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Film cooling Effects on Wall Heat Flux of a Subscale Calorimetric Combustion Chamber  

Kim, Jong-Gyu (한국항공우주연구원 연소기팀)
Lim, Byoung-Jik (한국항공우주연구원 연소기팀)
Seo, Seong-Hyeon (한국항공우주연구원 연소기팀)
Han, Yeoung-Min (한국항공우주연구원 연소기팀)
Kim, Hong-Jip (한국항공우주연구원 연소기팀)
Choi, Hwan-Seok (한국항공우주연구원 연소기팀)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.10, no.4, 2006 , pp. 93-99 More about this Journal
Abstract
The effects of the changes of a film cooling mass flow rate and operating conditions on wall heat flux characteristics of a subscale calorimetric combustion chamber were investigated by experiment and numerical analysis. At the nominal operating condition, with the film cooling mass flow rate being 10.5 percent of a main fuel mass flow rate, maximum heat flux at the nozzle throat was measured to be 30 percent lower than that without the film cooling. For the relatively higher mixture ratio and chamber pressure condition, maximum heat flux at the nozzle throat was increased by 31 percent compared to that of the nominal condition test without film cooling.
Keywords
Calorimeter; Heat Flux; Film Cooling; Liquid Rocket Engine;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
연도 인용수 순위
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