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http://dx.doi.org/10.5139/JKSAS.2012.40.3.222

Effect of Injector Cooling on Ignition of Cryogenic Spray  

Kim, Do-Hun (한국항공대학교 항공우주 및 기계공학과 대학원)
Lee, Jin-Hyuk (한국항공대학교 항공우주 및 기계공학부)
Koo, Ja-Ye (한국항공대학교 항공우주 및 기계공학부)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.40, no.3, 2012 , pp. 222-229 More about this Journal
Abstract
The cooling of a injector effects on the vapor pressure of cryogenic oxidizer spray, and it decides the phase transition point at the ignition process, when the combustion chamber pressure increases drastically. The phase transition of oxidizer spray affects the ignition characteristics, and several ignition tests with the LOx/$GCH_4$ uni-element coaxial swirl injector was performed in the different initial temperatures of oxidizer injector, in order to investigate the effect of injector cooling on the ignition transient characteristics. At the transition point of oxidizer phase, where the combustion chamber pressure increased over the LOx vapor pressure, the temporary quenching phenomenon of the flame occurred. The lower temperature of chilled down injector and tubing tends to move up the phase transition earlier.
Keywords
Injector Cooling; Cryogenic Spray; Ignition Characteristics; Vapor Pressure;
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