• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.213-217
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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). For teaming the NN, a BPN with one hidden, one input and one output layer was used. The input layer had seven neurons of variations of measurement parameters such as SHP, MF, P2, T2, P4, T4 and T5, and the output layer used 6 neurons of degradation ratios of flow capacities and efficiencies for compressor, compressor turbine and power turbine. Database for network teaming 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 algorithm could detect well the single fault types such as compressor fouling and compressor turbine erosion.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.2
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• pp.15-22
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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 is being developed by KARI (Korea Aerospace Research Institute). For teeming the NN(Neural Network), a BPN(Back Propagation Network) with one hidden, one input and one output layer was used. The input layer has seven neurons: variations of measurement parameters such as SHP, MF, P2, T2, P4, T4 and T5, and the output layer uses 6 neurons: degradation ratios of flow capacities and efficiencies for compressor, compressor turbine and power turbine, respectively, Database for network teaming and test was constructed using a gas turbine performance simulation program. From application of the learned networks to diagnostics of the PW206C turboshaft engine, it was confirmed that the proposed diagnostics algorithm could detect well the single fault types such as compressor fouling and compressor turbine erosion.

• 보일러설비
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• s.71
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• pp.59-67
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• 1999

이 논문에서는 태양발전과 저장을 위한 환경친화적 장치에 대하여 기술하였다. 컴퓨터 모델에 주안점을 두고 시스템의 최적 발전조건을 계산하였는데, 여기에는 작동유체 효율과 태양열 집열판의 크기와 효율 그리고 출력이 포함되어 있다. 영국과 멕시코의 기후조건들이 분석되고, 각 위도에 대한 신뢰 할만한 최근 기상자료가 컴퓨터 수치모사에 사용되었다. 결과를 보면, 연간 출력 4000kW.h를 얻기 위해서, 영국의 경우 시스템 설치에 필요한 집열 면적은 $92m^{\2}$이며, 멕시코의 경우에는 유사 모사조건하에서 동일한 출력을 얻기 위해서는 $48m^{\2}$의 집열면적이 필요하다. 터빈과 이송펌프, 발전기 등의 효율에 민감하여 약간의 효율향상이 있으면 집열 면적을 현저히 감소시킬 수 있다.

• Proceedings of the KIEE Conference
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• 1998.07b
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• pp.787-791
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• 1998

본 논문에서는 ${\alpha}$, ${\beta}$분리 및 결합형, 피드 포워드형, 미분선행형(PI형)의 2-자유도 PID제어기의 각 종류에 대해 파라메터 변화에 따른 특성을 가스 터빈의 연료 제어계통 전달함수를 이용해 비교 고찰하였다. ${\alpha}$, ${\beta}$는 제어기의 출력 특성에 크게 영향을 미치나 ${\gamma}$는 크게 영향을 미치지 않는 것으로 나타났고 각 제어기의 특성에서는 ${\alpha}$, ${\beta}$결합형이 가장 양호한 출력 특성이 나타났다.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1995.11a
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• pp.110-114
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• 1995

This paper is dealing with speed control of Darrieus Wind Turbine, which can be figured out from torque equation. The operating point of Darrieus Wind Turbine can be found from speed-torque curve, which is either stable or instable. The transfer of operating point due to variation of wind speed and generating power is shown in this paper.

• Proceeding of EDISON Challenge
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• 2015.03a
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• pp.563-568
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• 2015

풍력터변의 성능을 높이기 위한 방법으로 최근 해외에서는 쉬라우드를 장착하여 유입 유량을 증진시키는 형상에 대한 새로운 아이디어가 제안되고 시범적으로 적용되고 있다. 본 연구에서는 쉬라우드가 장착된 수평축 풍력터빈에 대해서 EDISON CFD를 이용하여 쉬라우드 내부로 유입되는 질량 유량의 변동을 몇 가지 형상에 대해 수치적으로 비교 분석하였다. 유동장은 비압축성 난류유동으로 가정하였으며, 수치 해석 결과로부터 쉬라우드 주변의 순환의 세기를 형상 변동에 따라 도출하였다. 쉬라우드 형상으로는 캠버를 갖는 goe 417 에어포일을 두 개의 받음각(5도, 10도)에 대해서 수치해석을 수행하였으며, 브림을 갖는 디퓨저 형상(Wind-lens)에 대해서도 유입 유량 변동과 순환 세기에 대해 수치해석을 수행하고 결과를 상호 비교하였다. 본 연구를 통해 쉬라우드가 발생시키는 순환에 의한 유입 유량 증가 현상을 파악할 수 있었으며, 이로써 풍력터빈의 출력을 증대시킬 수 있음을 확인하였다.

• Proceedings of the KIPE Conference
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• 2018.11a
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• pp.15-17
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• 2018

본 논문은 DFIG기반의 가변속 양수발전소의 조속기, 터빈-수압관(penstock), 발전기/컨버터 및 시스템 제어기를 모델링하였으며, 발전기/컨버터 모델은 하나의 전류원과 임피던스로 등가화 되었다. 최적 운전 조건을 위한 터빈의 속도와 게이트 위치 지령치는 시스템 제어기를 통해서 얻을 수 있으며, 계통 전력의 지령치를 통해서 발전기/컨버터 모델의 전류 지령치를 만들며. 터빈 회전속도와 게이트 위치는 DFIG의 속도와 지령 속도의 비교를 통해 출력된다. 시뮬레이션 모델링을 통해 전력의 지령치 변화에 따라 계통의 전력과 터빈의 응답성을 확인하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.4
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• pp.99-105
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• 2002

The performance test of an axial-type turbine is carried out with various axial gap distances between the stator and rotor. The turbine is operated at the low pressure and speed, and the degree of reaction is 0.373 at the mean radius. The axial-type turbine consists of ons-stage and 3-dimensional blades. The chord length of rotor is 28.2mm and mean diameter of turbine is 257.56mm. The power of turbo-blower for input power is 30kW and mass flow rate is $340m^3$/min at 290mmAq static-pressure. The RPM and output power are controlled by a dynamometer connected directly to the turbine shaft. The axial gap distances are changed from a quarter to three times of stator axial chord length, and performance curves are obtained with 9 different axial gaps. The efficiency varies about 8% of its peak value due to the variation of axial gap on the same non-dimensional mass flow rate and RPM, and experimental results show that the optimum axial gap is 1.6-1.9Cx.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.9
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• pp.943-954
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• 2010

In this study, a radial inflow type turbine was applied and the outer diameter of the turbine rotor was 108 mm. The turbine blade on a circular plate disc was designed as an axial-type because its partial admission rate was 1.4-4.1%. The turbine consisted of three stages. The performance test has been conducted with various admission rates, tip clearances and nozzle flow angles. The turbine output power was measured on each stage. The turbine performance was obtained in a wide rotational speed range in order to compare its performance according to various operating conditions. The net specific output torque was also measured to compare its overall performance. Computational analysis was conducted for predicting turbine performance. The computed results were in good agreement with the experimental results.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.11
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• pp.1015-1022
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• 2013

This study simulates the operation of a 200 kW class micro gas turbine that is currently under development. The performance and operating characteristics depending on the load control scheme (constant turbine inlet temperature versus constant turbine exit temperature) and ambient condition were investigated using detailed component performance data. The sensitivities of operating parameters, such as the compressor surge margin and flow path temperatures, according to unit fuel flow change were predicted for a wide load range. The sensitivity analysis showed that the steady state calculation provided useful information about the maximum surge margin reduction during load change.