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An Experimental Study of the Rocket Preburner Injector  

Choi, Seong-Man (전북대학교 항공우주공학과, 공업기술연구센터)
Yang, Joon-Ho (전북대학교 항공우주공학과, 공업기술연구센터)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.11, no.1, 2007 , pp. 57-63 More about this Journal
Abstract
The oxidizer-rich preburner is applied to the high efficiency closed cycle rocket propulsion system. This system is generally operated on oxidizer-fuel mixture ratio over than 50. The spray quality and mixing performance are very important for stable combustion of this preburner. This paper presents basic design concept and spray characteristic of the oxidizer-rich preburner injector and this result could be applied to the development of the oxidizer rich preburner system.
Keywords
Oxidizer-rich preburner; Swirl injector; Discharge coefficient; Spray characteristics;
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  • Reference
1 L. Schoenman, "Fuel/oxidizer-rich high -pressure preburners," NASA CR 165404, October, l981
2 V. Barzarov, "Development of Russian Rocketry-Historical and Technical Aspects", 6th NRL Workshop, Issues on Rocket Engine, 2005
3 V. Barzarov, "lecture on Liquid Propellant Rocket Engine Injectors", Seoul National University, Jan. 28-Feb. 8, 2002
4 G. P. Sutton, "Rocket propulsion elements", Seventh Edition, 2001, pp.197-265