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Axial Thrust Measurement of Fuel Pump for 75-ton Class Rocket Engine  

Kim, Dae-Jin (한국항공우주연구원 터보펌프팀)
Hong, Soon-Sam (한국항공우주연구원 터보펌프팀)
Choi, Chang-Ho (한국항공우주연구원 터보펌프팀)
Kim, Jin-Han (한국항공우주연구원 터보펌프팀)
Publication Information
Aerospace Engineering and Technology / v.9, no.2, 2010 , pp. 8-13 More about this Journal
Abstract
An effective control of the axial thrust of a turbopump is one of the critical issues for obtaining its operational stability. Axial thrusts of the fuel pump for the 75-ton class rocket engine under development were measured with water as a test propellant at a room temperature. According to the test results, the axial thrust of the fuel pump seemed to satisfy the axial force condition of its bearing. Also, the thrust was increased as a whole when the flowrate of the pump was decreased. Furthermore it was found that the thrust and the leakage flowate were modified when the gaps between the floating ring seals and the impeller were changed.
Keywords
turbopump; fuel pump; axial thrust; floating ring seal; secondary flow;
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  • Reference
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