• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.368-373
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• 2005

To achieve efficient combustion within a manageable length, a successful fuel injection scheme must provide rapid mixing between the fuel and airstreams. The aim of the present numerical research is to investigate the mixing enhancement combustion phenomena according to fuel injector location near the cavity in supersonic flow. Fuel injector location changes the actual length to depth ratio of the cavity in the supersonic combustor. Therefore fuel injector location near the cavity effects different fuel/air mixing efficiency and combustion efficiency.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.1
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• pp.18-26
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• 2007

A development of monopropellant thruster for microsatellite that uses concentrated hydrogen peroxide is described. Catalyst, the most important component in the thruster, was prepared and coated on a monolith honeycomb. Performance evaluation of thruster was peformed by considering the efficiency of characteristic velocity and ignition delay. As a result, 96.0% of $C^*$ efficiency was obtained at designed propellant flowrate and steady state operating condition.

• Journal of Advanced Marine Engineering and Technology
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• v.36 no.7
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• pp.942-947
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• 2012

As electricity has been used in ship's propulsion, it is necessary to increase the system voltage and current for the electrical distribution system. So it is required to improve the system safety and efficiency, the power stability, the efficiency of the generation through various analysis of ship's electric power system. In this paper, the electrical service reliability of the power distribution system of semi submersible drilling rigs has been analysed and discussed using ETAP.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.5
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• pp.65-71
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• 2010

Performance test of the 75ton class turbopump turbine was performed. Using the measured turbine power characteristics in the wide-range operational conditions, variations of nozzle velocity ratio, total pressure loss, and relative flow angle to the pressure ratios and rotational speeds are quantified. Efficiency and nozzle exit pressure behavior was also investigated and compared with 30ton turbopump turbine data. A rotor blade was redesigned based on the test results and CFD analysis.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2003.11a
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• pp.316-323
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• 2003

The gear system is commonly applied in the marine propulsion shafting system using the diesel engine with the power take off/in system and it also is necessary to reduce propeller revolution increasing the propulsion efficiency. The diesel engine has the advantage more than other thermal engines in high thermal efficiency and mobility. But the large vibratory torque which induced by higher combustion pressure is transmitted to these gears. In this paper, the surface durability and bending stress of gear system considering vibratory and transient torque is evaluated by ISO and AGMA regulation. And the influence of these in gear design is investigated with the theoretical analysis and onboard measurement result of torsional vibration.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.622-627
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• 2004

There are many difficulties in realizing Ultra-micro gas turbine system. Among them, the effects of tip clearance upon the micro turbine flowfield are discussed in this paper. The flowfield was investigated numerically with the Reynolds-averaged three-dimensional thin-layer Navier-Stokes equations. Calculations were conducted with clearance height from 0％ to 10% of the passage height. Leakage mass flow and deterioration of efficiency are proportional to the clearance height for the clearance height larger than 4%. However, in the case of 2% clearance, leakage flow is significantly reduced due to relative motion of the casing and as a result deterioration of efficiency is very small. It is difficult to control tip clearance in micro turbines, but the results of this study indicate that if the clearance height is controlled within a few per-cent of passage height, deterioration of stage performance will be small.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.314-317
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• 2004

On 9/5/2003, the planet probe “HAYABUSA” as MUSES-C project was launched by The Institute of Space and Astronautical Science. “HAYABUSA” has microwave discharge ion engines and these engines are characterized by their high efficiency and specific impulse in comparison with chemical engine. A large ion engine can be used as a planet explorer, while a small ion engine can be used as attitude control of small satellite. We have been developing a high thrust density microwave discharge ion engine using “Multi-Monopole Antenna”. The performance of this engine are: ion cost of 344W/A, propellant utilization efficiency of 52% and thrust density of 0.055mN/$\textrm{cm}^2$ for Kr gas flow rate of 2.5sccm, microwave(2.45㎓) power of 32W and acceleration voltage of l.4㎸.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.38-44
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• 2010

Performance test of the 75ton class turbopump turbine was performed. Through the turbine power measurement in the wide-range operational conditions, velocity ratio, total pressure loss, and relative flow angle characteristics was quantified. Efficiency and nozzle exit pressure behavior was also investigated and compared with 30ton turbopump turbine data. A rotor blade was redesigned based on the test results and CFD analysis.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.378-382
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• 2008

A 50 N monopropellant thruster being developed for attitude control in a variety of aerospace application systems is described in this paper. Ninety percent hydrogen peroxide was selected as a propellant, since it is much less hazardous than hydrazine. A scaled down thruster with aluminum oxide loaded with the platinum in the reaction chamber was tested to determine propellant decomposition onto a catalyst. A scaled up 50 N thruster, with a catalyst bed of 3 cm in diameter and 4 cm in length, was evaluated by decomposition efficiency based on temperature, ${\eta}_T$, efficiency of characteristic velocity, ${\eta}_{C^*}$, and measurement of thrust. The performance of a 50 N thruster was 40.5 Newton in thrust, about 100 % in ${\eta}_T$, and 98 % in ${\eta}_{C^*}$, and 125 sec in specific impulse at sea level.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.163-166
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• 2012

The hybrid combustion were performed with the different diaphragm position for the experimental studies on characteristic of regression rate and combustion efficiency. The diaphragm was installed in 25% and 50% of fuel length from the front of solid fuel, respectively. As results of experiments, the position of diaphragm has small effect on the regression rate and combustion efficiency. It is considered that the diaphragm has local effect near the diaphragm.