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http://dx.doi.org/10.5139/JKSAS.2003.31.4.076

Study on Calorimeteric Chamber for Heat Flux Measurement in Liquid Rocket Engine  

Kim, Byeong Hun (한국항공우주연구원)
Park, Hui Ho (충남대학교)
Hwang, Su Gwon (국방과학연구소)
Kim, Yu (충남대학교)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.31, no.4, 2003 , pp. 76-81 More about this Journal
Abstract
To investigate the convective heat transfer phenomena inside the Lox/Kerosene liquid rocket combustion chamber, hot fire tests were performed by using a water-cooled calorimetric chamber. The calorimetric chamber consists of one cylindrical section and nozzle section with independent cooling passage. To measure the heat flux, thermocouples were installed inlet and outlet of cooling passage of each section. The investigated range of combustion chamber pressure is from 100 psi to 300psi at fixed O/F ratio of 2.0 and radiation heat transfer from the hot gas to the surface is not considered. The measured heat flux was almost linearly depended on the chamber pressure.
Keywords
Calorimetric combustion Chamber;
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