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Analysis of Performance and Combustion Characteristics in KSR-III Liquid Rocket Engine with Combustion Instability Passive Control Device(Baffle)  

문윤완 (한국항공우주연구원 엔진그룹)
류철성 (한국항공우주연구원 엔진그룹)
설우석 (한국항공우주연구원 엔진그룹)
김영목 (한국항공우주연구원 추진제어그룹)
이수용 (한국항공우주연구원 우주추진기관실)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.7, no.4, 2003 , pp. 63-72 More about this Journal
Abstract
The combustion characteristics of the KSR-III engine were investigated numerically from the viewpoint of performance and combustion field. For numerical analysis of KSR-III engine with hub-and-spoke baffle, 3-D calculation was performed about $30^{\cire}$ section and the prediction of performance was in a good agreement with hot-firing test result. As a result of baffle installed, the performance of KSR-III engine was reduced in comparison with no baffle case and local high temperature region appeared on injector plate, combustion wall and baffle wall, This calculation was used practically as basic data for designing injector plate with film cooling holes and predicting the performance of KSR-III final flight test.
Keywords
Combustion; Performance; Liquid Rocket Engine;
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