• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.12-12
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• 2000

국내에서 최초로 개발된 초등훈련기 KT-1의 추진기관인 터보프롭 엔진(PT6A-62)을 위한 정상상태 성능모사 및 진단 프로그램을 개발하였다. 개발된 정상상태 성능해석 프로그램의 검증을 위해 해석 결과를 엔진 제작사에서 제공한 성능 데이터 및 가스터빈 엔진의 성능모사 프로그램으로 잘 알려진 GASTURB와 비교하였다.(중략)

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.12
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• pp.1238-1244
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• 2009

This work proposes a GUI-type on-line diagnostic program using SIMULINK and Fuzzy-Neuro algorithms for a helicopter turboshaft engine. During development of the diagnostic program, a look-up table type base performance module for reducing computer calculating time and a signal generation module for simulating real time performance data are used. This program is composed of the on-line condition monitoring program to monitor on-line measuring performance condition, the fuzzy inference system to isolate the faults from measuring data and the neural network to quantify the isolated faults. The reliability and capability of the proposed on-line diagnostic program were confirmed through application to the helicopter engine health monitoring.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.1
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• pp.80-88
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• 2013

In currently developed engine condition monitoring systems, most field engine maintenance engineers have difficulties to use them in fields due to complexity, unpractical use, lack of understanding, etc. Therefore a practical usable engine condition monitoring system must be needed. This work proposes a practical performance condition monitoring of a small turbojet engine through comparing between the on-line performance monitoring data and the initial clean performance data calculated by the base engine performance model. Moreover the proposed monitoring system checks the gas path components' on-line health condition through comparing the component performance characteristics between the running engine represented as a deteriorated engine or a degraded engine and the base engine performance model represented as a clean engine. The proposed condition monitoring system is coded in a friendly GUI type program for easy practical application by a commercial tool, MATLAB/SIMULINK and LabVIEW.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.4
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• pp.60-68
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• 2003

In this study, a steady state performance analysis program was developed for a turbofan engine, and its performance was analyzed at installed conditions. For the purpose of evaluation, the developed program was compared with the performance data provided by the engine manufacturer. It was confirmed that the developed program was reliable because the results by the developed program were well agreed with those by the engine manufacturer within 3.5%. The non-linear GPA(Gas Path Analysis) program for performance diagnostics were developed, and selection of optimal measurement variables was studied. Furthermore, in order to investigate effects of the number and the kind of measurement variables, the non-linear GPA was analyzed with various measurement sets. Finally, the measurement parameters selected in the previous step were applied to the fault detection analysis of the 2-spool separate flow type turbofan engine.

• 한국IT서비스학회:학술대회논문집
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• 2009.05a
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• pp.335-338
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• 2009

통합통신서비스는 차세대 정보서비스산업에서 중요한 위치를 차지할 것으로 기대되고 있다. 전화, 이메일, 인스턴트 메시징, 팩스, 음성사서함과 같은 여러 종류의 통신매체를 통합한 서비스를 제공하기 위해서는 각매체를 연결하는 통일된 통신 프로토콜이 필요한데, 현재 가장 각광받고 있는 통신프로토콜은 인터넷 기술에 기반한 SIP (Session Initiation Protocol)이고, 이를 활용하기위한 프로그래밍 인터페이스로는 기존 웹프로그래머에게 익숙한 Servlet 형식을 갖고 있는 SIP Servlet 이 제공되고 있다. 그러나 프로그래머 인터페이스의 유사성과는 별개로 시스템의 처리용량이 증가할 때 발생하는 성능상의 문제를 해결하기 위해서는 SIP 응용프로그램의 특성을 고려하여 진단을 수행하고 운영파라미터를 조정하여야 한다. 또한 응용프로그램설계에 있어서도 전통적인 웹응용프로그램에서는 무시되었던 부분이 중요한 성능방해요소로 작용하기 때문에 주의가 필요하다. 이 논문은 공개된 인터넷망에서의 서비스를 목적으로 개발된 통합통신서비스를 개발하는 과정을 중심으로 성능문제의 진단과 개선 사례를 소개하고 응용프로그램 설계에서의 고려사항에 대해서 논의한다.

• Journal of Aerospace System Engineering
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• v.13 no.1
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• pp.38-46
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• 2019

There is a growing interest in engine diagnostic technology for gas turbine engines. An engine simulation program, precisely simulating the engine performance, is required in order to apply it to the engine diagnosis technology for engine health monitoring. In particular, the simulation program can predict not only design point performance but also off-design point and partial load performance in accurate. So the engine simulation program for the 2-spool separate flow type turbofan engine was developed and the JT9D-7R4G engine of PW(Pratt & Whitney) was analyzed. The steady-sate performance analysis is conducted at both design and off-design points in flight path and the differences between analysis results of takeoff and cruise conditions are compared. The effect of Reynold's correction method was analyzed as a scaling method of the engine component performance. The simulation results was compared with NPSS.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.4
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• pp.87-97
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• 2000

A steady state performance simulation and diagnostics program for the turboprop engine (PT6A-62), which is the power plant of the first developed military basic trainer KT-1 in Republic of Korea, was developed. The developed steady state performance analysis program was evaluated with the performance data provided by the engine manufacturer and with analysis results of GASTURB program, which is well known for the performance simulation of gas turbines. Performance parameters were discussed to evaluate validity of the developed program at various cases such as altitude, flight velocity and part load variation. GPA(Gas Pass Analysis) allows engine performance deterioration to be identified at the module level in terms of reduction in component efficiencies and changes in mass flow. In order to find optimal instrument set to detect the physical faults such as fouling, erosion and corrosion, a gas path analysis approach is utilized. This study was performed in two cases for selection of optimal measurement parameters. One case was considered with the effect of instrument number by changing independent parameter number. The other case was performed with selection of independent parameter set. According to the analysis results, the optimal measurement parameters selected were eight dependent variables such as shaft horsepower, fuel flow rate, compressor exit pressure and temperature, compressor turbine inlet pressure and temperature and power turbine inlet pressure and temperature.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.281-284
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• 2006

An intelligent performance diagnostic program using the Neural Network was proposed for PW206C turboshaft engine. It was selected as a power plant for the tilt rotor type Smart UAV (Unmanned Aerial Vehicle) which has been developed by KARI (Korea Aerospace Research Institute). The measurement parameters of Smart UAV propulsion system are gas generator rotational speed, power turbine rotational speed, exhaust gas temperature and torque. But two measurement such as compressor exit pressure and compressor turbine exit temperature were added because they were difficult each component diagnostics using the default measurement parameter. The performance parameters for the estimate of component performance degradation degree are flow capacities and efficiencies for compressor, compressor turbine and power turbine. Database for network learning and test was constructed using a gas turbine performance simulation program. From application results for diagnostics of the PW206C turboshaft engine using the learned networks, it was confirmed that the proposed diagnostics could detect well the single fault types such as compressor fouling and compressor turbine erosion.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.105-113
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• 2002

In this study, the steady state performance analysis program was developed for a turboprop engine, and its performance was analyzed at uninstalled and installed conditions. For the purpose of evaluation the developed program was compared with the performance data provided by the engine manufacturer and analysis results of GASTURB8.0 program. It was confirmed that the developed program was reliable because the results by the developed program were well agreed with those by GASTURB8.0 within %%. The linear and non-linear GPA(Gas Path Analysis) programs for performance diagnotics were developed, and selection of optimal measurement variables was studied. Furthermore, in order to investigate effects of the number and the kind of measurement variables, the linear and non-linear GPAs were analyzed with various measurement set. If the measurement parameters were properly selected, the reliable and economic faults detection might be possible even thought the small number of measuring parameters were used.

• Proceedings of the Korea Society for Simulation Conference
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• 1999.10a
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• pp.133-137
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• 1999

STAREX 교환기의 DBMS는 교환기 시스템의 호처리, 운용, 보전 등에 관련된 모든 데이터를 유지하면서, 응용 프로그램 데이터의 효율적 지원, 데이터의 일관성 유지, 데이터의 백업, 데이터의 무결성 진단 및 복구 등의 종합적인 관리를 수행하는 시스템 소프트웨어이다. 또한, DBMS는 교환기의 실시간 처리 요구를 만족시키기 위하여 여러 가지 기능들을 제공한다. 그러나, 이러한 기능들은 응용 프로그램들이 얼마나 효율적으로 사용 하느냐에 따라 성능이 크게 좌우된다. 본 논문에서는 STAREX 교환기의 DBMS가 제공하는 실시간 처리 기능들을 소개하고, 교환기의 성능을 향상시키기 위하여 응용 프로그램들이 효율적으로 데이터베이스에 접근하는 방안을 제시한다.