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- W2029656487 abstract "․ Jong-Gyu Kim** ․ Byoungjik Lim* ․ Munki Kim** ․ Donghyuk Kang** ․ Seong-Ku Kim* ․ Hwan-Seok Choi*ABSTRACT Fuel-side cold-flow tests were performed on the technology demonstration model of a 75 ton-class liquid rocket engine combustion chamber for the first stage of the Korea space launch vehicle Ⅱ. Pressure drop in the cooling channels of the combustion chamber was measured by changing fuel mass flow rate through a pressure regulating system. Pressure d rop in each segment of the chamber could be obtained and a lot of pressure drop was caused by high flow velocity in the nozzle throat segment. The accuracy of a hydraulic analysis method for calculating a pressure loss in cooling channels could be verified by applying it to the cold-flow test conditions. 초 록 한국형발사체 1단에 사용될 75톤급 액체로켓엔진 연소기의 기술검증시제를 설계, 제작하여 연료 수류시험을 수행하였다. 가압압력을 조절하여 연료 유량을 변경함으로써 주어진 유량에서 발생하는 연소기 재생냉각 채널에서의 압력 손실을 측정하였다. 연소실 각 부에서의 압력 손실을 측정할 수 있었으며, 상당량의 압력 손실이 유속이 강한 연소실 노즐목부에서 발생함을 확인하였다. 주어진 연료 수류시험 조건에서 수력학 해석을 통하여 수력학 해석 방법의 정확도를 검증할 수 있었다. Key Words: Liquid Rocket Engine(액체로켓엔진), Regeneratively-Cooled Combustion Chamber( 재생냉각 연소기), Fuel-Side Cold-Flow Test(연료 수류시험), Pressure Drop Analysis(차압 해석)" @default.
- W2029656487 created "2016-06-24" @default.
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- W2029656487 date "2012-12-01" @default.
- W2029656487 modified "2023-09-27" @default.
- W2029656487 title "Fuel-Side Cold-Flow Test and Pressure Drop Analysis on Technology Demonstration Model of 75 ton-class Regeneratively-Cooled Combustion Chamber" @default.
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- W2029656487 doi "https://doi.org/10.6108/kspe.2012.16.6.056" @default.
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