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Conceptual Design of Coolant Channel for Sub-scale Combustion Chamber  

정용현 (한국항공우주연구원)
조원국 (한국항공우주연구원)
한상엽 (한국항공우주연구원)
류철성 (한국항공우주연구원)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.6, no.4, 2002 , pp. 1-6 More about this Journal
Abstract
A numerical heat transfer analysis and the structural analysis were performed for the design of sub-scale combustion chamber's coolant passage. The heat flux through the combustion chamber wall was estimated by 2-D heat transfer analysis of compressible hot gas and the result was applied as a thermal boundary condition of 3-D analysis. The heat flux estimated by the present method agreed well with the experimental correlation and proved to be insensitive to cooling condition. So the same thermal boundary condition was applied for various operating conditions. The maximum temperature of combustion chamber wall was predicted by 3-D analysis for single coolant passage and the result will be used for the development of a regeneratively cooled combustion chamber. Also estimated were the stress distribution and structural safety of coolant passage through the static structural analysis.
Keywords
Heat Transfer; Sub-Scale Combustion Chamber; Coolant Passage; Heat Flux; regeneratively Cooled Combustion Chamber;
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