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http://dx.doi.org/10.6108/KSPE.2014.18.2.052

Effect of Thermal Barrier Coating and Film Cooling Condition on the Cooling Performance of Liquid-propellant Rocket Engine Combustor  

Joh, Miok (Combustion Chamber Team, Korea Aerospace Research Institute)
Kim, Seong-Ku (Combustion Chamber Team, Korea Aerospace Research Institute)
Choi, Hwan-Seok (Combustion Chamber Team, Korea Aerospace Research Institute)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.18, no.2, 2014 , pp. 52-59 More about this Journal
Abstract
The effect of ceramic thermal barrier coating thickness on the cooling performance of a liquid-propellant rocket engine combustor has been investigated through combustion/cooling performance analysis whose results verified against measured data from hot-firing tests. Also have been confirmed the effects of film cooling amount near the face plate on the coolant temperature and on the thermal barrier coating surface temperature. Some important points to be considered for designing cooling schemes for regeneratively cooled rocket engine combustor have been drawn and reviewed from present study and further verification of the analysis tool should be performed in the future.
Keywords
Liquid-propellant Rocket Engine; Thermal Barrier Coating; Film Cooling; Combustion/Cooling Performance;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
연도 인용수 순위
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