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The combustion of a solid fuel under supersonic cross flow conditions was investigated theoretically. A two-dimensional, axisymmetric, turbulent (k -Ɛ), global one step reaction model was solved numerically. Numerical simulations of the combustor geometries presenting the situations with solid fuel regression were conducted using FLUENT software. The combustor inlet airflow had a Mach number of 2, total temperature of 1200 K and total pressure of 30 atm. The HTPB fuel and a global one step reaction mechanism were used. The results of non reacting computation reveal that the airflow velocity deceases in the majority zone of combustor with the solid fuel boundary regression. The results of reacting computation reveal that the supersonic zone in the divergent section of the case gets larger than non reaction case. Combustion takes place in the vicinity of solid fuel wall.
Dr K.M Pandey. 2013. \u201cCFD Analysis of Solid Fuel Scramjet Combustors\u201d. Global Journal of Research in Engineering - A : Mechanical & Mechanics GJRE-A Volume 12 (GJRE Volume 12 Issue A7): .
Crossref Journal DOI 10.17406/gjre
Print ISSN 0975-5861
e-ISSN 2249-4596
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Total Score: 108
Country: India
Subject: Global Journal of Research in Engineering - A : Mechanical & Mechanics
Authors: Dr. Probhas Bose, K.M.Pandey, K.O.Reddy (PhD/Dr. count: 1)
View Count (all-time): 230
Total Views (Real + Logic): 5332
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Publish Date: 2013 01, Tue
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The combustion of a solid fuel under supersonic cross flow conditions was investigated theoretically. A two-dimensional, axisymmetric, turbulent (k -Ɛ), global one step reaction model was solved numerically. Numerical simulations of the combustor geometries presenting the situations with solid fuel regression were conducted using FLUENT software. The combustor inlet airflow had a Mach number of 2, total temperature of 1200 K and total pressure of 30 atm. The HTPB fuel and a global one step reaction mechanism were used. The results of non reacting computation reveal that the airflow velocity deceases in the majority zone of combustor with the solid fuel boundary regression. The results of reacting computation reveal that the supersonic zone in the divergent section of the case gets larger than non reaction case. Combustion takes place in the vicinity of solid fuel wall.
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