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http://dx.doi.org/10.20910/JASE.2017.11.1.8

Study on the Turbine Performance of 7 ton Liquid Rocket Engine Turbopump  

Lee, Hanggi (Korea Aerospace Research Institute, Turbopump Department)
Shin, Juhyun (Korea Aerospace Research Institute, Turbopump Department)
Choi, Changho (Korea Aerospace Research Institute, Turbopump Department)
Publication Information
Journal of Aerospace System Engineering / v.11, no.1, 2017 , pp. 8-13 More about this Journal
Abstract
This study was performed to evaluate the turbine performance of a turbopump in the third stage engine of the Korea Space Launch Vehicle-II. The turbine is a supersonic impulse type with a single rotor. One nozzle is for starting and four remaining nozzles are for steady operation. A similarity test was carried out in the high air test facilities at the Korea Aerospace Research Institute. Test results showed that turbine efficiency changed much more from rotational speed variations than by pressure ratio variations. These results showed characteristics similar to other supersonic impulse turbines.
Keywords
Supersonic Impulse Turbine; Turbopump; Partial Admission;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
연도 인용수 순위
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