• International Journal of Aeronautical and Space Sciences
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• v.15 no.4
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• pp.434-443
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• 2014

A turbo fan engine performance analysis and the optimization using particle swarm optimization(PSO) algorithm have been conducted to investigate the effects of major performance design parameters of an aircraft gas turbine engine. The FJ44-2C turbofan engine, which is widely used in the small business jet, CJ2 has been selected as the basic model. The design parameters consists of the bypass ratio, burner exit temperature, HP compressor ratio, fan inlet mass flow, and nozzle cooling air ratio. The sensitivity analysis of the parameters has been evaluated and the optimization of the parameters has been performed to achieve high net thrust or low specific fuel consumption.

• 한국전산유체공학회:학술대회논문집
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• 1995.10a
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• pp.70-75
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• 1995

Recently, for the thermal system design in an engine room, the importance of the numerical analysis on the heat and fluid flow has been recognized. In the present study, the flow inside an engine room with complex geometry was analysed by use of TURBO-3D program being developed in KIST. Radiator and Cooling fan were simulated by porous media and momentum sources, and the result shows a good agreement with our expectation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.211-214
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• 2003

For prediction of the windmilling performance with consideration of bypass-duct loss of the twin-spool axi-centrifugal turbo-fan engine in flight condition, this study has examined the windmilling process and the physical phenomenon of the engine parts. Also, a mixing phenomenon with air passed through the bypass-duct has been analyzed. The results of the predicted windmilling performance has been compared and analyzed using the dimensional parameters.

• 유체기계공업학회:학술대회논문집
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• 1998.02a
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• pp.136-143
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• 1998

• The KSFM Journal of Fluid Machinery
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• v.13 no.6
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• pp.71-76
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• 2010

This study has investigated numerically and experimentally the flow characteristic of air-cooling fan for transmission oil cooler in the large-size diesel engine. Impellers of cooler were composed of eight normal-scale and eight small-scale blades in the zig-zag pattern. In order to increase the discharge pressure of cooling fan, turbo type of fan blade is proposed in the impeller for transmission oil cooler. The fluidic performance of cooling fan has been estimated numerically by using the commercial code and experimentally carried out with reference on AMCA Standard 210-99. As a result, it is confirmed that the numerical result for performance curve is in good agreement with experimental data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.4
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• pp.326-333
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• 2015

A turbo fan engine performance analysis program combined with a particle swarm optimization(PSO) has been developed to optimize the major design parameters of the combat aircraft gas turbine engine. The optimized parameters includes bypass ratio, fan pressure ratio, high pressure compression ratio and burner exit temperature. The objective parameters have been determined using a multi-objective function consisting of the net thrust and specific fuel consumption along a weight function. The basic model for the combat aircraft gas turbine engine has been selected as the F404 turbofan engine which is widely used in the combat aircraft, F-18 and Korean high level training aircraft, T-50. The optimal conditions of four parameters have been obtained for various design conditions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.75-78
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• 2007

In this study, low velocity impact analysis on Turbo Fan Engine composite sandwich structure was performed. Sandwich structure configuration is made of carbon/epoxy face sheets and foam cores. For validating study, the results of an experimental and of a Finite Element Method analysis were compared previously. From the Finite Element Method analysis results of sandwich panel, it was confirmed that the result of analysis was reasonable. Impactor velocity to initiate damage was estimated, and in order to investigate the damage at the predicted velocity, impact analysis using Finite Element Method was performed. According to the impact analysis results of sandwich panel, it was confirmed that the damage was generated at the estimated impact velocity.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.592-596
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• 2012

The details of engine data are essentially needed for engine modeling and simulation. But, the engine data are kept secret because the information is company's experiential property. In this paper performed the performance modeling of the mixed flow turbofan engine cycles from the general available engine data, and verify the validity.

• Journal of Applied Reliability
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• v.7 no.2
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• pp.89-100
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• 2007

For the certification of aircraft and part, it must be show the compliance with applicable requirements through system safety assessment. The safety assessment process should be planned and managed to provide the necessary assurance that all relevant failure conditions have been identified and that all significant combinations of failures which could cause those failure conditions have been considered. Complex systems, especially aircraft, should take into account any additional complexities and interdependencies which arise due to integration. In all cases involving integrated systems, the safety assessment process is of fundamental importance in establishing appropriate safety objectives for the system and determining that the implementation satisfies these objectives. This study review the safety assessment for the certification process of the aircraft engine system and analyze turbo-fan engine by fault analysis method for compliance with airworthiness requirement of aircraft engine system.

• The KSFM Journal of Fluid Machinery
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• v.15 no.5
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• pp.27-31
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• 2012

Turbine inlet temperature is steadily increasing to achieve high specific thrust and efficiency of gas turbine engines. Turbine cooling technology is essential to increase turbine inlet temperature. For this study, a small or medium sized aircraft engine of 10,000 lbf class with the turbine inlet temperature of $1,400^{\circ}C$, the engine overall pressure ratio of 32.2, and the bypass ratio of 5 was set as the baseline model and its performance analysis was performed at the design point. The engine has the performance of 10,013 lbf thrust and the specific fuel consumption of 0.362 lbm/hr/lbf. The thrust and the specific fuel consumption of the baseline model were compared with those of similar class engines. Based on these results, the turbine design requirements were assigned. In addition, the parametric analysis of the engine, related to aerodynamic and cooling design of the high pressure turbine, was performed. Based on the baseline model engine, the influence of turbine inlet temperature, cooling flow ratio, and high pressure turbine efficiency variations on the engine performance was analyzed.