Proceedings of the Korean Society of Propulsion Engineers Conference (한국추진공학회:학술대회논문집)
- 2009.11a
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- Pages.119-122
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- 2009
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- 1975-342X(pISSN)
Design of Film-cooling Ring of The Engine Using Green Propellant And Thermal Analysis
친환경 추진제를 사용하는 액체로켓엔진의 막냉각링 설계 및 열해석
Abstract
The purpose of this study is to design of film-cooling ring for the small thrust rocket engine using green propellants(Hydrogen peroxide and kerosene). Cold flow test was carried out to measure the mass flow rate and atomizing characteristic. Required mass flow rate was obtained from thermal analysis of the engine, and measured flow rate 42.25g/s was in the range of permissible coolant flow rate. With the same mass flow rate, cooling ring with more hole and high velocity shows better spray pattern. The result of thermal analysis, cooling ring has enough cooling performance.
본 연구는 친환경 추진제인 과산화수소(
Keywords