• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.203-207
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• 2005

An experimental study was carried out to investigate the effect of film cooling in the thrust chamber of liquid rocket using LOx and Kerosene as propellant. The heat fluxes were obtained from the measured wall temperature to the axial direction of thrust chamber for different type of coolant, the various O/F ratio, mass flow rate and the location of the film cooling injector. A thin wall combustion chamber and nozzle were used to obtain the heat flux.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.132-136
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• 2004

Experimental study has been conducted to investigate effect of mainstream turbulence intensity on film cooling performance of staggered rows of rectangular holes in combustor. Temperature fields and adiabatic film cooling effectiveness under $10\%$ mainstream turbulence intensity are measured. The results of temperature fields show that overall values are decreased and thicker film of coolant is formed downstream of rows of holes for high mainstream turbulence intensity. The results of film cooling effectiveness show that the values around the holes are smaller than the case of the low mainstream turbulence intensity, however, the difference of film cooing performance is decreasedforthefurtherdownstream.