항공우주시스템공학회지 (Journal of Aerospace System Engineering)

  • 제18권1호
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  • Pages.53-63
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  • 2024
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  • 1976-6300(pISSN)
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  • 2508-7150(eISSN)
항공우주시스템공학회 (The Society for Aerospace System Engineering)
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450 N급 메탄-산소 로켓 엔진을 위한 스파크 토치 점화기 개발

Development of the Spark Torch Igniter for the 450 N-scale Methane-Oxygen Rocket Engine

  • 박신영 (국립한밭대학교 기계공학과) ;
  • 최이담 (국립한밭대학교 기계공학과) ;
  • 한은조 (국립한밭대학교 기계공학과) ;
  • 김진건 (국립한밭대학교 기계공학과) ;
  • 이다혜 (페리지에어로스페이스(주)) ;
  • 이은광 (페리지에어로스페이스(주)) ;
  • 이민우 (국립한밭대학교 기계공학과)
  • Sinyoung Park (Department of Mechanical Engineering, Hanbat National University) ;
  • Edam Choi (Department of Mechanical Engineering, Hanbat National University) ;
  • Eunjo Han (Department of Mechanical Engineering, Hanbat National University) ;
  • Jin Geon Kim (Department of Mechanical Engineering, Hanbat National University) ;
  • Dahae Lee (Perigee Aerospace Inc.) ;
  • Eunkwang Lee (Perigee Aerospace Inc.) ;
  • Minwoo Lee (Department of Mechanical Engineering, Hanbat National University)
  • 투고 : 2023.12.22
  • 심사 : 2024.01.12
  • 발행 : 2024.02.28
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초록

액체 로켓 엔진의 작동 신뢰성 확보를 위하여 높은 효율과 점화 성능을 가진 점화기가 필수적이다. 본 연구에서는 450 N급 메탄-산소 액체 로켓 엔진에 사용할 수 있는 스파크 토치 방식의 점화기를 개발하였으며, 이를 위해 수치해석, 제작 및 검증을 수행하였다. 구체적으로, 점화 성능 확보를 위해 점화기 출구에서의 엔탈피를 최대화하도록 질량 유량, 노즐 면적비, 연료-산화제 혼합비 및 세장비를 설계변수로 설정하고 파라메트릭 해석을 수행하였으며, 3차원 반응 유동 수치해석을 통해 출구 열량을 산출하였다. 나아가, 도출된 설계를 바탕으로 점화기를 제작하여 연소 실험을 수행하였으며, 안전을 고려하여 설정한 최대 압력 이내에서 수치해석 결과에 부합하는 점화 성능 확보가 가능한 것으로 확인되었다. 본 연구를 통해 설계 및 제작한 점화기는 차후 소형 우주발사체 상단 엔진 등 실제 추진 시스템 구성에 기여할 수 있을 것으로 판단된다.

Adopting an engine igniter with high efficiency and ignition performance is essential for reliable operation of liquid rocket engines. In this study, we developed a spark torch igniter for a 450 N-scale methane-oxygen liquid rocket engine by conducting numerical analyses, igniter manufacturing and validation. Specifically, we conducted a parametric study for maximizing the enthalpy at the igniter exit, specifically by adjusting the mass flow rate, nozzle area ratio, fuel-oxidizer mixture ratio, and the igniter length-to-diameter. The heat transferred via the igniter nozzle exit was computed using 3-dimensional numerical simulations. We also manufactured and tested the igniter based on a deduced design to confirm ignition performance of the designed spark torch igniter. The igniter developed through this study could contribute to the development of practical propulsion systems such as upper-stage engines of small launch vehicles.

키워드

참고문헌

  1. K. Lee, J. Cha, S. Ko, S.-Y. Park, E. Jung, "Mathematical Modeling and Simulation for Steady State of a 75-ton Liquid Propellant Rocket Engine," Journal of Aerospace System Engineering Vol. 11, No. 5, pp. 6-12, 2017 https://doi.org/10.20910/JASE.2017.11.5.6
  2. E. A. Fletcher, G. Morrell, "Ignition in liquid propellant rocket engines," Progress in Combustion Science and Technology, Vol. 1, pp. 183-215, 1960 https://doi.org/10.1016/B978-0-08-009468-7.50010-1
  3. S.-Y. Park, W.-S. Seol, "Numerical Analysis on the Startup of a Rocket Engine," Journal of the Korean Society of Propulsion Engineers Vol. 11, No. 5, pp. 60-71, 2007
  4. S. Kim, M. Shin, J. Cha, Y. Ko, "Evaluation of Ignition Performance of Green Hypergolic Propellant," Journal of Aerospace System Engineering Vol. 17, No. 1, pp. 51-58, 2023 https://doi.org/10.20910/JASE.2023.17.1.51
  5. T. Neill, D. Judd, E. Veith, and D. Rousar, "Practical uses of liquid methane in rocket engine applications," Acta Astronautica Vol. 65, No. 5-6, pp. 696-705, 2010. https://doi.org/10.1016/j.actaastro.2009.01.052
  6. S. A. O'Briant, S. B. Gupta, S. S. Vasu, "Laser ignition for aerospace propulsion," Propulsion and Power Research Vol. 5, No. 1, pp. 1-21, 2016. https://doi.org/10.1016/j.jppr.2016.01.004
  7. J, S, Choi, H, I, Huh W, K, Ki, "Technology and Development Trends of Small Launch Vehicles," Journal of the Korean Society of Propulsion Engineers Vol. 24, No. 5, pp. 91-102, 2020 https://doi.org/10.6108/KSPE.2020.24.5.091
  8. C. Hwang, J. Lee, C. Kim, J.-S. Jeon, J.-Y. Park, K.-J. Lee, N.-K. Cho, S. H. Kim, Y. Han, "A Study on Purge Gas Inflow according to Valve Operation Sequence during Staged Combustion Cycle Engine Reignition Test," Journal of the Korean Society of Propulsion Engineers Vol. 26, No. 4, pp. 64-71, 2022 https://doi.org/10.6108/KSPE.2022.26.4.064
  9. O. Shynkarenko, Olexiy, S. Domenico, "Oxygen-Methane Torch Ignition System for Aerospace Applications," Aerospace Vol. 7, No. .8, pp. 114, 2020
  10. P, J, Robinson, E, M, Veith, E, A, Hurlbert, R, Jimenez, T, D, Smith, "445N (100-lbf) LO2/LCH4 reaction control engine technology development for future space vehicles," Acta Astronautica, Vol. 66, No. 5-6, 836-843, 2010 https://doi.org/10.1016/j.actaastro.2009.08.026
  11. S. D. Rosenberg, ""Ignition system for oxygen/hydrogen auxiliary propulsion systems," Acta Astronautica, Vol. 10, No. 1, pp. 19-30, 1983 https://doi.org/10.1016/0094-5765(83)90014-0
  12. C, W, Kim, B, G, Lim, K, J, Lee, J, S, Park, "A Study on Fuel Selection for Next-Generation Launch Vehicles," Journal of the Korean Society of Propulsion Engineers Vol. 25, No. 3, pp. 62-80, 2021 https://doi.org/10.6108/KSPE.2021.25.3.062
  13. W, M, Marshall., J, E, Kleinhenz, "Hot-Fire Testing of 100 lbf LOX/LCH4 Reaction Control Engine at Altitude Conditions," 2010 JANNAF JPM/MSS/LPS/SPS Joint Subcommittee Meeting. No. E-17514. 2010.
  14. L, E, Sanchez, "Development and testing of oxygen/methane torch igniter technologies for propulsion systems," Ph.D. Thesis, University of Texas at El Paso, 2016.
  15. L. Konozsy, "A New Hypothesis on the Anisotropic Reynolds Stress Tensor for Turbulent Flows," Springer International Publishing, 2019.
  16. C. Wang, L. Lesshafft, K. Oberleithner, "Global linear stability analysis of a flame anchored to a cylinder," Journal of Fluid Mechanics, Vol. 951, A27, 2022.
  17. M. Lee, "Early warning detection of thermoacoustic instability using three-dimensional complexity-entropy causality space," Experimental Thermal and Fluid Science, Vol. 130, pp. 110517, 2022.
  18. S. Guk, S. Seo, M. Lee, "Thermoacoustic Dynamics in an Annular Model Gas-turbine Combustor under Transverse Stochastic Forcing," Journal of The Korean Society Combustion, Vol. 28, No. 3, pp. 20-27, 2023. https://doi.org/10.15231/jksc.2023.28.3.020