Journal of ILASS-Korea (한국분무공학회지)

Institute for Liquid Atomization and Spray Systems-Korea (한국분무공학회)
권호 표지
DOI QR코드

DOI QR Code

A Study on the Thrust Throttling Using Gas Injection in Swirl Injectors

기체주입을 이용한 와류형 분사기들에서의 가변추력 연구

  • 이원구 (충북대학교 기계공학부) ;
  • 윤영빈 (서울대학교 기계항공공학부) ;
  • 안규복 (충북대학교 기계공학부)
  • Received : 2018.06.30
  • Accepted : 2018.08.10
  • Published : 2018.12.30
Download PDF
⟨ Previous Next ⟩

Abstract

Thrust throttling in a liquid rocket engine can be implemented via several ways such as high pressure drop injector, dual manifold, multiple chamber, pintle injector, and gas injection. Thrust throttling using gas injection controls thrust by usually injecting inert gas into propellant through an aerator to reduce the propellant's bulk density. In this study, the outside-in aerator was used in the propellant line to create two phase flow. Closed-type, open-type, and screw-type bi-swirl coaxial injectors were utilized for investigating throttling characteristics such as pressure drop, mixture density, and discharge coefficient according to gas-liquid mass ratio.

Keywords

OMHHBZ_2018_v23n4_159_f0001.png 이미지

Fig. 1 Schematic of aerator

OMHHBZ_2018_v23n4_159_f0003.png 이미지

Fig. 4 Mixture density using three two phase flow models according to GLR at the TR of 50% through the inner closed-type swirl injector

OMHHBZ_2018_v23n4_159_f0004.png 이미지

Fig. 5 Injection pressure drop of mixture according to GLR through the inner swirl injectors

OMHHBZ_2018_v23n4_159_f0005.png 이미지

Fig. 6 Injection pressure drop of mixture according to GLR through the outer swirl injectors

OMHHBZ_2018_v23n4_159_f0006.png 이미지

Fig. 7. Ratio of the injection pressure drop to the corresponding chamber pressure according to GLR through the inner swirl injectors

OMHHBZ_2018_v23n4_159_f0007.png 이미지

Fig. 8. Ratio of the injection pressure drop to the corresponding chamber pressure according to GLR through the outer swirl injectors

OMHHBZ_2018_v23n4_159_f0008.png 이미지

Fig. 9 Mixture density according to GLR through the inner swirl injectors

OMHHBZ_2018_v23n4_159_f0009.png 이미지

Fig. 10 Mixture density according to GLR through the outer swirl injectors

OMHHBZ_2018_v23n4_159_f0010.png 이미지

Fig. 11 Discharge coefficient using three two phase flow models according to GLR at the TR of 10% through the inner closed-type swirl injector

OMHHBZ_2018_v23n4_159_f0011.png 이미지

Fig. 12 Discharge coefficient of mixture according to GLR through the inner swirl injectors

OMHHBZ_2018_v23n4_159_f0012.png 이미지

Fig. 13 Discharge coefficient of mixture according to GLR through the outer swirl injectors

OMHHBZ_2018_v23n4_159_f0013.png 이미지

Fig. 2 Schematic of bi-swirl coaxial injectors: (a) closedtype, (b) open-type, and (c) screw-type

OMHHBZ_2018_v23n4_159_f0014.png 이미지

Fig. 3 Experimental set-up for cold-flow tests of gas injection throttling

Table 1 Experimental conditions

OMHHBZ_2018_v23n4_159_t0001.png 이미지

References

  1. D. K. Huzel and D. H. Huang, "Modern engineering for design of liquid-propellant rocket engines", 2nd ed., AIAA, Washington D.C., 1992.
  2. G. P. Sutton, "Rocket propulsion elements", 6th ed., John Wiley & Sons Inc., New York, 1992.
  3. M. J. Casiano, J. R. Hulka and V. Yang, "Liquid-propellant rocket engine throttling: a comprehensive review", Journal of Propulsion and Power, Vol. 26, No. 5, 2010, pp. 897-923. https://doi.org/10.2514/1.49791
  4. W. A. Tomazic, "Rocket-engine throttling", NACA, RM E55J20, 1995.
  5. G. A. Dressler, "Summary of deep throttling rocket engines with emphasis on apollo LMDE", AIAA Paper 2006- 5220, 2006.
  6. G. Morrell, "Rocket thrust variation with foamed liquid propellant", NACA, RM E56K27, 1957.
  7. W. Conrad, N. P. Hannum and H. E. Bloomer, "Photographic study of liquid-oxygen boiling and gas injection in the injector of a chugging rocket engine", NASA, TM X948, 1989.
  8. J. P. Mitchell, "Technical rept. No. 2 of advanced throttling concepts study", PWA FR 1045, 1964.
  9. J. P. Mitchell, "Technical rept. No. 3 of advanced throttling concepts study", PWA FR 1108, 1964.
  10. J. P. Mitchell, "Final rept. of advanced throttling concepts study", PWA FR 1279, 1964.
  11. J. G. Rivard, "New techniques for throttleable bipropellant rocket engines", AIAA Paper 65-560, 1965.
  12. H. S. Park and J. G. Hong, "Experimental study on spray characteristics of twin fluid nozzle in urea-SCR", Journal of ILASS-Korea, Vol. 22, No. 2, 2017, pp. 96-102.
  13. S. J. Lee and J. G. Hong, "Atomization characteristics of effervescent twin-fluid nozzle with different nozzle shapes", Journal of ILASS-Korea, Vol. 22, No. 3, 2017, pp. 146-152. https://doi.org/10.15435/JILASSKR.2017.22.3.146
  14. S. M. Zivi "Estimation of steady-state steam void fraction by means of the principle of minimum entropy production", Transactions ASME, Journal of Heat Transfer, Series C, Vol. 86, 1964, pp. 247-252. https://doi.org/10.1115/1.3687113
  15. D. Chisholm, "Two-phase flow in heat exch-angers and pipelines", Heat Transfer Engineering, Vol. 6, No. 2, 1985, pp. 48-57. https://doi.org/10.1080/01457638508939624
  16. P. B. Whalley, "Boiling, condensation, gas-liquid flow", Oxford University Press, New York, 1990.
  17. S. D. Sovani, P. E. Sojka and A. H. Lefebvre, "Effervescent atomization", Progress in Energy and Combustion Science, Vol. 27, 2001, pp. 483-521. https://doi.org/10.1016/S0360-1285(00)00029-0
  18. E. E. Michaelides, C. T. Crowe and J. D. Schwarzkopf, "Multiphase flow handbook", 2nd ed., CRC Press, Now York, 2016.
  19. Z. Kang, Z. Wang, Q. Li and P. Cheng, "Review on pressure swirl injector in liquid rocket engine", Acta Astronautica, Vol. 145, 2018, pp. 174-198. https://doi.org/10.1016/j.actaastro.2017.12.038
  20. K. Ahn and H. W. Choi, "A study on discharge coefficient of closed-type swirl Injectors", Atomization and Sprays, Vol. 27, No. 7, 2017, pp. 569-578. https://doi.org/10.1615/AtomizSpr.2017019096
  21. K. Ahn and H. W. Choi, "An extensive study on the discharge coefficient of open-type swirl injectors", Atomization and Sprays, Vol. 27, No. 10, 2017, pp. 835-846. https://doi.org/10.1615/AtomizSpr.2017019293