Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Visualization of Transient Ignition Flow-field in a 50 N Scale N2O/C2H5OH Thruster

50 N급 아산화질소/에탄올 추력기의 점화 과도 유동장 가시화

  • Kim, Dohun (Department of Aerospace and Mechanical Engineering, Graduate School of Korea Aerospace University) ;
  • Park, Jaehyeon (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Yu, Myunggon (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Lee, Kyungeun (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Koo, Jaye (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
  • Received : 2013.12.10
  • Accepted : 2014.11.15
  • Published : 2014.12.01
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Abstract

The combustion flowfield at the near-injector region of a 50 N scale $N_2O/C_2H_5OH$ thruster was visualized using shadowgraph technique. The explosive ignition was occurred at the design spray condition, and the expanding combustion gas quenched the flame immediately. Approximately after 83 ms from the initial ignition, the propellant spray was re-ignited, and the flame was stabilized after 23 ms elapsed. In the increased oxidizer flow rate condition, the transient pressure at the moment of ignition was smoother than explosive ignition, and the blow down phenomenon was not appeared in the same operating sequence. In addition, the flame was stabilized within 17 ms, and it is caused by improved propellants mixing before ignition.

아산화질소/에탄올 추진제 조합을 사용하는 50 N급 추력기 분사기 인접부에서 shadowgraph 기법을 사용하여 연소 유동장을 가시화하였다. 설계 작동조건에서 폭발성 점화가 일어났으며, 급격히 팽창하는 연소가스에 의해 순간적으로 소염되는 현상이 관찰되었다. 최초 점화로부터 약 83 ms 뒤 추진제 분무는 재점화 되었으며, 그로부터 약 23 ms 후 화염이 안정화되는 것이 관찰되었다. 동일한 시퀀스에서 설계 조건보다 산화제 유량을 증가시킨 경우, 소염 현상 없이 완만한 연소 압력 과도 특성을 보였으며 최초 점화로부터 약 17 ms이내에 화염 안정화가 이루어졌다. 이는 점화 직전의 연소기 내부 미연 추진제 혼합 향상에 의한 것으로 생각되었다.

Keywords

References

  1. Bazarov, V., Yang, V. and Puri, P., Liquid Rocket Thrust Chambers: Aspect of Modeling, Analysis, and Design, American Institute of Aeronautics and Astronautics, Reston, VA, U.S.A., 2004.
  2. Farago, Z. and Chigier, N., "Morphological Classification of Disintegration of Round Jets in a Coaxial Air Stream," Atomization and Sprays, Vol. 2, Issue 2, pp. 137-153, 1992. https://doi.org/10.1615/AtomizSpr.v2.i2.50
  3. Lasheras, J.C., Villermaux, E. and Hopfinger, E.J., "Break-up and Atomization of a Round Water Jet by a High-speed Annular Air Jet," Journal of Fluid Mechanics, Vol. 357, pp. 351-379, 1998. https://doi.org/10.1017/S0022112097008070
  4. Varga, C.M., Lasheras, J.C. and Hopfinger, E.J., "Initial Breakup of a Small-diameter Liquid Jet by a High-speed Gas Stream," Journal of Fluid Mechanics, Vol. 497, pp. 405-434, 2003. https://doi.org/10.1017/S0022112003006724
  5. Gautam, V. and Gupta, A.K., "Cryogenic Flow and Atomization from a Coaxial Injector," Journal of Propulsion and Power, Vol. 25, No. 1, pp. 33-39, 2009. https://doi.org/10.2514/1.28921
  6. Branam, R. and Mayer, W., "Characterization of Cryogenic Injection at Supercritical Pressure," Journal of Propulsion and Power, Vol. 19, No. 3, pp. 342-355, 2003. https://doi.org/10.2514/2.6138
  7. Lux, J. and Haidn, O.J., "Flame Stabilization in High-Pressure Liquid Oxygen/Methane Rocket Engine Combustion," Journal of Propulsion and Power, Vol. 25, No. 1, pp. 15-23, 2009. https://doi.org/10.2514/1.36852
  8. Yang, B., Cuoco, F. and Oschwald, M., "Atomization and Flames in LOX/H2- and LOx/CH4- Spray Combustion," Journal of Propulsion and Power, Vol. 23, No. 4, pp. 763-771, 2007. https://doi.org/10.2514/1.26538
  9. Locke, J.M., Pal, S., Woodward, R.D. and Santoro, R.J., "High Speed Visualization of LOX/GH2 Rocket Injector Flowfield: Hot-Fire and Cold-Flow Experiments," 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Nashville, TN, U.S.A., AIAA 2010-7145, Jul. 2010.
  10. Salgues, D., Mouis, A.G., Lee, S.Y., Kalitan, D., Pal, S. and Santoro, R.J., "Shear and Swirl Coaxial Injector Studies of LOX/GCH4 Rocket Combustion Using Non-Intrusive Laser Diagnostics," 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, U.S.A., AIAA 2006-757, Jul. 2006.
  11. Cuoco, F., Yang, B., Bruno, C., Haidn, O.J. and Oschwald, M., "Experimental Investigation on LOx/CH4 Ignition," 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Fort Lauderdale, FL, U.S.A., AIAA 2004-4005, Jul. 2004.