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http://dx.doi.org/10.6108/KSPE.2019.23.3.076

Combustion Characteristics Based on Injector Shape of Supersonic Combustor  

Jin, Sangwook (The 4th R&D Institute - 5th Directorate, Agency for Defense Development)
Choi, Hojin (The 4th R&D Institute - 5th Directorate, Agency for Defense Development)
Lee, Hyung Ju (Division of Aeronautics, Cheongju University)
Byun, Jong-Ryul (The 4th R&D Institute - 5th Directorate, Agency for Defense Development)
Bae, Juhyun (The 4th R&D Institute - 5th Directorate, Agency for Defense Development)
Park, Dongchang (The 4th R&D Institute - 5th Directorate, Agency for Defense Development)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.23, no.3, 2019 , pp. 76-87 More about this Journal
Abstract
A direct connected test was conducted for a supersonic combustor with a cavity-type flame holder. Liquid hydro-carbon fuel was injected in different types of injectors: inclined and aeroramp injectors, for the flow condition of Mach 4 at an altitude of 20 km. The static pressure on the combustor wall along the axis and the total pressure at the exit of combustor were measured to analyze the combustion characteristics at various fuel flow rates.
Keywords
Supersonic Combustor; Direct-Connect Test; Cavity Type Flame Holder; Aero-ramp injector; Inclined Injector;
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