• Transactions of the KSME C: Technology and Education
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• v.5 no.2
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• pp.97-104
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• 2017

In this study, we verify the accurate numerical analysis and simplify the perforated plate of inlet and exhaust duct using porous media for the cost reduction and the efficiency improvement of thermal-fluid analysis to evaluate cooling performance of wheel-loader. The flow loss coefficient of the perforated plate is defined by the experiment result. To define analytically the flow loss coefficient of the perforated plate, we calculate the pressure drop of unit-cell and compare to experiment result. Finally, we compare the heat balance test and the simplified simulation result on the inlet and exhaust duct of wheel-loader. After this study, we verify the applicability of the simplified analysis method on the inlet and exhaust duct of wheel-loader. And, foundation which can carry out effectively the evaluation and improvement for cooling performance of wheel-loader is prepared.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.10
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• pp.1027-1037
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• 2009

The development of a combustion chamber for a 30-$ton_f$ regeneratively-cooled space liquid rocket engine is described. Starting from the development of bi-propellant swirl coaxial injectors, essential technologies were verified through subscale combustion chambers and afterwards applied to the full-scale combustion chambers. A total of 5 full-scale combustion chambers have been utilized to verify ignition, combustion efficiency and stability, cooling, and duration requirements. A total of 46 combustion tests were performed among which 23 tests were parallely performed with stability rating tests using a pulse gun device. The test results have revealed that the 30-$ton_f$ regeneratively-cooled combustion chamber fully complies to the performance and combustion stability requirements and thus concluded that the development is successfully completed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1021-1025
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• 2017

Numerical heat/flow analysis was performed on a liquid rocket engine head with the cooling water manifold to ensure the durability of a ground test facility for heat exchanger. Through these studies, the shapes of the injector and the flow path were determined and applied to the head of the engine under development. Firing tests were conducted to verify the designed coolant manifold and no thermal damage was found on the engine-head-face. Comparing the combustion test results with the numerical analysis, the outlet temperature of coolant showed a difference of about $15^{\circ}C$. This trend is reasonable considering existence of LOX manifold, thermal barrier coating, and the actual location of flame.

• Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
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• v.23 no.8
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• pp.110-115
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• 2009

Recently, there has been a growing global interest in environmental conservation, and the field of electric power equipment has been working to become more environment-friendly. Accordingly, the low noise cooling fan of power transformers was developed through the improvement of blade shape. These are expected to apply to existing power transformers and low noise transformers. It is essential for low noise fan to possess good cooling performance as well as low audible noises. But, there was not analysis on the audible noise level and the cooling performance for low noise cooling fans until present. In this paper, we measure the audible noise level and the flow rate of low noise cooling fans to inspect the performance, Also, we confirmed that the low noise cooling fan is available to apply to power transformers through temperature rise tests of power transformers.

• The Bulletin of The Korean Astronomical Society
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• v.24 no.2
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• pp.46-46
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• 1999

• 기계와재료
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• v.12 no.4 s.46
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• pp.115-121
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• 2000

• Proceedings of the Korean Nuclear Society Conference
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• 2001.05a
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• pp.187.1-187
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• 2001

• Proceedings of the Korean Nuclear Society Conference
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• 2001.05a
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• pp.518.2-518
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• 2001

• Proceedings of the Korean Nuclear Society Conference
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• 2003.10a
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• pp.98.2-98.2
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• 2003

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.756-762
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• 2011

A gas deflector cooling system plays an important role in the suppression of shock wave generated during the ignition of a launch vehicle engine. Also, this system decrease a large vibration of damaging the payload and structure of the launch vehicle. The gas deflector cooling system in the launch pad of NARO space center was constructed to directly inject water into the plume of the launch vehicle engine. The flight test result of NARO space launch vehicle showed that this method had a good performance on the viewpoint of cooling the gas deflector.