• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.2
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• pp.48-55
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• 1999

Performance analysis of a 50KW turbo-generator gas turbine engine with a recuperator was studied. Recuperated cycle has been employed to meet maximum fuel economy and ultra low emissions especially for military and vehicular engines. From thermodynamic stand point, it is known that recuperative cycle can contribute most to enhance thermal cycle efficiency for the Pressure ratios under 10 and of comparatively low turbine inlet temperature. Efficiency of a simple cycle with a recuperator increases relatively about 30% than without one at effectiveness of 0.5. Pressure losses in the heat exchanger less than 5.2% is considered in the design process. A tubular type heat exchanger is selected for this particular engine because it can provide simple construction as well as structural sturdiness and excellent leak tightness.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.1
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• pp.65-78
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• 2010

DARPA carries out several R&D programs for hypersonic vehicles to maintain the U.S. military superiority in air and space. Falcon program is the core of the DARPA's activitiy for the hypersonics including the long-term step-by-step approach from HTV-1, HTV-2, HTV-3X to HCV. Hypersonic Turbo-Based Combined Cycle (TBCC) engine technologies research and development programs, HiSTED, FaCET and Vulcan, are also the parts of their activities. Present article presents the summarized review on the backgrounds, technologies and relationships of those programs.

• 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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• 2017.05a
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• pp.583-586
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• 2017

Infrared signal measurement are conducted from a micro-turbo jet engine with different nozzle configurations. The conventional cone type, a S-shaped type with aspect ratio 5.2 and five rectangular type nozzle with different aspect ratios are used for this experiment work. The result show that infrared signal from the exhaust gas decrease as the aspect ratio increase. In case of S-shaped nozzle, the maximum infrared signal is reduced about 28.4% when compared of rectangular nozzle with aspect ratio 5(AR5).

• 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.

• Journal of Aerospace System Engineering
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• v.11 no.5
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• pp.56-64
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• 2017

A high altitude long endurance aircraft which carries out missions of environmental research communication relay or ground surveillance, should have the capacity to cruise in the stratosphere at a relatively low speed for a long dwell time without the necessity of refueling. When one considers the propulsion system for such an aircraft, a reciprocating engine with a serial turbo-charger system to boost rarefied ambient air up to sea level condition, would represent an good, informed and practical choice regardless of the cruising altitude of the aircraft. In this paper, high altitude long endurance aircraft developed by overseas research groups and research trends, regarding multi-stage turbocharger systems, are introduced.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.389-392
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• 2011

In this study, the engine performance data was extracted and analyzed through the flight test of Smart UAV which is tilt rotor aircraft. The flight test was conducted for the transition flight regime where the tilt angle of prop-rotor varies from 90 degree to 0 degree and vice versa. The engine performance data such as engine power and specific fuel consumption gathered from flight tests were compared well with the results of engine performance analysis program.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.4
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• pp.42-49
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• 2019

This paper presents a method to predict the storage reliability of springs for turbo engine components based on an accelerated degradation test. The reliability assessment procedure for springs is established to proceed with the accelerated degradation test. The spring constant is selected as the performance degradation characteristic, the temperature is determined to be the stress factor that deteriorates the spring constant. The storage tests are performed at three temperature test conditions. The spring constant is measured periodically to check the degradation status of the springs. Failure times of the springs are predicted by using the degradation model. Finally, the storage lifetime of the springs at normal use conditions is predicted using an accelerated model and failure times of all test conditions.

• Journal of Advanced Marine Engineering and Technology
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• v.39 no.6
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• pp.626-632
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• 2015

The International Maritime Organization (IMO) has adopted several regulations for the prevention of air pollution from ships. In addition, there is a requirement for shipping liners to reduce greenhouse gas emissions. Accordingly, we need to take measurements to ensure that the steps taken are both efficient and environmentally friendly. It has been determined that the application of the Miller cycle in diesel engines has the effect of both reducing the amount of NOx and improving thermal efficiency. However, this method requires a considerably larger charge air pressure. Therefore, we consider a two-stage turbo-charging system, which not only results in a high charging pressure, but also improves the part load performance with an exhaust-gas bypass system or the application of the Miller cycle. Because of complications associated with the two-stage turbo-charging system, it is complex and difficult to realize a design that optimizes matching between diesel engine and turbo-chargers. Accordingly, it is necessary to perform a quantitative analysis to determine the effects and optimal conditions of these different systems in the early stage of system design. In this paper, we develop a simulation program to model these systems, and we verify that the results of this program are reliable. Further, we discuss methods that can be employed to improve its efficiency.

• Transactions of the Korean Society of Mechanical Engineers
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• v.19 no.2
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• pp.580-590
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• 1995

To design and develop a turbocharged engine, ti needs that many study must be preceded about the characteristics of engine performance. Especially, a basic data about deciding target power is urgently needed for which is practically useful for engine design. The power output of turbo-charged engine is dominated by engine speed, displacement, compression ratio, air fuel ratio and charge pressure ratio. Therefore, the independent effect of these factors on power output was clarified from experiment, and the experimental equation to predict the power was founded from there results. The predicted power output from the experimental equation was well coincided with power measured through experiment.