• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2010년도 춘계학술대회 초록집
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• pp.186.2-186.2
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• 2010

풍력발전기의 구성요소 중 브레이드는 바람의 운동에너지를 회전력으로 변환하는 핵심요소이며, 효율적인 설계기법이 절실히 요구되는데 선진국에서는 설계기술을 회피하는 실정으로 브레이드 형상 설계기법의 확보는 어려운 실정이다. 본 논문은 날개요소 운동량이론(BEMT) 및 X-foil을 이용하여 10kW급 브레이드 국산화 개발에 목적을 두고 공기역학적 설계를 수행하여 국내 풍황에 적합한 최적의 풍력발전기 에어포일을 개발하는데 목적을 두고 그 방안을 제시한다.

• 에너지공학
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• 제29권1호
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• pp.34-43
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• 2020

풍력발전기 로터의 저속운전 가능성에 대해 기동토크를 평가하고자 하였다. 본 연구에서 살펴본 저속시동 가능성의 날개는 초임계에어포일을 보완하여 AMI계열(AMI903 및 AMI904)의 날개를 제안하여 공력성능을 유지하며 제작상 및 유지보수의 어려움을 제거하였다. 따라서 본 연구는 FLUENT를 이용하여 난류유동 해석을 통해 제안된 날개의 받음각(-180°~+180°)에 대한 항력계수와 양력계수를 제시하였으며, 이 값들로부터 정지하고 있는 날개의 회전 위치에 따른 접선방향의 토크계수를 정의하여 제시하였다. 기동력의 크기와 방향을 결정할 토크계수는 대부분 양의 값(반시계방향)으로 나타났으며 특별히 받음각이 0°에서 180° 및 -90°에서 -180°에서 양의 값이며 0°에서 -90°에서 매우 작거나 음의 값을 나타냈다. 한편 기동토크는 두께가 얇은 AMI903보다 두꺼운 AMI904에서 더 큰 것으로 나타났다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2009년 춘계학술대회논문집
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• pp.19-19
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• 2009

Dynamic Stall is a flow phenomenon which occurs on the retreating side of helicopter rotor blades during forward flight. It also occurs on blades of stall regulated wind turbines under yawing conditions as well as during gust loads. Time scales occurring during this process are comparable on both helicopter and wind turbine blades. Dynamic Stall limits the speed of the helicopter and its manoeuvrability and limits the amount of power production of wind turbines. Extensive numerical as well as experimental investigations have been carried out recently to get detailed insight into the very complex flow structures of the Dynamic Stall process. Numerical codes have to be based on the full equations, i.e. the Navier-Stokes equations to cover the scope of the problems involved: Time dependent flow, unsteady flow separation, vortex development and shedding, compressibility effects, turbulence, transition and 3D-effects, etc. have to be taken into account. In addition to the numerical treatment of the Dynamic Stall problem suitable wind tunnel experiments are inevitable. Comparisons of experimental data with calculated results show us the state of the art and validity of the CFD-codes and the necessity to further improve calculation procedures. In the present paper the phenomenon of Dynamic Stall will be discussed first. This discussion is followed by comparisons of some recently obtained experimental and numerical results for an oscillating helicopter airfoil under Dynamic Stall conditions. From the knowledge base of the Dynamic Stall Problems, the next step can be envisaged: to control Dynamic Stall. The present discussion will address two different Dynamic Stall control methodologies: the Nose-Droop concept and the application of Leading Edge Vortex Generators (LEVoG's) as examples of active and passive control devices. It will be shown that experimental results are available but CFD-data are only of limited comparison. A lot of future work has to be done in CFD-code development to fill this gap. Here mainly 3D-effects as well as improvements of both turbulence and transition modelling are of major concern.

• 대한기계학회논문집B
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• 제21권2호
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• pp.316-328
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• 1997

There were appreciable progresses on the study of shock wave / boundary layer interaction control in the transonic flow without nonequilibrium condensation. But in general, the actual flows associated with those of the airfoil of high speed flight body, the cascade of steam turbine and so on accompany the nonequilibrium condensation, and under a certain circumstance condensation shock wave occurs. Condensation shock wave / boundary layer interaction control is quite different from that of case without condensation, because the droplets generated by the result of nonequilibrium condensation may clog the holes of the porous wall for passive control and the flow interaction mechanism between the droplets and the porous system is concerned in the flow with nonequilibrium condensation. In these connections, it is necessary to study the condensation shock wave / boundary layer interaction control by passive cavity in the flow accompanying nonequilibrium condensation with condensation shock wave. In the present study, experiments were made on a roof mounted half circular arc in an indraft type supersonic wind tunnel to evaluate the effects of the porosity, the porous wall area and the depth of cavity on the pressure distribution around condensation shock wave. It was found that the porosity of 12% which was larger than the case of without nonequilibrium condensation produced the largest reduction of pressure fluctuations in the vicinity of condensation shock wave. The results also showed that wider porous area, deeper cavity for the same porosity of 12% are more favourable "passive" effect than the cases of its opposite. opposite.