Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Performance Test of a 7 tonf Liquid Rocket Engine Turbopump

7톤급 액체로켓엔진용 터보펌프 조립체 성능시험

  • Kwak, Hyun Duck (Turbopump Team, Korea Aerospace Research Institute) ;
  • Kim, Dae-Jin (Turbopump Team, Korea Aerospace Research Institute) ;
  • Kim, Jin-Sun (Turbopump Team, Korea Aerospace Research Institute) ;
  • Kim, Jinhan (Turbopump Team, Korea Aerospace Research Institute) ;
  • Noh, Jun-Gu (Turbopump Team, Korea Aerospace Research Institute) ;
  • Park, Pyun-Goo (Turbopump Team, Korea Aerospace Research Institute) ;
  • Bae, Jun-Hwan (Turbopump Team, Korea Aerospace Research Institute) ;
  • Shin, Ju-Hyun (Turbopump Team, Korea Aerospace Research Institute) ;
  • Yoon, Suck-Hwan (Turbopump Team, Korea Aerospace Research Institute) ;
  • Lee, Hanggi (Turbopump Team, Korea Aerospace Research Institute) ;
  • Jeon, Seong-Min (Turbopump Team, Korea Aerospace Research Institute) ;
  • Jeong, Eunhwan (Turbopump Team, Korea Aerospace Research Institute) ;
  • Choi, Chang-Ho (Turbopump Team, Korea Aerospace Research Institute) ;
  • Hong, Soon-Sam (Turbopump Team, Korea Aerospace Research Institute) ;
  • Kim, Seong-Lyong (Propulsion Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Kim, Seung-Han (Propulsion Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Han, Yeong-Min (Propulsion Test and Evaluation Team, Korea Aerospace Research Institute)
  • Received : 2014.12.27
  • Accepted : 2015.03.13
  • Published : 2015.04.01
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Abstract

Performance tests of a turbopump for the developing 7-tonf liquid rocket engine were conducted. The performance of turbopump components and their power matching were measured and examined firstly under the LN2 and water environment. In the real propellant(LOX and kerosene) environment tests, design and off-design performances of turbopump were fully verified. During the off-design tests, turbopump running time was set the same as engine operating time and pump inlet pressure were set lower than nominal operating value in order to investigate pump suction capability. It have been verified that subject turbopump satisfies required performance - flow rate, head, suction performance and operational time - in the operating regime of developing liquid rocket engine.

7톤급 액체로켓엔진용 터보펌프 개발 시제에 대한 조립체 성능시험이 수행되었다. LN2와 물이 적용된 상사매질 조립체 시험을 통해 터보펌프 단품 간 출력 매칭 및 조립체 레벨에서의 수력/공력 성능검증이 선행되었으며 LOX와 케로신의 실제 운용 환경의 실매질 시험에서는 터보펌프의 설계점, 탈설계점 성능 검증시험이 이루어졌다. 탈설계시험은 엔진의 운용시간을 적용하여 이루어졌으며 펌프의 흡입성능 검증을 병행하였다. 개발된 7톤급 액체로켓용 터보펌프는 엔진운용영역에서 유량, 양정, 흡입성능, 그리고 운용시간의 요구규격을 만족시키는 것으로 확인되었다.

Keywords

References

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