10.1016/j.applthermaleng.2019.114627.
Yin, L., J. E. J. Ding, and Y. Li. 2021. “An experimental study on the spray characteristics of splash platelet injector.” Acta Astronaut. 181 (8): 377–383. https://doi.org/10.1016/j.actaastro.2021.01.046.
Yin, L., and W. Liu. 2017. “Effect of structural parameters on the combustion performance of platelet engines.” IOP Conf. Ser.: Earth Environ. Sci. 104 (1): 012002. https://doi.org/10.1088/1755-1315/104/1/012002.
Yin, L., and W. Liu. 2018. “Gaseous film cooling investigation in a multi-element splash platelet injector.” Acta Astronaut. 144 (Mar): 353–362. https://doi.org/10.1016/j.actaastro.2017.12.045.
Yin, L., W. Liu, B. Shen, and H. Liu. 2018. “Numerical investigation on the film cooling performance in a multi-elements splash platelet injector.” Acta Astronaut. 152 (Nov): 458–467. https://doi.org/10.1016/j.actaastro.2018.08.043.
Yu, N., Y. Zhang, F. Li, and J. Dai. 2018. “Numerical and experimental investigations of single-element and double-element injectors using gaseous oxygen/gaseous methane.” Aerosp. Sci. Technol. 75 (12): 24–34. https://doi.org/10.1016/j.ast.2017.12.039.
Zips, J., C. Traxinger, and M. Pfitzner. 2019. “Time-resolved flow field and thermal loads in a single-element GOX/GCH_4 rocket combustor.” Int. J. Heat Mass Transfer 143 (Nov): 118474. https://doi.org/10.1016/j.ijheatmasstransfer.2019.118474.
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Published In
Journal of Aerospace Engineering
Volume 35 • Issue 4 • July 2022
Copyright
© 2022 American Society of Civil Engineers.
History
Received: May 7, 2021
Accepted: Feb 28, 2022
Published online: Apr 29, 2022
Published in print: Jul 1, 2022
Discussion open until: Sep 29, 2022
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