Development of Turbopump Cavitation Performance Test Facility and the Test of Inducer Performance

터보펌프 Cavitation 성능시험기 개발 및 성능시험에 관한 연구

  • 손동기 (한국항공우주연구원, 터보기계연구그룹) ;
  • 김춘택 (한국항공우주연구원, 터보기계연구그룹) ;
  • 윤민수 (한국항공우주연구원, 터보기계연구그룹) ;
  • 차봉준 (한국항공우주연구원, 터보기계연구그룹) ;
  • 김진한 (한국항공우주연구원, 터보기계연구그룹) ;
  • 양수석 (한국항공우주연구원, 터보기계연구그룹)
  • Published : 2001.06.27

Abstract

A performance test facility for turbopump inducer cavitation was developed and the inducer cavitation performance tests were performed. Major components of the performance test facility are driving unit, test section, piping, water tank, and data acquisition and control system. The maximum of testing capability of this facility are as follows: flow rate - 30kg/s; pressure - 13 bar; rotational speed 10,000rpm. This cavitation test facility is characterized by the booster pump installed at the outlet of the pump that extends the flow rate range, and by the pressure control system that makes the line pressure down to vapor pressure. The vacuum pump is used for removing the dissolved air in the water as well as the line pressure. Performance tests were carried out and preliminary data of test model inducer were obtained. The cavitation performance test and cavitation bubble flow visualization were also made. This facility is originally designed for turbopump inducer performance test and cavitation test. However it can be applied to the pump impeller performance test in the future with little modification.

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