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http://dx.doi.org/10.5762/KAIS.2014.15.6.3403

Effect of Combustion Instability on Heat Transfer in a Subscale Thrust Chamber  

Ahn, Kyubok (School of Mechanical Engineering, Chungbuk National University)
Publication Information
Journal of the Korea Academia-Industrial cooperation Society / v.15, no.6, 2014 , pp. 3403-3409 More about this Journal
Abstract
Hot-firing tests were carried out using a mixing head with 19 swirl coaxial injectors and a combustion chamber with internal cooling channels. The propellants of liquid oxygen and kerosene(Jet A-1) were burned in a range of chamber pressures (59~82 bar) and mixture ratios (2.0~3.0). The temperature of water used as the cooling fluid was measured at the inlet and outlet of the cooling channels, and the heat flux was calculated. The aim of this study was to examine the effect of combustion instability on heat transfer in a subscale thrust chamber, and detect the temperature variation of cooling water. During several hot-firing tests, combustion instability was encountered which caused a 5~20% increase in heat flux. The peak heat flux took place in the initial stages of combustion instability.
Keywords
Combustion Instability; Heat Transfer; Liquid Rocket Engine Thrust Chamber;
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Times Cited By KSCI : 1  (Citation Analysis)
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