Hydraulic Tests of Fuel Pump for 75-ton class Liquid Rocket Engines

75톤급 로켓엔진용 연료펌프의 수력성능시험

  • 김대진 (한국항공우주연구원 터보펌프팀) ;
  • 홍순삼 (한국항공우주연구원 터보펌프팀) ;
  • 최창호 (한국항공우주연구원 터보펌프팀) ;
  • 노준구 (한국항공우주연구원 터보펌프팀) ;
  • 김진한 (한국항공우주연구원 터보펌프팀)
  • Published : 2009.11.19

Abstract

A series of hydraulic tests of a fuel pump are performed using water at a room temperature. The pump is under development for 75-ton class liquid rocket engines of the open-loop gas generator type. According to the test results, the fuel pump satisfies its design requirement and its head and efficiency at the design flowrate are higher than the expected value by the computational analysis. Also, it is found that the pressure at the rear bearing outlet is higher than expected because the inlet of bypass pipe line is narrow. Furthermore, the flowrate of the secondary flow is estimated using the pressure difference of the elbow of the bypass pipe line.