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Atomizing Characteristics of Coaxial Porous Injectors

다공성재를 이용한 동축형 분사기의 미립화특성

  • 김도헌 (한국항공대학교 대학원 항공우주 및 기계공학과) ;
  • 신정환 (한국항공대학교 대학원 항공우주 및 기계공학과) ;
  • 이인철 (한국항공대학교 대학원 항공우주 및 기계공학과) ;
  • 구자예 (한국항공대학교 항공우주 및 기계공학부)
  • Received : 2012.02.24
  • Accepted : 2012.03.10
  • Published : 2012.03.30

Abstract

To improve the mixing and atomizing performance at the center region of the conventional coaxial shear injector spray, the concept of a coaxial porous injector was invented. This novel injection concept for liquid rocket engines utilizes the Taylor-Culick flow in the cylindrical porous tube. The 2-dimensional injector, which can be converted in three injection configurations, was fabricated, and several cold flow tests using water-air simulant propellant was performed. The hydraulic characteristics and the effects of a gas flow condition on the spray pattern and the Sauter mean diameter (SMD) was analyzed for each configuration. The atomizing mechanism of coaxial porous injector was different with the coaxial shear injector, and it was explained by the momentum of the gas jet, which is injected normally against the center liquid column, and by the secondary disintegration at the wavy interface of liquid jet, which was generated at the recessed region. The SMD of 2D coaxial porous injector, which has higher gas momentum, was measured and it shows better atomizing performance at the center and outer side of spray than the 2D coaxial shear injector.

Keywords

References

  1. D. K. Huzel and D. H. Huang, "Design of Liquid Propellant Rocket Engines", NASA SP-125.
  2. J. Lux, D. Suslov and O. Haidn, "Porous Injectors in Cryogenic Liquid Propellant Rocket Engines at Suband Super Critical Pressures", 46th AIAA aerospace Science Meeting and Exhibit, AIAA2008-947, 2008.
  3. R. D. Woodward, S. Pal, S. Farhangi, G. E. Jensen and R. J. Santoro, "LOX/GH2 Shear Coaxial Injector Atomization Studies: Effect of Recess and Non- Concentricity", 45th AIAA Aerospace Sciences Meeting and Exhibit, AIAA 2007-571, 2007.
  4. Y. Nunome, H. Tamura, T. Onodera, H. Sakamoto, A. Kumakawa and T. Inamura, "Effect of Liquid Disintegration on Flow Instability in a Recessed Region of a Shear Coaxial Injector", 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA 2009-5389, 2009.
  5. S. A. Rahman, "Primary Atomization Study of a Swirl Coaxial Liquid Propellant Rocket Injector", Ph. D. Thesis in Mechanical Engineering, The Pennsylvania State University, 1997.
  6. S. A. Rahman, S. Pal and R. J. Santoro, "Swirl Coaxial Atomization: Cold-Flow and Hot-fire Experiments", AIAA 95-0381, 1995.
  7. V. M. Polyaeva, V. M. Zhdanov and B. V. Kichatov, "Study of The Operation of a Gas-liquid Atomizer with a Porous Mixing Element", Journal of Engineering Physics and Thermophysics, Vol. 73, No. 3, 2000.
  8. J. Deeken, D. Suslov, O. Haidn and S. Schlechtriem, "Design and testing of a porous injector head for transpiration cooled combustion chambers", 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, AIAA 2010-1595, 2010.
  9. V. G. Bazarov, "New class of Porous Injectors for Combustion Chambers and Gas Generators", AIAA/ SAE/ASME/ASEE 29th Joint Propulsion Conference and Exhibit, AIAA 93-1955, 1993.
  10. E. Sozer, W. Shyy and S. Thakur, "Multi-Scale Porous Media Modeling for Liquid Rocket Injector Applications", 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA 2006-5044, 2006.
  11. J. Griffond, G. Casalis, "Secondary Instability of The Planar Taylor Flow", 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA 2000-3806, 2006.
  12. R. J. Santoro and C. L. Merkle, "Main Chamber and Preburner Injector Technology", Final Report for NASA Cooperative Agreement Grant No. NCC 8-46.

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  1. Combustion Performance of a Coaxial Porous Injector using Ethanol/N2O Propellant vol.17, pp.5, 2013, https://doi.org/10.6108/KSPE.2013.17.5.037