Journal of the Korean Society of Visualization (한국가시화정보학회지)

The Korean Society of Visualization (한국가시화정보학회)
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A Visualization of the Spray from Small Liquid-rocket Engine Injector by Dual-mode Phase Doppler Anemometry

이중모드 위상도플러 속도계측기법에 의한 소형 액체로켓엔진 인젝터 분무의 가시화

  • 정훈 (부경대학교 대학원 에너지시스템공학과) ;
  • 김정수 (부경대학교 기계공학과) ;
  • 배대석 (부경대학교 기계공학과) ;
  • 권오붕 (부경대학교 기계공학과)
  • Received : 2010.12.14
  • Accepted : 2010.12.29
  • Published : 2010.12.31
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Abstract

A focus is given to the breakup behavior of spray droplets issuing from a nonimpinging-type injector. The analysis has been carried out experimentally by means of the dual-mode phase Doppler anemometry (DPDA). Spray characteristic parameters in terms of axial velocity, mean diameter, velocity fluctuation, and span (width of the size distribution) of droplets are measured down the geometric axis of a nozzle orifice and on the plane normal to the spray stream with the injection pressure variations. As the injection pressure increases, the velocity and its fluctuation become higher, whereas the droplet sizes get smaller. It is also shown that the magnitudes of those parameters are smoothed out by dispersion when the droplets move downstream as well as outwardly. The atomization process is significantly influenced by the injection pressure rather than the traveling distance in the experimental condition presented.

Keywords

References

  1. Kim, J. S., Park, J., Kim, S., Choi, J. and Jang, K. W., 2006, “Test and Performance Evaluation of Small Liquid-monopropellant Rocket Engines”, 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit”, AIAA-2006-4388.
  2. Law, C. K., 1911, “Mechanics of Flame Stabilization in Subsonic and Supersonic Flow”, Major Research Topics in Combustion, Springer-Verlag.
  3. Heidmann, M. F., Priem, R. J. and Humphrey, J. C., 1957, “A Study of Sprays Formed by Two Impinging Jets”, NACA TN 3835.
  4. Ryan, H. M., Anderson, W. E., Pal, S. and Santoro, R. J., 1995, “Atomization Characteristics of Impinging Liquid Jets”, Journal of Propulsion and Power, Vol. 11(1), pp. 135-145. https://doi.org/10.2514/3.23851
  5. Marchione, T., Allouis, C., Amoresano, A. and Beretta, F., 2007, “Experimental Investigation of a Pressure Swirl Atomizer Spray”, Journal of Propulsion and Power, Vol. 23(5), pp. 1096-1101. https://doi.org/10.2514/1.28513
  6. Kim, J. S. and Kim, J. S., 2008, “A Characterization of the Spray Evolution by Dual-mode Phase Doppler Anemometry in an Injector of Liquid-propellant Thruster”, Journal of Mechanical Science and Technology, Vol. 23(6), pp. 1637-1649. https://doi.org/10.1007/s12206-009-0209-7
  7. Jung, H. and Kim J. S., 2008, “Spatial Distribution Characteristics of Small LRE-injector's Spray-droplet According to the Variation of Fuel-injection Pressure”, Journal of the Korean Society of Propulsion Engineers, Vol. 12(5), pp. 1-8.
  8. Edwards, C. F. and Marx, K. D., 1992, “Analysis of the Ideal Phase-Doppler System: Limitations Imposed by the Single-particle Contraint”, Atomization and Sprays, Vol. 2(3), pp. 319-366. https://doi.org/10.1615/AtomizSpr.v2.i3.70
  9. Lefebvre, A. H., 1989, “Atomization and Sprays”, Hemisphere Publishing Corp., New York, pp. 367-409.
  10. Schmidt, E. W., 2001, “Hydrazine and Its Derivatives: Preparation, Properties, Applications”, 2nd Ed., John Wiley & Sons, Inc., New York.

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