Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Study on the Turbine Performance of 7 ton Liquid Rocket Engine Turbopump

7톤급 액체로켓 엔진 터보펌프 터빈 성능 연구

  • Lee, Hanggi (Korea Aerospace Research Institute, Turbopump Department) ;
  • Shin, Juhyun (Korea Aerospace Research Institute, Turbopump Department) ;
  • Choi, Changho (Korea Aerospace Research Institute, Turbopump Department)
  • 이항기 (한국항공우주연구원 터보펌프팀) ;
  • 신주현 (한국항공우주연구원 터보펌프팀) ;
  • 최창호 (한국항공우주연구원 터보펌프팀)
  • Received : 2016.10.18
  • Accepted : 2016.12.05
  • Published : 2017.02.28
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Abstract

This study was performed to evaluate the turbine performance of a turbopump in the third stage engine of the Korea Space Launch Vehicle-II. The turbine is a supersonic impulse type with a single rotor. One nozzle is for starting and four remaining nozzles are for steady operation. A similarity test was carried out in the high air test facilities at the Korea Aerospace Research Institute. Test results showed that turbine efficiency changed much more from rotational speed variations than by pressure ratio variations. These results showed characteristics similar to other supersonic impulse turbines.

한국형 발사체 3단 엔진용 터보펌프 터빈에 관해 성능 시험을 수행하여 성능 특성 결과를 분석하였다. 터빈은 초음속 충동형 방식의 단단 형태이며, 노즐은 시동 노즐 1개와 정상 운전용 노즐 4개로 이루어졌으며, 부분 분사 형태로 되어 있다. 한국항공우주연구원 내의 고압 공기 터빈 상사 시험 설비를 이용하여 상사 시험을 수행하였다. 시험 결과 효율은 회전수 변화에 크게 변화하며, 이에 반해 압력비 변화에는 다소 작게 변화하는 초음속 충동형 터빈의 일반적인 특성을 보이고 있다.

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References

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