Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
권호 표지
DOI QR코드

DOI QR Code

Performance Analysis of Liquid Pintle Thruster Using Quasi-one-dimensional Multi-phase Reaction Flow: Part I Key Sub-model Validation

준 일차원 다상 반응유동 기법을 이용한 케로신/과산화수소 액체 핀틀 추력기 성능해석 연구: Part I. 주요 구성 모델 검증

  • Kang, Jeongseok (Department of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Bok, Janghan (Department of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Sung, Hong-Gye (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Kwon, Minchan (The 4th R&D Institute, Agency for Defense Development) ;
  • Heo, JunYoung (The 4th R&D Institute, Agency for Defense Development)
  • Received : 2020.07.27
  • Accepted : 2020.11.17
  • Published : 2020.12.31
Download PDF
⟨ Previous Next ⟩

Abstract

A quasi one-dimensional multi-phase reaction flow analysis code is developed for the performance analysis of liquid pintle thrusters. Unsteady flow field, droplet evaporation, finite reaction and film cooling models are composed as the major models of the performance analysis. The droplet vaporization takes account of Abramzon's vaporization model, and the combustion employs a flamelet model based on detail chemical reactions. Shine's model is applied for the film cooling calculation. To verify each model, the Sod shock tube, single droplet vaporization, kerosene droplets combustion, and film length are evaluated.

액체 핀틀 추력기의 성능해석을 위해 준 일차원 다상 반응유동 해석코드를 개발하였다. 해석코드의 주요모델로서 다상 유동장, 액적의 기화, 다상 연소, 액체 막냉각 등의 모델들을 적용하였다. 액적기화 모델은 Abramzon의 기화모델을 적용하였으며 연소 모델은 flamelet 모델을 적용하였다. 막냉각 효과는 Shine의 모델을 적용하였다. 각 모델을 사용하여 산소-질소의 Sod shock 튜브, n-decane 액적기화, 케로신 다상연소, 막냉각 길이를 계산하여 선행 연구자의 결과와 비교 검증하였다.

Keywords

Acknowledgement

본 연구는 방위사업청 국방과학연구소 기초연구사업(2016-05-044)과 한국항공우주연구원이 지원하는 한국형발사체개발사업(2019M1A3A1A020-9859913)의 지원에 의해 수행되었습니다.

References

  1. Elverum, G.W., Staudhammer, P. and Miller, J., "The Descent Engine For the Lunar Module," 3rd Propulsion Joint Specialist Conference, Washington, DC., U.S.A., AIAA 1967-521, Jul. 1967.
  2. Gordon, A.D. and Martin, B., "TRW Pintle Engine Heritage and Performance Characteristics," 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Las Vegas, N.V., U.S.A., AIAA 2000-3871, Jul. 2000.
  3. Chang, Y., Zou, J., Li, Q. and Cheng, P., "Numerical Study on Combustion and Heat Transfer of a GOX/GCH4 Pintle Injector," 2018 Asia-Pacific International Symposium on Aerospace Technology, Sanghai, China, Jul. 2018.
  4. Muss, A.J., Johnson, W.C., Kruse W. and Cohn K.R., "The Performance of Hydrocarbon Fuels with H2O2 in a Uni-element Combustor," 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Las Vegas, N.V., U.S.A., AIAA 2003-4623, July. 2003.
  5. Fang, X. and Shen, C.B., "Study on Atomization and Combustion Characteristics of LOX/methane pintle injectors," Acta Astronautica, Vol. 136, pp. 369-379, 2017. https://doi.org/10.1016/j.actaastro.2017.03.025
  6. Ryu, H., Yu, I., Kim, W., Shin, D., Ko, Y. and Kim, S., "Experimental Investigation on Combustion Performance of a Pintle Injector Engine with Double-row Rectangular Slot," Journal of the Korean Society of Propulsion Engineers, Vol. 21, No. 3, pp. 25-33, 2017. https://doi.org/10.6108/KSPE.2017.21.3.025
  7. Nam, J., Lee, K., Park, S., Huh, H. and Koo, J., "Spray Characteristics of a Movable Pintle Injector with Pintle Tip Shape," The Korean Society for Aeronautical and Space Sciences, Vol. 47, No. 9, pp. 658-664, 2019. https://doi.org/10.5139/JKSAS.2019.47.9.658
  8. Han, D.H., Yoo, Y.L. and Sung, H.G., "An Analysis of the Different Flow Characteristics of a Closed Bomb Test in Cylindrical and Spherical Closed Vessels," International Journal of Aeronautical and Space Sciences, Vol. 20, pp. 150-156, 2018.
  9. Abramzon, B. and Sirignano, W.A., "Droplet Vaporization Model for Spray Combustion Calculations," International Journal of Heat and Mass Transfer, Vol. 32, No. 9, pp. 1605-1618, 1989. https://doi.org/10.1016/0017-9310(89)90043-4
  10. Kang, J.S. and Sung, H.G., "Kerosene/GOx Dynamic Combustion Characteristics in a Mixing Layer Under Supercritical Conditions Using the LES-FP approach," Fuel, Vol. 203, pp. 579-590, 2017. https://doi.org/10.1016/j.fuel.2017.04.088
  11. Shine, S.R., Kumar, S.S. and Suresh, B.N., "A New Generalised Model for Liquid Film Cooling in Rocket Combustion Chambers," International Journal of Heat and Mass Transfer, Vol. 55, pp. 5065-5075, 2012. https://doi.org/10.1016/j.ijheatmasstransfer.2012.05.006
  12. Yoo, Y.L. and Sung, H.G., "Numerical Investigation of an Interaction Between Shock Waves and Bubble in a Compressible Multiphase Flow Using a Diffuse Interface Method," International Journal of Heat and mass Transfer, Vol. 127, No. 1, pp. 210-221, 2018. https://doi.org/10.1016/j.ijheatmasstransfer.2018.08.012
  13. Zettervall, N., Fureby, C. and Nilsson, E.J.K., "A Small Skeletal Kinetic Mechanism for Kerosene," Energy & Fuels, Vol. 30, No. 11, pp. 9801-9813, 2016. https://doi.org/10.1021/acs.energyfuels.6b01664
  14. Strelkova, M.I., Kirillov, I.A., Potapkin, B.V., Safonov, A.A. and Sukhanov, L.P., "Detailed and Reduced Mechanisms of Jet A Combustion at High Temperature," Combustion Science and Technology, Vol. 180, pp. 1788-1802, 2008. https://doi.org/10.1080/00102200802258379
  15. CHEMKIN-PRO 15512, Reaction Design: San Diego, 2011.
  16. Turns, S.R., An Introudction to Combustion Conecpts and Application, 3rd ed., Mc Graw Hill, New York, N.Y., U.S.A., 2012
  17. Morrell, G., "Investigation of Internal Film Cooling of a 1000-pound Thrust Liquid Ammonia Liquid Oxygen Rocket," Technical Report, NACA RME51E04, 1951.