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Real-Propellant Test of a Turbopump for a 30-Ton Thrust Level of Liquid Rocket Engine  

Hong, Soon-Sam (한국항공우주연구원 터보펌프팀)
Kim, Dae-Jin (한국항공우주연구원 터보펌프팀)
Kim, Jin-Sun (한국항공우주연구원 터보펌프팀)
Kim, Jin-Han (한국항공우주연구원 터보펌프팀)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.13, no.3, 2009 , pp. 20-26 More about this Journal
Abstract
Turbopump test for a 30-ton-thrust liquid rocket engine was carried out using real-propellant. Liquid oxygen, kerosene, cold hydrogen gas were used for the oxidizer pump, the fuel pump, and the turbine, respectively. The turbopump was reliably operated at the design and off-design conditions and the performance requirements were satisfied, which implies that the turbopump development at the engine subsystem level is successfully accomplished in the point of performance validation. This paper presents the results of a test where the turbopump was run for 75 seconds at three operating modes. In terms of performance characteristics of pumps and turbine, the results of turbopump assembly test using real-propellant showed a good agreement with those of the turbopump component tests using simulant working fluid.
Keywords
Turbopump; Liquid Rocket Engine; Real-Propellant Test; Oxidizer Pump; Fuel Pump; Turbine;
Citations & Related Records
Times Cited By KSCI : 4  (Citation Analysis)
연도 인용수 순위
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