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주완돈(Wandon Joo),이보성(Bo-sung Lee),이관중(Kwanjung Yee),이동호(Dong-Ho Lee) 한국항공우주학회 2005 韓國航空宇宙學會誌 Vol.33 No.1
본 연구에서는 진동 운동하는 익형의 동적실속 특성을 향상시키기 위하여, 고정 앞전 Droop과 Gurney 플랩의 크기와 위치에 대한 최적설계를 수행하였다. 고정 앞전 Droop이 모멘트 특성의 개선에 효율적이나 양력특성의 저하를 유발 할 수 있다. 반면에 Gurney 플랩은 양력특성의 향상을 가져오지만, 모멘트특성을 악화시키는 특성이 있다. 고정앞전 Droop의 설계변수는 상호 보완적인 특성을 갖는 위치와 각도를 설정하였으며, Gurney 플랩은 그 길이를 설계변수로 설정하였다. 또한, 동적실속과 같이 비선형성이 강한 문제의 설계를 위해서 고차 다항식의 반응면 기법과 민감도 기반의 최적설계 기법을 사용하였다. 최적화는 양력과 모멘트 특성이 동시에 개선되도록 수행 하였다. 설계 결과 동적실속의 양력, 모멘트 및 항력특성의 향상을 가져올 수 있었으며, 가변 앞전 Droop과 Gurney 플랩을 결합한 능동제어장치에 버금가는 동적실속 제어 효과를 갖을 수 있음을 확인하였다. In order to improve dynamic stall characteristics of an oscillating airfoil, optimal design has been performed for fixed nose droop and Gurney flap. Fixed nose droop is known to be very effective to improve pitching moment characteristics but may cause degeneration of aerodynamic lift at the same time. On the other hand, Gurney flap has the opposite characteristics. For fixed nose droop, location and angle are chosen as design variables, while length is defined as design variable for Gurney flap. Higher order response surface methodology and sensitivity based optimal design method are employed to handle highly nonlinear problem such as dynamic stall. Optimal design has been performed so that lift and pitching moment are simultaneously improved. The design results show that aerodynamic characteristics can be remarkably improved through present design approach and the present passive control method is as good as active control method which combines variable nose droop and Gurney flap.
주완돈(Wandon Joo),이기학(Ki-Hak Lee),이관중(Kwanjung Yee),이동호(Dong-Ho Lee) 한국항공우주학회 2006 韓國航空宇宙學會誌 Vol.34 No.1
본 연구에서는 완전 내재적 기법을 이용한 2계 자유도 모델에 대한 플러터 해석을 수행하였다. 유동해석을 위하여 2차원 Navier-Stokes 지배방정식을 ε-SST 난류모델과 DP-SGS 병렬화 기법을 이용해 구성하였다. 구조해석을 위하여 피치와 플런지의 2계 자유도를 갖는 모델을 구성하였으며 시간영역에서의 해석을 위하여 유동해석과 마찬가지로 이중 시간 전진 기법을 이용하였다. 가상 시간 전진에서 유체-구조 결합을 통해서 강성결합을 구현하였으며 이를 천음속 플러터 예측에 적용하였다. 플러터 해석의 전형적인 응답인 감쇠응답, 중립응답, 발산응답 및 limit cycle oscillation (LCO) 등을 계산하였으며, 더불어 플러터 속도 경계곡선을 작성하였다. 천음속 플러터 해석은 난류모델 뿐만 아니라 유체-구조 결합 방법에 따라 다른 특성을 보임을 확인하였다. In the present study, a strongly coupled analysis code is developed for transonic flutter analysis. For aerodynamic analysis, two dimensional Reynolds-Averaged Navier-Stokes equation was used for governing equation, and ε-SST for turbulence model, DP-SGS(Data Parallel Symmetric Gauss Seidel) Algorithm for parallelization algorithm. 2 degree-of-freedom pitch and plunge model was used for structural analysis. To obtain flutter response in the time domain, dual time stepping method was applied to both flow and structure solver. Strongly coupled method was implemented by successive iteration of fluid-structure interaction in pseudo time step. Computed results show flutter speed boundaries and limit cycle oscillation phenomena in addition to typical flutter responses - damped, divergent and neutral responses. It is also found that the accuracy of transonic flutter analysis is strongly dependent on the methodology of fluid-structure interaction as well as on the choice of turbulence model.
주완돈(Joo, Wan-Don),박정훈(Park, Jeung-Hun),최준혁(Choi, June-Hyug),임채욱(Lim, Chae-Wook),박종포(Park, Jong-Po) 한국신재생에너지학회 2007 한국신재생에너지학회 학술대회논문집 Vol.2007 No.06
This paper presents the general results of the conceptual design of a 3MW class offshore wind turbine named WinDS 3000 under development. In WinDS 3000, an integrated drive train design, three stage gearbox and permanent magnet generator (PMG) with fully rated converters have been introduced. A pitch regulated variable speed power control with individual pitch control has been adopted to regulate rotor torque while generator reaction torque can be adjusted almost instantaneously by the associated power electronics. Through the introduction of WinDS 3000, it is expected that helpful to understanding of the development status of 3MW offshore wind turbine.
주완돈(Joo, Wan-Don),이정훈(Lee, Jeong-Hoon),김정일(Kim, Jeong-Il),정석용(Jeong, Seok-Yong),신영호(Shin, Young-Ho),박종포(Park, Jong-Po) 한국신재생에너지학회 2009 한국신재생에너지학회 학술대회논문집 Vol.2009 No.06
This paper introduces the design concepts and characteristics of WinDS3000^{TM} which is a trade mark of Doosan's 3MW offshore/onshore wind turbine. WinDS3000^{TM} has been designed in consideration of high RAMS (Reliability, Availability, Maintainability and Serviceability) and cost effectiveness for the TC Ia condition in GL guideline. An integrated drive train design with an innovative three-stage gearbox has been introduced to minimize nacelle weight of the wind turbine and to enhance a high reliability for transmission. A permanent magnet generator with full converter system has been introduced to get higher efficiency in part load operation, and grid friendliness use of 50 Hz and 60 Hz grid. A pitch regulated variable speed power control with individual pitch system has been introduced to regulate rotor torque while generator reaction torque can be adjusted almost instantaneously by the associated power electronics. An individual pitch control system has been introduced to reduce fatigue loads of blade and system. The wind turbine has been also equipped with condition monitoring and diagnostic systems in order to meet maintainability requirements. And internal maintenance crane in nacelle has been developed. As a result, the maintenance cost was dramatically reduced and maintenance convenience also enhanced in offshore condition.
Design of Substructure for 3MW Offshore Wind Turbine Demonstrator Project
변철진(Byun, Chuljin),주완돈(Joo, Wandon),정석용(Jeong, Seokyong),박종포(Park, Jongpo) 한국신재생에너지학회 2010 한국신재생에너지학회 학술대회논문집 Vol.2010 No.11
The 3MW OWEC demonstrator project in Korea will be the first offshore wind project with Korean turbine, Doosan WinDS3000, and constructed on the north-eastern sea of Jeju Island as the water depth of 15m. Integrated loadings of wind and wave are investigated to describe a design loads for both extreme and fatigue conditions using GH-Bladed. A dynamic behaviour of substructure strongly affects a substructure loadings. The jacket structure is designed in accordance with DNV guidelines. The results of this paper show overall design process of offshore substructure as a complex jacket concept and this design process can be implemented on a design of monopile and tripod structures.
김경택(Kyung-Taek Kim),주완돈(Wan-Don Joo),이상일(Sang-Il Lee),이정훈(Jeong-Hoon Lee) 한국신재생에너지학회 2015 신재생에너지 Vol.11 No.2
This paper deals with a numerical investigation on aeroelastic stability characteristics of a 3-MW wind turbine blade. Utilizing a commercial software, a linear aeroelastic model for the blade stability analysis is constructed based on both the blade element momentum (BEM) theory and formulations for flexible multi-body system dynamics. Conventional linear stability analysis, which is suitable for the early stages of blade design, is then carried out by calculating complex eigenvalues of the analysis model taking normal and abnormal operating conditions into account. The results demonstrate that the blade maintains the stability during standard normal operation, and also emphasize the necessity of considering potential abnormal operating events, such as those caused by control system faults, for blade aeroelastic stability analysis.
배의성(Eui-Sung Bae),주완돈(Wan-Don Joo),이동호(Dong-Ho Lee) 한국항공우주학회 2006 韓國航空宇宙學會誌 Vol.34 No.1
본 연구에서는 Gurney 플랩이 달린 NACA 0012 익형에 대한 플러터 해석을 시간 영역에서 수행하였다. 2차원 비정상 압축성 Navier-Stokes 방정식과 Lagrange 방정식으로부터 유도한 2계 자유도 plunge & pitch 모델을 지배방정식으로 하여 연성 결합 기법을 통해 플러터 해석을 수행하였다. 계산 결과 Gurney 플랩을 장착할 경우 NACA 0012에 비해 플러터가 발생하는 속도가 낮아졌고, 마하수가 0.85보다 작은 영역에서는 Gurney 플랩의 플러터 경계 곡선은 안전 여유를 상회하는 영역에 위치하였다. 그러나, 마하수가 0.85에서 0.9사이일 경우에는 안전 여유에 근접하게 되므로 이러한 운용 영역에서는 Gurney 플랩의 사용에 주의를 요한다. Flutter analysis of NACA 0012 with Gurney flap was conducted in time domain. Flutter analysis was performed with a conjunction of two governing equations; one is 2D Navier-Stokes equation and, the other is Lagrange equation of two dimensional plunge & pitch model. Both governing equations were coupled by loose-coupling method. From the computed results, the effect of Gurney flap was concluded to move the flutter boundary of NACA 0012 downward, which means flutter occurs at lower speed than that of NACA 0012. Although flutter boundary of gurney flap was above the safety margin when mach number was lower than 0.85, there might be a possibility of crossing the safety margin when mach number was between 0.85 and 0.9. For safety, the effect of gurney flap needs to be investigated carefully before using it.