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http://dx.doi.org/10.5139/JKSAS.2005.33.6.064

Combustion Characteristics of Fuel-rich Gas Generator with Impinging Injector for a Liquid Rocket Engine  

Han, Yeoung-Min (한국항공우주연구원)
Kim, Seung-Han (한국항공우주연구원)
Lee, Kwang-Jin (한국항공우주연구원)
Moon, Il-Yoon (한국항공우주연구원)
Seol, Woo-Seok (한국항공우주연구원)
Lee, Chang-Jin (건국대학교 항공우주공학과)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.33, no.6, 2005 , pp. 64-70 More about this Journal
Abstract
The overall results of hot firing tests of fuel-rich gas generator with impinging injector at design and off-design points are described. The gas generator consists of an injector head with impinging injector, a water cooled combustor wall, a turbulence ring to enhance mixing, an instrument ring measuring temperature and pressure and a nozzle. The combustion tests were successfully performed without damage of gas generator. Test results show that the outlet temperature is not dependent on residence time of hot gas within 4～6msec but dependent on chamber pressure. The relation between outlet temperature and combustion efficiency resulting from measured pressure, mass flow rate and area of nozzle throat is shown. The overall O/F ratio is the critical parameter to determine the outlet temperature and the linear correlation between two parameters is established.
Keywords
Impinging Injector; Fuel Rich; O/F Ratio; Outlet Temperature; Combustion Efficiency;
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  • Reference
1 Huzel, D. K. and Huang, D. H., 'Modern Engineering for Design of Liquid-Propellant Rocket Engines,' AIAA, 1992
2 H. W. Douglass, H. W. Schmidt, L. Levinson, 'Liquid Propellant Gas Generators', NASA SP-8081, 1972
3 NAL, 'NAL TM-354' 1974
4 권순탁, 이창진, '액체로켓 농후 가스발생기 최적설계', 한국항공우주학회지, 제32권 제5호, 2004, pp. 91-96
5 한영민 등, '충돌형 분사기 형태의 액체로켓엔진용 가스발생기 연소성능시험', 한국추진공학회지, 제8권 제2호, 2004, pp. 10-17
6 권순탁, 이창진, '액체로켓 가스발생기용 F-O-F 인젝터의 설계와 분사특성', 한국항공우주학회 추계학술발표회 논문집(II), 2003, pp. 1039-1043