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8톤급 다단연소 사이클 로켓엔진 연소기 혼합헤드 설계

Design of Mixing Head Part of Combustion Chamber for 8tonf Class Staged Combustion Cycle Rocket Engine

  • 김동기 (한국항공우주연구원 발사체엔진팀) ;
  • 하성업 (한국항공우주연구원 발사체엔진팀) ;
  • 문일윤 (한국항공우주연구원 발사체엔진팀) ;
  • 문인상 (한국항공우주연구원 발사체엔진팀)
  • Kim, Dongki (Rocket Engine Team, Korea Aerospace Research Institute(KARI)) ;
  • Ha, Seong up (Rocket Engine Team, Korea Aerospace Research Institute(KARI)) ;
  • Moon, Il yoon (Rocket Engine Team, Korea Aerospace Research Institute(KARI)) ;
  • Moon, Insang (Rocket Engine Team, Korea Aerospace Research Institute(KARI))
  • 투고 : 2015.04.21
  • 심사 : 2015.06.26
  • 발행 : 2015.06.30

초록

Staged combustion cycle engines are well known to have high combustion efficiencies and specific impulse. In this study, design of mixing head part of combustion chamber for 8tonf class staged combustion cycle rocket engine (ES-08) was performed. Structural stability of the mixing head part of the combustion chamber is very important design factor because it is loaded by high temperature and high pressure of fuel and oxidizer as well as by thrust load simultaneously. Uniformity of flow distributions of the propellants to the injectors is also important factor. First, a basic configuration for the ES-08 mixing head part was designed on the basis of the structural design requirements. And then, the structural analyses were performed on the basic configuration as well as some of reinforced configurations. As the structural analyses results, the most stable configuration was selected for the ES-08 mixing head part. In order to examine the uniformity of the flow distributions of the propellants through the manifold of the mixing head, flow analysis was performed based on the selected configuration. The results of the flow analysis showed that the fuel and the oxidizer were uniformly supplied to the injector.

키워드

참고문헌

  1. Sutton, G. P., Rocket Propulsion Elements, 7th ed., Wiley, New York, pp. 221-227, 2001.
  2. Katorgin, B. I., Chvanov, V. K., Chelkis, F. J., and Tanner, L. G., "Oxidizer-Rich Staged Combustion Rocket Engines Use and Development in Russia," AIAA Paper 1995-3607, 1995.
  3. I. Y. Moon, S. H. Kang, S. Y. Lee, and S. H. Seo, "Study on Combustion Dynamic Characteristics of Oxygen-Rich Preburners," Journal of Propulsion and Power, vol. 30, no. 4, pp. 917-924, July-August 2014. https://doi.org/10.2514/1.B35140
  4. S. H. Kang, I. Y. Moon, and S. Y. Lee, "Experiments on an Oxidizer-Rich Preburner for Staged Combustion Cycle Rocket Engines," Journal of Propulsion and Power, vol. 30, no. 4, pp. 1098-1102, July-August 2014. https://doi.org/10.2514/1.B35202
  5. 문인상, 문일윤, 하성업, "소형 액체로켓용 산화제 과잉 예연소기 개발," 한국추진공학회 추계학술대회 논문집, pp.479-482, 2012.
  6. 강진모, 방정석, 이병호, 유재한, 문인상, 이수용 "소형 액체로켓용 산화제과잉 예연소기 제작," 한국추진공학회 추계학술대회 논문집, pp.533-536, 2010.
  7. 유철성, 이금오, 허성찬, 최환석, "7톤급 연소기 헤드부 구조설계," 한국추진공학회 춘계학술대회 논문집, pp.249-252, 2012.
  8. Huzel, D. K. and Huang, D. H., " Modern Engineering for of Liquid-propellant Rocket Engine," AIAA, vol. 147 Preogress in Astronautics & Aeronautics, 1992.
  9. 한상훈, 조미옥, 김성구, 최환석, "액체 로켓 엔진 연소기의 산화제 매니폴드 설계 및 유동해석" 한국항공우주학회 2013년도 추계학술대회 논문집, pp. 1452-1455, 2013.
  10. 김홍집, 최환석, "75톤급 가스 발생기 연료 및 산화제 매니폴드 유동해석을 통한 유동균일성 파악," 한국항공우주학회 2008년도 추계학술대회 논문집2, pp.855-858, 2008.
  11. R. Kindermann, et, al., Advanced Production and Process Technologies for Current and Future Thrust Chambers of Liquid Rocket Engines," 4th International Conference on Launcher Technology "Space Launcher Liquid Propulsion", 2002.
  12. Abaqus/CAE User's Manual, version 6.12.
  13. Fluent User's Manual, Version 14.