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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.28 SNIP: 0.421 CiteScore™: 0.9

ISSN Печать: 2150-766X
ISSN Онлайн: 2150-7678

Выпуски:
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International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2012001351
pages 155-168

LIQUID OXYGEN VAPORIZATION TECHNIQUES FOR SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINES

Saburo Yuasa
Tokyo Metropolitan University, 6-6 Asahigaoka, Hino-city, Tokyo, 191-0065, Japan
Koki Kitagawa
Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan; The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-0033, Japan
Toshiaki Sakurazawa
Tokyo Metropolitan University, 6-6 Asahigaoka, Hino-city, Tokyo, 191-0065, Japan
Ikuno Kumazawa
Tokyo Metropolitan University, 6-6 Asahigaoka, Hino-city, Tokyo, 191-0065, Japan
Takashi Sakurai
Tokyo Metropolitan University, 6-6 Asahigaoka, Hino-city, Tokyo, 191-0065, Japan

Краткое описание

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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