Publicado 6 números por año
ISSN Imprimir: 2150-766X
ISSN En Línea: 2150-7678
Indexed in
LIQUID OXYGEN VAPORIZATION TECHNIQUES FOR SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINES
SINOPSIS
The authors have been developing a 1500 N-thrust, swirling-oxidizer-flow-type hybrid rocket engine. The oxygen to which swirl is applied should be in a gaseous state to increase the engine performance. Two methods were proposed to vaporize liquid oxygen (LOX): a regenerative-cooling LOX-vaporization nozzle and a LOX-vaporization burner. We fabricated a LOX-vaporization nozzle with 30 rectangular channels, each with a depth of 1.0 mm, and conducted burning experiments. The experiments showed that rapid ignition and stable combustion without combustion oscillation were achieved, and LOX increased in temperature and sufficiently vaporized while passing through the nozzle. There was no essential problem in vaporizing LOX with the nozzle. The feasibility of the LOX-vaporization burner using combustion of polymethyl methacrylate (PMMA) in LOX was examined from the viewpoint of thermal energy and a preliminary burning experiment was conducted. The burning amount of PMMA to vaporize the LOX propellant for a 1500-N-thrust, hybrid rocket engine was estimated to be at most 3% of the fuel propellant of the rocket. PMMA could burn steadily and safely in LOX and vaporize a large amount of it. The trade-off between the two methods suggested that the vaporization burner had the advantage of a compact and simple structure when compared with the LOX-vaporization nozzle.
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Kamps Landon T., Sakurai Kazuhito, Ozawa Kohei, Nagata Harunori, Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using N2O/HDPE, AIAA Propulsion and Energy 2019 Forum, 2019. Crossref
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Kamps Landon, Hirai Shota, Sakurai Kazuhito, Viscor Tor, Saito Yuji, Guan Raymond, Isochi Hikaru, Adachi Naoto, Itoh Mitsunori, Nagata Harunori, Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using Oxygen/High-Density Polyethylene, Journal of Propulsion and Power, 36, 3, 2020. Crossref
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Ozawa Kohei, Shimada Toru, Performance of Mixture-Ratio-Controlled Hybrid Rockets for Nominal Fuel Regression, Journal of Propulsion and Power, 36, 3, 2020. Crossref
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Kojima Hiroki, Kamps Landon T., Nobuhara Yuki, Nagata Harunori, Valembois Thomas, Cottenot Camille, Progress Towards Graphite Nozzle Cooling for Throat Erosion Suppression, AIAA AVIATION 2022 Forum, 2022. Crossref