• Title/Summary/Keyword: CFD/CSD coupled analysis

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Performance Prediction a 10MW-Class Wind Turbine Blade Considering Aeroelastic Deformation Effect (공탄성 변형효과를 고려한 10MW급 풍력발전기 블레이드의 성능해석)

  • Kim, Dong-Hyun;Kim, Yo-Han;Ryu, Gyeong-Joong;Kim, Dong-Hwan;Kim, Su-Hyun
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2011.04a
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    • pp.657-662
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    • 2011
  • In this study, aeroelastic performance analyses have been conducted for a 10MW class wind turbine blade model Advanced computational analysis system based on computational fluid dynamics (CFD) and computational structural dynamics (CSD) has been developed in order to investigate detailed dynamic responsed of wind turbine blade Reynolds-averaged Navier-Stokes (RANS) equations with k-${\omega}$ SST turbulence model are solved for unsteady flow problems of the rotating turbine blade model. A fully implicit time marching scheme based on the Newmark direct integration method is used for computing the coupled aeroelastic governing equations of the 3D turbine blade for fluid-structure interaction (FSI) problems.

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Transonic Flutter Characteristics of the AGARD 445.6 Wing Considering DES Turbulent Model and Different Angle-of-Attacks (DES 난류모델 및 받음각 변화를 고려한 AGARD 445.6 날개의 천음속 플러터 응답 특성)

  • Kim, Yo-Han;Kim, Dong-Hyun
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.18 no.1
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    • pp.27-32
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    • 2010
  • In this study, transonic flutter response characteristics have been studied for the AGARD 445.6 wing considering various turbulent models and several angle of attacks. The developed fluid-structure coupled analysis system is applied for flutter computations combining computational structural dynamics(CSD), finite element method(FEM) and computational fluid dynamics(CFD) in the time domain. The flutter boundaries of AGARD 445.6 wing are verified using developed computational system. For the nonlinear unsteady aerodynamics in high transonic flow region, DES turbulent model using the structured grid system have been applied for the wing model. Characteristics of flutter responses have been investigated for various angle of attack conditions. Also, it is typically shown that the current computation approach can yield realistic and practical results for aircraft design and test engineers.

Nonlinear Characteristics of Low-speed Flow Induced Vibration for the Safety Design of Micro Air Vehicle

  • Chang, Tae-Jin;Kim, Dong-Hyun;Lee, In
    • Transactions of the Korean Society for Noise and Vibration Engineering
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    • v.12 no.11
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    • pp.873-881
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    • 2002
  • The fluid induced vibration (FIV) phenomena of an equivalent airfoil system of MAV have been investigated in low Reynolds number flow region. Unsteady flows with viscosity are computed using two-dimensional incompressible Navier-Stokes equations. The present fluid/structure interaction analysis is based on one of the most accurate computational approach with computational fluid dynamics (CFD) and computational structural dynamics (CSD) techniques. The highly nonlinear fluid/structure interaction phenomena due to severe flow separations have been analyzed for the low Reynolds region that has a dominancy of flow viscosity. The effects of Reynolds number and initial angle of attack on the fluid/structure coupled vibration instability are shown and the qualitative trend of FIV phenomenon is investigated.

Aeroelastic Response Analysis of 3D Wind Turbine Blade Considering Rotating and Flow Separation Effects (회전과 유동박리효과를 고려한 3차원 풍력발전 터빈 블레이드의 공탄성 응답 해석)

  • Kim, Dong-Hyun;Kim, Yo-Han;Kim, Dong-Man;Kim, Yu-Sung;Hwang, Mi-Hyun
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2009.04a
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    • pp.68-75
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    • 2009
  • In this study, aeroelastic response analyses have been conducted for a 3D wind turbine blade model. Advanced computational analysis system based on computational fluid dynamics(CFD) and computational structural dynamics(CSD) has been developed in order to investigate detailed dynamic responsed of wind turbine blade. Vibration analyses of rotating wind-turbine blade have been conducted using the general nonlinear finite element program, SAMCEF (Ver.6.3). Reynolds-averaged Navier-Stokes (RANS)equations with spalart-allmaras turbulence model are solved for unsteady flow problems of the rotating turbine blade model. A fully implicit time marching scheme based on the Newmark direct integration method is used for computing the coupled aeroelastic governing equations of the 3D turbine blade for fluid-structure interaction (FSI) problems. Detailed dynamic responses and instantaneous Mach contour on the blade surfaces considering flow-separation effects are presented to show the multi-physical phenomenon of the rotating wind-turbine blade model.

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Virtual Flutter Plight Test of a Full Configuration Aircraft with Pylon/External Stores

  • Kim, Dong-Hyun;Kwon, Hyuk-Jun;Lee, In;Paek, Seung-Kil
    • International Journal of Aeronautical and Space Sciences
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    • v.4 no.1
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    • pp.34-44
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    • 2003
  • An advanced aeroelastic analysis using a computational structural dynamics (CSD), finite element method (FEM) and computational fluid dynamics (CFD) is presented in this Paper. A general aeroelastic analysis system is originally developed and applied to realistic design problems in the transonic flow region, where strong shock wave interactions exist. The present computational approach is based on the modal-based coupled nonlinear analysis with the matched-point concept and adopts the high-speed parallel processing technique on the low-cost network based PC-clustered machines. It can give very accurate and useful engineering data on the structural dynamic design of advanced flight vehicles. For the nonlinear unsteady aerodynamics in high transonic flow region, Euler equations using the unstructured grid system have been applied to easily consider complex configurations. It is typically shown that the advanced numerical approach can give very realistic and practical results for design engineers and safe flight tests. One can find that the present study conducts a virtual flutter flight test which are usually very dangerous in reality.

Flow-Induced Vibration (FIV) Analysis of a 3D Axial Compressor Blade (3차원 축류압축기 블레이드의 유체유발진동 해석)

  • Kim, Dong-Hyun;Kim, Yu-Sung;Yang, Guo Wei;Jung, Kyu-Kang;Kim, Kyung-Hee;Min, Dae-Gee
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2009.04a
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    • pp.652-653
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    • 2009
  • In this study, flow-induced vibration (FIV) analyses have been conducted for a 3D compressor blade model. Advanced computational analysis system based on computational fluid dynamics (CFD) and computational structural dynamics (CSD) has been developed in order to investigate detailed dynamic responses of designed compressor blades. Fluid domains are modeled using the computational grid system with local grid deforming and remeshing techniques. Reynolds-averaged Navier-Stokes equations with $\kappa-\varepsilon$ turbulence model are solved for unsteady flow problems of the rotating compressor model. A fully implicit time marching scheme based on the Newmark direct integration method is used for computing the coupled aeroelastic governing equations of the 3D compressor blade for fluid-structure interaction (FSI) problems. Detailed dynamic responses and instantaneous pressure contours on the blade surfaces considering flow-separation effects are presented to show the multi-physical phenomenon of the rotating compressor blade.

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Flow-induced Vibration(FIV) Analysis of a 3D Axial Compressor Blade (3차원 축류압축기 블레이드의 유체유발진동 해석)

  • Kim, Dong-Hyun;Kim, Yu-Sung;Yang, Guo Wei;Jung, Kyu-Kang;Kim, Kyung-Hee;Min, Dae-Gee
    • Transactions of the Korean Society for Noise and Vibration Engineering
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    • v.19 no.6
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    • pp.551-559
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    • 2009
  • In this study, flow-induced vibration(FIV) analyses have been conducted for a 3D compressor blade model. Advanced computational analysis system based on computational fluid dynamics(CFD) and computational structural dynamics(CSD) has been developed in order to investigate detailed dynamic responses of designed compressor blades. Fluid domains are modeled using the computational grid system with local grid deforming and remeshing techniques. Reynolds-averaged Navier-Stokes equations with $\kappa-\epsilon$ turbulence model are solved for unsteady flow problems of the rotating compressor model. A fully implicit time marching scheme based on the Newmark direct integration method is used for computing the coupled aeroelastic governing equations of the 3D compressor blade for fluid-structure interaction(FSI) problems. Detailed dynamic responses and instantaneous pressure contours on the blade surfaces considering flow-separation effects are presented to show the multi-physical phenomenon of the rotating compressor blade.

Aerodynamic and Structural Design of 6kW Class Vertical-Axis Wind Turbine (공탄성 변형효과를 고려한 5MW급 풍력발전 블레이드의 피치각에 따른 성능해석)

  • Kim, Yo-Han;Kim, Dong-Hyun;Hwang, Mi-Hyun;Kim, Kyung-Hee;Hwang, Byung-Sun;Hong, Un-Sung
    • The KSFM Journal of Fluid Machinery
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    • v.14 no.3
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    • pp.39-44
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    • 2011
  • In this study, performance analyses have been conducted for a 5MW class wind turbine blade model. Advanced computational analysis system based on computational fluid dynamics(CFD) and computational structural dynamics(CSD) has been developed in order to investigate detailed dynamic responsed of wind turbine blade. Reynolds-averaged Navier-Stokes (RANS) equations with K-${\epsilon}$ turbulence model are solved for unsteady flow problems of the rotating turbine blade model. A fully implicit time marching scheme based on the Newmark direct integration method is used for computing the coupled aeroelastic governing equations of the 3D turbine blade for fluid-structure interaction (FSI) problems. Predicted aerodynamic performance considering structural deformation effect of the blade show different results compared to the case of rigid blade model.

Transonic Flutter Characteristics of Supercritical Airfoils Considering Shockwave and Flow Separation Effects (충격파 및 유동박리 효과를 고려한 초임계 에어포일의 천음속 플러터 특성)

  • Kim, Dong-Hyun;Kim, Yu-Sung;Kim, Yo-Han;Kim, Seok-Soo
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2008.11a
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    • pp.167-174
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    • 2008
  • In this study, flutter analyses for supercritical airfoil have been conducted in transonic region. Advanced computational analysis system based on computational fluid dynamics (CFD) and computational structural dynamics (CSD) has been developed in order to investigate detailed static and dynamic responses of supercritical airfoil. Reynolds-averaged Navier-Stokes equations with Spalart-Allmaras (S-A) and SST ${\kappa}-{\omega}$ turbulence models are solved for unsteady flow problems. A fully implicit time marching scheme based on the Newmark direct integration method is used for computing the coupled aeroelastic governing equations of cascades for fluid-structure interaction (FSI) problems. Also, flow-induced vibration (FIV) analyses for various supercritical airfoil models have been conducted. Detailed flutter responses for supercritical are presented to show the physical performance and vibration characteristics in various angle of attack.

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Transonic Flutter Characteristics of Supercritical Airfoils Considering Shockwave and Flow Separation Effects (충격파 및 유동박리 효과를 고려한 초임계 에어포일의 천음속 플러터 특성)

  • Lin, Han;Kim, Dong-Hyun;Kim, Yu-Sung;Kim, Yo-Han;Kim, Seok-Soo
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.17 no.2
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    • pp.8-17
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    • 2009
  • In this study, flutter analyses for supercritical airfoil have been conducted in transonic region. Advanced computational analysis system based on computational fluid dynamics (CFD) and computational structural dynamics (CSD) has been developed in order to investigate detailed static and dynamic responses of supercritical airfoil. Reynolds-averaged Navier-Stokes equations with Spalart-Allmaras (S-A) and SST ${\kappa}-{\omega}$ turbulence models are solved for unsteady flow problems. A fully implicit time marching scheme based on the Newmark direct integration method is used for computing the coupled aeroelastic governing equations of cascades for fluid-structure interaction (FSI) problems. Also, flow-induced vibration (FIV) analyses for various supercritical airfoil models have been conducted. Detailed flutter responses for supercritical are presented to show the physical performance and vibration characteristics in various angle of attack.

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