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Cryogenic Performance Test of a Turbopump Inducer  

Kim, Jin-Sun (한국항공우주연구원 터보펌프팀)
Kim, Jin-Han (한국항공우주연구원 터보펌프팀)
Hong, Soon-Sam (한국항공우주연구원 터보펌프팀)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.11, no.1, 2007 , pp. 64-70 More about this Journal
Abstract
A test facility was developed where an inducer for a liquid rocket engine turbopump can be tested using liquid nitrogen as a working fluid. At the facility, a hydrodynamic performance test and a cavitation performance test for an oxidizer turbopump were carried out. Head-flow relation at liquid nitrogen test was similar to the case at water test. However, cavitation performance at the liquid nitrogen was superior to the case at water test, which results from the thermodynamic effect of cavitation.
Keywords
Turbopump; Inducer; Performance Test; Liquid Nitrogen; Cavitation;
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  • Reference
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