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A Study on the Combustion Performance with Variation of Fuel Injection Hole Configuration at Supersonic Combustion  

Lee, Kyung-Jae (한국항공우주연구원 항공추진기관팀)
Kang, Sang-Hun (한국항공우주연구원 항공추진기관팀)
Lee, Yang-Ji (한국항공우주연구원 항공추진기관팀)
Yang, Soo-Seok (한국항공우주연구원 항공추진기관팀)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.15, no.5, 2011 , pp. 19-26 More about this Journal
Abstract
In order to investigate the effect of fuel injection hole configuration within the scramjet combustor, experiment and quasi-one-dimensional analysis was performed. And the results were compared with experiment and analysis result which were performed in 2008 with same facility and test condition. Fuel injection hole size was decreased and quantity was increased. However the depth of fuel penetration and flow quantity of fuel were maintained. As a test result, combustion performance was increased significantly with no-cavity injector and slightly with plain-cavity. However, combustion performance with zigzag-cavity was decreased.
Keywords
Scramjet; Supersonic Combustion; Fuel Injection; Hydrogen; Combustion Efficiency;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
연도 인용수 순위
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