Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Operational Characteristic of Liquid Rocket Engine by Cavitation Instability at Low Inlet Pressure Condition

낮은 입구압력 조건에서 캐비테이션 불안정성에 의한 액체로켓엔진의 작동 특성

  • Received : 2020.07.20
  • Accepted : 2020.11.12
  • Published : 2020.12.31
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Abstract

The turbopump of the liquid rocket engine adapts an inducer to minimize the cavitation due to the variations of the propellants supply condition. However, the inducer introduces cavitation instabilities which are well-known problems in the engine development. In this paper, operational characteristics by the cavitation instabilities are analyzed and the reliability of the engine is checked when the first stage engine of the KSLV-II is tested at the low inlet pressure conditions. The characteristic frequencies representing the cavitation instabilities of the LOx pump are clearly found in various high frequency sensor signals around the entire engine in addition to the LOx and fuel pump.

액체로켓엔진의 터보펌프는 추진제 상태 변화로 인한 캐비테이션 발생을 최소화하기 위해 인듀서를 사용한다. 그러나 인듀서에서 발생하는 캐비테이션 불안정성은 엔진 개발의 큰 문제점으로 알려져 있다. 본 논문에서는 한국형발사체 1단용 엔진이 낮은 입구압력 조건에서 작동될 때 캐비테이션 불안성에 의한 엔진 작동 특성을 검토하고 엔진의 신뢰도를 확인하고자 하였다. 산화제펌프의 캐비테이션 불안정성을 대표하는 특성주파수가 산화제펌프와 연료펌프를 비롯한 엔진 여러 곳에 부착된 동압센서, 가속도계, 스트레인 게이지 등의 신호에서 뚜렷하게 관찰되었다.

Keywords

References

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