Advertisement

Journal of Visualization

, Volume 22, Issue 4, pp 773–781 | Cite as

Flow visualization of cryogenic spray from a movable pintle injector

  • Keonwoong Lee
  • Dongsoo Shin
  • Min Son
  • Heejang Moon
  • Jaye KooEmail author
Regular Paper
  • 53 Downloads

Abstract

Pintle injector has the advantages of wide throttle-ability by sustaining high combustion efficiency and weight lightening by replacing multi-injector elements with a single injector element. However, compared to typical injectors with a fixed shape, like shear coaxial or coaxial swirl injector, there are many complex variables owing to the moving parts. In this study, using cryogenic liquid nitrogen and gaseous nitrogen as simulants, experiments on cryogenic nitrogen spray visualization were performed to simulate cryogenic oxygen and gaseous methane combustion experiments. Experimental conditions were varied by changing the pintle tip angle, pintle opening distance, and simulant supplying pressure. With the visualization images, the spray angle of cryogenic spray was obtained and compared with the previous empirical equations. The former empirical equation between total momentum ratio and spray angle is not well matched, but the other equation between velocity ratio and spray angle fits well with experimental result, through modification of parameter.

Graphical abstract

Keywords

Pintle injector Visualization image Cryogenic spray 

Notes

Acknowledgements

This work was supported by Advanced Research Center Program (NRF-2013R1A5A1073861) through the National Research Foundation of Korea (NRF) grant funded by the Korean government (MSIP) contracted through Advanced Space Propulsion Research Center at Seoul National University.

References

  1. Boettcher PA, Mikellides IG, Vaughan DA, Shepherd JE, Damazo J (2009) Visualization of transverse annular jets. In: 62nd Annual meeting of the APS division of fluid dynamics meeting abstractsGoogle Scholar
  2. Cheng P, Li Q, Xu S, Kang Z (2017) On the prediction of spray angle of liquid-liquid pintle injectors. Acta Astranaut 138:145–151CrossRefGoogle Scholar
  3. Dressler G, Bauer J (2000) TRW pintle engine heritage and performance characteristics. In: Proceedings of 36th AIAA/ASME/SAE/ASEE joint propulsion conference and exhibit, AIAA 2000-3871Google Scholar
  4. Huzel DK, Huang DH (1992) Progress in astronatics and aeronatuics. AIAA, RestonGoogle Scholar
  5. Iannetti A, Girard N, Tchou-kien D, Bonhomme C, Ravier N, Edeline E (2017) Prometheus, a LOx/LCH4 reusable rocket engine. In: Proceedings of 7th European conference for aeronautics and space sciences, EUCASS 2017-537Google Scholar
  6. Ingebo RD (1993) Atomizing-gas temperature effect on cryogenic spray dropsize. In: Proceedings of 29th joint propulsion conference and exhibit, AIAA 1993-2333Google Scholar
  7. Kato T, Terakado D, Nanri H, Morito T, Masuda I (2017) Subscale firing test for regenerative cooling LOx/methane rocket engines. In: Proceedings of 7th European conference for aeronatuics and space sciences, EUCASS 2017-381Google Scholar
  8. Long MR, Bazarov VG, Anderson WE (2003) Main chamber injectors for advanced hydrocarbon booster engine. In: Proceedings of 39th AIAA/ASME/SAE/ASEE joint propulsion conference and exhibit, AIAA 2003-4599Google Scholar
  9. Park S, Nam J, Lee K, Koo JY, Hwang Y (2018) Prediction on throttling performance of a movable sleeve injector for deep throttling. J Korean Soc Aeronaut Space Sci 46(6):487–495Google Scholar
  10. Preuss A, Preclik D, Mäding C, Görgen J, Soller S, Haidn O, Oschwald M, Clauss R, Arnold R, Sender J (2008) LOx/Methane technology efforts for future liquid rocket engines. In: Proceedings of 5th international spacecraft propulsion conferenceGoogle Scholar
  11. Son M (2017) Correlations between spray and combustion characteristics of a movable pintle injector for liquid rocket engines. Dissertation, Korea Aerospace UniversityGoogle Scholar
  12. Son M, Yu K, Koo JY, Kwon OC, Kim JS (2015) Effects of momentum ratio and weber number on spray half angles of liquid controlled pintle injector. J Therm Sci 24(1):37–43CrossRefGoogle Scholar
  13. Son M, Kanmaniraja R, Koo JY, Kwon OC, Kim HD (2017) Design procedure of a movable pintle injector for liquid rocket engines. J Propuls Power 33(4):858–869CrossRefGoogle Scholar
  14. Sutton GP (2003) History of liquid-propellant rocket engine in Russia, formerly the Soviet Union. J Propuls Power 19(6):1008–1037CrossRefGoogle Scholar

Copyright information

© The Visualization Society of Japan 2019

Authors and Affiliations

  1. 1.Graduate SchoolKorea Aerospace UniversityGoyangRepublic of Korea
  2. 2.Institute of Space Propulsion, DLRLampoldshausenGermany
  3. 3.School of Aerospace and Mechanical EngineeringKorea Aerospace UniversityGoyangRepublic of Korea

Personalised recommendations