• 한국신재생에너지학회:학술대회논문집
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• 2005.11a
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• pp.219-228
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• 2005

본 연구에서는 에너지 및 환경에 대한 문제가 대두되면서 기술 개발의 필요성이 높아지고 있는 풍력발전시스템에 대하여 750kW급 Geared Type 가변속 풍력 발전시스템을 개발하였다. 풍력발전시스템이 급속히 대용량화됨을 고려하여 MW급의 기술 조합이 반영되도록 설계하였으며, 베어링과 같은 국내 인프라가 부족한 구성품을 제외한 모든 구성기기들을 자체 설계/제작하였다. 블레이드는 국내 풍황에 적합하도록 자체 에어포일을 설계하여 개발하였으며, 가변속 제어를 위한 이중 여자 유도발전기 및 제어기와 Down sizing 구현을 위한 유성 및 헬리컬 기어 혼합형 증속기를 개발하여 시동 풍속 3.5m/s, 정지 풍속 25m/s, 정격 풍속은 12.7m/s이며 IEC 61400-1의 Class I 에 준한 750kW급 풍력 발전시스템을 개발하였다.

• Journal of computational fluids engineering
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• v.17 no.2
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• pp.28-34
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• 2012

In this study, the reliability-based design optimization of the airfoil was performed. PARSEC function was used to consider the uncertainty of the aerodynamic shape for the reliability-based shape optimization of airfoils. Among various reliability analysis methods, the moment method was used to compute the probability of failure of the aerodynamic performance. The accuracy of the reliability analysis was compared with other methods and it was found that the moment method predicts the probability of failure accurately. Deterministic and reliability-based optimizations were performed for the shape of the airfoil and it was demonstrated that reliability-based optimum assures the aerodynamic performances under uncertainties of the shape of the airfoil.

• 한국전산유체공학회:학술대회논문집
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• 2010.05a
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• pp.50-54
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• 2010

In this study, reliability-based design optimizations of airfoils were performed. PARSEC function was used to consider the uncertainty of the aerodynamic shape for the reliability-based shape optimization of airfoils. Among aerodynamic performance. The accuracy of the reliability analysis was compared with other method and it was found that the moment method predicts the probability accurately. Deterministic and reliability-based optimizations were performed for shape of the RAE2822 airfoil and it was demonstrated that reliability-based optimizations the aerodynamic performances under uncertainties of the shape of the airfoil.

• 한국전산유체공학회:학술대회논문집
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• 2004.10a
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• pp.165-171
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• 2004

Smart UAV, which adopting tiltrotor aircraft concept, requires long endurance and high speed capability simultaneously These two contradictable flight performances are hard to meet with single wing concept and inevitably require the operation of flap system which should reveal optimal performance for each flight mode. In order to design SUAV flaperon satisfying the performance requirement, various configurations are generated and their aerodynamic performances are analyzed using numerical flow computations around flaps. Considering aerodynamic performance and manufacturing simplicity, a final flap configuration is selected.

• Journal of Advanced Marine Engineering and Technology
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• v.31 no.1
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• pp.58-66
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• 2007

Genetic Algorithms (GA) have some difficulties in practical applications because of too many function evaluations. To overcome these limitations, an approximated modeling method such as Response Surface Modeling(RSM) is coupled to GAs. Original RSM method predicts linear or convex problems well but it is not good for highly nonlinear problems cause of the average effect of the least square method(LSM). So the locally approximated methods. so called as moving least squares method(MLSM) have been used to reduce the error of LSM. In this study, the efficient evolutionary GAs tightly coupled with RSM with MLSM are constructed and then a 2-dimensional inviscid airfoil shape optimization is performed to show its efficiency.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.8
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• pp.26-33
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• 2005

Smart UAV, which adopting tiltrotor aircraft concept, requires vertical take-off and landing, long endurance and high speed capability. These contradictable flight performances are hard to meet unless the operation of flap system which should reveal optimal performance for each flight mode. In order to design SUAV flaperon satisfying the three performance requirements, various configurations are generated and their aerodynamic performances are analyzed using numerical flow computations around flap systems. Considering aerodynamic performance and structural simplicity, a final flap configuration is selected and the performance is validated through the wind tunnel testing for 40% scale model.

• Tribology and Lubricants
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• v.36 no.6
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• pp.332-341
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• 2020

High-speed turbomachinery implements gas foil bearings (GFBs) due to their distinctive advantages, such as high efficiency, lesser part count, and lower weight. This paper provides the test results of the static structural stiffnesses and loss factors of bump-type foil thrust bearings with increasing preload and bearing deflection. The focus of the current work is to experimentally quantify variability in structural stiffnesses and loss factors among the four test thrust bearings with identical design values and material of the bump and top foil geometries using the same (open-source) fabrication method. A simple test setup, using a rigidly mounted non-rotating shaft and thrust disk, measures the bearing bump deflections with increasing static loads on the test bearing. The inner and outer diameters of the test bearings are 41 mm and 81 mm, respectively. The loss factor, best-representing energy dissipation in the test bearings, is estimated from the area inside the local hysteresis loop of the load versus the bearing deflection curve. The measurements show that structural stiffnesses and loss factors of the test bearings significantly rely on applied preloads and bearing deflections. Local structural stiffnesses of the test bearings increase with applied preloads but decrease with bearing deflections. Changes of loss factors are less sensitive to applied preloads and bearing deflections compared to those of structural stiffnesses. Up to 35% variability in static load structural stiffnesses is found between bearings, while up to 30% variability in loss factors is found between bearings.

• 한국신재생에너지학회:학술대회논문집
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• 2011.05a
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• pp.64.2-64.2
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• 2011

해상용(offshore) 부이(bouy)는 선박의 항로를 지시하거나 암초, 침몰선 등 항해상의 위험물을 알리기 위해 사용 되며, 야간을 위해 등화장치를 설치한 것을 등부표라 한다. 등부표는 야간 점등을 위해 자체 전력 생산시스템을 갖추고 있으나, 기존의 태양광을 이용한 전력 시스템은 해상 환경에 따른 제약이 많아 안정적인 운영이 어려우므로 풍력 발전기(wind turbine)를 이용한 하이브리드 전력 생산시스템으로의 전환이 필요한 실정이다. 선행 연구는 수직축(vertical axis) 양력(lift) 및 항력(drag) 조합형 해상용 풍력발전기 개발에 대하여 수행하였으나, 본 논문에서는 풍력발전기의 효율 증대를 위해 날개 길이 및 후면부 절개 비율에 따른 수직축 풍력발전기 특성에 대하여 연구하였다. 풍력발전기의 설치조건은 선행연구와 동일하게 등명구 교체 작업을 원활하게 하기 위하여 설치 공간을 $1m{\times}1m$로 제한하였으며, 등부표의 구조를 고려하여 최상단에 지지 프레임을 별도로 구성 하였다. 풍력발전기의 블레이드는 0.6mm의 알루미늄 박판을 절곡하여 NACA 4418의 외형을 가지도록 제작하였고, 블레이드 설계 시 에어포일의 후면부를 절개하여 양력과 항력을 효과적으로 이용하며 저속과 고속에서 높은 효율을 가지도록 설계하였다. 또한 블레이드 날개 길이와 후면부 절개 비율에 따른 풍력발전기 특성을 실험을 통해 비교하여 기준 해상 풍속에서 블레이드 설계 최적화를 수행하였으며 비교 모델 대비 약32% 발전량이 증가한 설계변수 조합을 구하였다.

• Journal of Aerospace System Engineering
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• v.17 no.6
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• pp.94-99
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• 2023

Recently, renewable energy has been widely used as a source of wind energy and solar energy due to the shortage of fossil fuels and environmental problems. Against this backdrop, wind energy is emerging as an important energy source, and the wind power market is showing rapid growth worldwide. In this study, a high-efficiency wind turbine blade was designed with an integrated blade aerodynamic design for prior research on separate blades. The blade airfoil was applied as NACA 4418, and it was verified by comparing it with the analysis results to evaluate the newly designed blade.

• Proceeding of EDISON Challenge
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• 2014.03a
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• pp.579-584
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• 2014

고속 열차의 속도가 점점 빨라짐에 따라 고속 열차 주행 시 발생하는 여러 공력적인 문제가 대두되고 있다. 그 중 고속 열차와 전력선을 이어주는 판토그래프에서의 소음 발생과 압상력 불안정 문제가 중요시 되어왔고 이에 대한 여러 선행연구가 진행되고 있다. 지금까지의 선행 연구는 원형, 사각형, 에어포일과 같이 기본적인 형상을 이용한 판토그래프 팬헤드의 최적 단면 형상을 찾는 데에 초점을 맞추고 있다. 본 연구는 이러한 주류의 접근 방식에서 벗어나 팬헤드에 구멍을 추가하여 그 효과를 보는 다양한 시도를 해보았고 구멍이 소음 발생과 압상력 불안정에 미치는 영향에 대하여 연구하였다.