• Proceedings of the SAREK Conference
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• 2006.11a
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• pp.45-45
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• 2006

• 유체기계공업학회:학술대회논문집
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• 2001.11a
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• pp.83-90
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• 2001

Experimental and numerical investigations of the off·design performance of a simple channel-wedge diffuser in a small centrifugal compressor are presented. Surge and choke conditions as well as design point are considered using somewhat limited range of experimental data and also supplementary 3D CFD results. Some critical meanline design parameters' behavior is investigated numerically, to render the basis for improved modelings in the meanline performance prediction.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.7
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• pp.36-43
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• 2002

A new scaling method for the prediction of gas turbine components characteristics using experimental data or partially given data from engine manufacturers has been proposed. In order to minimize the analyzed performance error in the this study, firstly component maps were constructed by identifying performance data given by engine manufacturers at some operating conditions, then the simulated performance using the identified maps was compared with the performance result using the currently used traditional scaling method. In comparison, the performance result by the currently used traditional scaling method was well agreed with the real engine performance at on-design point but it had maximum 12% error at off-design points within the flight envelope of a study turboprop engine. However because the analysed performance by the newly proposed scaling method had maximum 6% reasonable error even within all flight envelope.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.3
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• pp.60-67
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• 2008

In this study, the genetic algorithm has been used for the real-time defect diagnosis on the operation of the aircraft gas-turbine engine. The component elements of the gas-turbine engine for consideration of the performance deterioration consist of the compressor, the gas generation turbine and the power turbine. Compared to the on-design point, the teaming data has been increased 200 times in case off-design conditions for the altitude, the flight mach number and the fuel consumption. Therefore, enormous learning time has been required for the satisfied convergence. The optimal division has been proposed for learning time decrease as well as the high accuracy. As results, the RMS errors of the defect diagnosis using the genetic algorithm have been confirmed under 5 %.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.350-353
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• 2007

In this study, the genetic algorithm has been used for the real-time defect diagnosis on the operation of the aircraft gas-turbine engine. The component elements of the gas-turbine engine for consideriation of the performance deterioration is consist of the compressor, the gas generation turbine and the power turbine, repectively. Compared to the on-design point on the sea-level condition, the learning data has been increased 200 times in case of the off-design conditions for the altitude, the flight mach number and the fuel consumption. Therefore, enormous learning time has been required for the satisfied convergence. The optimum division has been proposed to decrease learning time as well as to obtain high accuracy. As results, the RMS errors of the defect diagnosis using the genetic algorithm have been estimated under 5 %.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.2
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• pp.15-23
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• 2008

A numerical method based on the prediction of total pressure loss of major components of the engine has been developed for prediction of the windmilling start performance of micro-turbojet engine. The start performance in on/off design region has been analysed by applying this method to predict windmilling start-able regions of the centrifugal-type engine. The results of this analysis have been validated by comparing with the test data. The effect of each design parameters on windmilling start performance has been analysed for the enlargement of start-able regions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.173-176
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• 2010

A subscale gas generator was designed and manufactured to understand a reason for increased pressure drop of liquid oxygen injectors observed in a technology demonstration model of a 75 ton-class gas generator. A total of 6 hot-firing tests were successfully performed including experimental conditions of design and off-design points. The hot-firing results showed that discharge coefficients of fuel and liquid oxygen remained constant as the mixture ratio varied at a fixed chamber pressure. At a fixed mixture ratio, it was also found that discharge coefficients of fuel and liquid oxygen was constant as the chamber pressure was increased.

• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.2
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• pp.47-55
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• 1998

Steady-state and transient performance for the medium scale civil aircraft turbofan engine was analyzed. Steady-state performance was analyzed on maximum take-off condition, maximum climb condition, and cruise condition. At 90％RPM of the low pressure compressor, the partload performance was economized. The transient performance was analyzed with cases of the step increase, the ramp increase, the ramp decrease, and the step increase and ramp decrease for the input fuel flow. For the transient performance analysis, work matching between compressor and turbine was needed. Modified Euler method was used the integration of residual torque in work matching equation. At all flight condition, the overshoot of the high pressure turbine inlet temperature was appeared in the step and ramp increase case, and the surge of high pressure compressor was appeared in the step increase case and the ramp increase case within 5.5 seconds of maximum climb condition.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.346-350
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• 2005

Effects of the changes of a film cooling mass flow rate and operating conditions on the heat flux characteristics of the subscale calorimeter were studied. A film cooling ring with twelve orifices is inserted between the injector head and the calorimeter. The calorimeter is composed of nineteen cooling channels. When a mass flow rate of film cooling is 10.5 % of a main fuel mass flow rate, maximum heat flux at the nozzle throat is decreased by 30% compared to that without film cooling. In the OD3(of-design point) test result, maximum heat flux at the nozzle throat is increased by 31% compared to that of the DP(design point) test when a film cooling flow rate is zero.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2015.10a
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• pp.536-538
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• 2015

전기 에너지가 우리 생활에 유용하게 사용되는 부분이 정말 많다. 최근에는 자전거 열풍이 불면서 덩달아 전동 자전거 업계에도 호황이 일고 있는데, 21C 기후 변화와 환경오염, 교통체증 등의 문제해결을 위한 저탄소 녹색성장의 인식 전환으로 전동 자전거 이용이 늘어나고 있다. 이는 전동 자전거도 전기 에너지가 사용되고 있다 점이다. 하지만 이런 장점을 가지고 있는 전동 자전거를 많은 사람들이 구입하지 못하는 이유가 있다. 대부분의 이유가 '집에 자전거 1대씩 가지고 있는데, 굳이 비싼 돈을 주고 전동 자전거를 구입해야하나?' 라는 생각을 가지게 된다. 또 다른 이유로는 기존의 전동 자전거가 탈 부착 형식이 아닌 일체형으로 나오기 때문에 다른 신제품의 전동 자전거가 나온다면 기존의 전동 자전거의 부품을 사용하지 못 하고 새로운 자전거를 사야 한다는 단점 때문이다. 따라서 본 논문에서는 탈 부착이 가능한 전기 자전거 시스템을 구현하고자 한다.