Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Investigation of Chill Down Characteristics of Liquid Oxygen Feeding System in 75 Tonf-class Liquid Rocket Engine Firing Test

75톤급 액체로켓엔진 연소시험에서의 액체산소 공급부 예냉특성 고찰

  • Seo, Daeban (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Cho, Namkyung (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Han, Yeoungmin (Engine Test and Evaluation Team, Korea Aerospace Research Institute)
  • Received : 2017.08.08
  • Accepted : 2017.11.08
  • Published : 2018.08.01
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Abstract

A firing test of the 75 tonf-class liquid rocket engine to be used as the first and second stage engines of the KSLV-II was carried out at the rocket engine test facility(RETF). Since this engine uses liquid oxygen as the oxidizer, which is a cryogenic fluid, it is essential that the chill down of the supply pipe line and engine proceed for the firing test; thus, the given inlet requirements must be met. Moreover, it is important to understand the chill down characteristics of the facility and the engine and the amount of liquid oxygen consumed in the chill down process for efficient test operation in the future. In this paper, chill down characteristics of the supply pipe and the engine were evaluated through the investigation of the chill down process of the 75 tonf-class liquid rocket engine at each stage before and after run tank pressurization. In addition, the amount of liquid oxygen consumed was also evaluated.

한국형발사체의 1단 및 2단 엔진으로 사용될 75톤급 액체로켓엔진의 연소시험이 엔진 연소시험설비에서 수행되었다. 이 엔진은 산화제로 극저온 유체인 액체산소를 사용하므로, 연소시험을 위해서는 필수적으로 설비의 공급 배관 및 엔진의 예냉과정이 진행되어 주어진 엔진 입구 온도 및 압력 요구조건이 만족되어야 한다. 따라서 향후 효율적인 시험 운용을 위해서는 시험 시 설비와 엔진에서의 예냉특성 및 예냉과정에서 소모되는 액체산소의 양을 파악하는 것이 중요하다. 이 논문에서는 75톤급 액체로켓엔진의 연소시험에서 예냉과정의 고찰을 통하여 런탱크 가압 전, 후 각 단계에서의 설비배관 및 엔진의 예냉특성을 평가하였으며, 시험 시 소모되는 액체산소의 양을 평가하였다.

Keywords

References

  1. Kim, S. et al., "Development Test of 75 tonf Engine System for KSLV-II," KSPE Fall Conference, Jeongsun, Korea, pp. 888-891, Dec. 2016.
  2. Kim, J., Choi, C., Jung, E., Jeon, S. and Hong, S., "Development Status of a Turbopump for Korea Space Launch Vehicle (KSLV-II)," KSAS Fall Conference, Jeju, Korea, pp. 254-263, Nov. 2012.
  3. Seo, D. et al., "Chill down Characteristisc of 75 tonf-class Engine 1G for KSLV-II," KSPE Fall Conference, Jeongsun, Korea, pp. 930-933, Dec. 2016.
  4. Cho, N., Seo, D., Yu, B., Kim, S. and Han, Y., "Investigation of chilling Procedure of LOX Supply System of Liquid Rocket Engine," KSPE Fall Conference, Jungsun, Korea, pp. 863-867, Dec. 2016.
  5. Liebenberg, L. and Meyer J.P., "The Characterization of flow regimes with power spectral density distributions of pressure fluctuations during condensation in smooth and micro-fin tubes," Experimental Thermal and Fluid Science, Vol. 31, No. 1, pp. 127-140, 2006. https://doi.org/10.1016/j.expthermflusci.2006.03.023
  6. Dr. Jacob and N. Chung, "Two Phase Flow Characteristics and Boiling Heat Transfer Rates During Cryogenic Chilldown and Transport in Reduced Gravity," NASA CR-2008-215440/PART3, 2008.