• Transactions of the Korean Society of Mechanical Engineers A
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• v.35 no.12
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• pp.1627-1633
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• 2011

Injection molds are generally fabricated by assembling a number of plates in which the core and cavity components are assembled. This assembled structure has a number of contact interfaces where the heat transfer characteristics are affected by thermal contact resistance. In previous studies, numerical approaches were investigated to predict the effect of thermal contact resistance on the temperature distribution of injection molds. In this study, thermal-fluid coupled numerical analyses are performed to take into account the thermal contact effect on the numerical evaluation of the mold filling characteristics. Comparisons with experimental results show that the proposed coupled analysis provides more reliable results than the conventional analyses in predicting the mold filling characteristics by taking into account the effect of thermal contact resistance inside the injection mold assembly.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.1
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• pp.72-78
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• 2008

In this study, advanced (fluid-structure interaction (FSI)) analysis system has been developed in order to predict turbine cascade performance with blade deformation effect due to aerodynamic loads. Intereference effects due to the relative movement of the rotor cascade with respect to the stator cascade are also considered. Reynolds-averaged Navier-Stokes equations with one equation Spalart-Allmaras and two-equation k-ω SST turbulence models are solved to accurately predict fluid dynamic loads considering flow separation effects. A fully implicit time marching scheme based on the (coupled Newmark time-integration method) with high artificial damping is efficiently used to compute the complex fluid-structure interaction problem. Predicted aerodynamic performance considering structural deformation effect of the blade shows somewhat different results compared to the case of rigid blade model. Cascade performance evaluations for different elastic axis positions are importantly presented and its aeroelastic effects are investigated.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.1
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• pp.1-9
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• 2017

In this paper, we present and verify an aerodynamic reduced-order model (ROM) based on a quasi-steady flow method to reduce the computational cost of supersonic aeroelastic analysis. For supersonic flows, especially when the characteristic time scale of the flow is small compared to that of the structural motion, the unsteadiness of flow can be negligible, and quasi-steady solutions can be used instead of the unsteady solutions for the aeroelastic analysis. Kriging method is used to build the ROM of the aerodynamics. The surface solutions from the ROM are used as the boundary conditions for the structural analysis at each time-step. The ROM is validated against the unsteady solutions.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.18 no.9
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• pp.94-99
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• 2019

To evaluate the stability of a pneumatic conveyor system, a flow analysis and structural analysis were performed using the FSI technique. Prototypes were fabricated and verified. As a result of the flow analysis, the maximum pressure applied to the device was calculated to be 0.55 MPa. The structural analysis determined that the maximum stress was 131 MPa and the yield strength of the structure was less than 205 MPa. The safety of the system was confirmed by the fact that no deformation occurred during the manufacturing and operation of the prototype.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.36 no.12
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• pp.1653-1661
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• 2012

In this study, the pressure drop changes and structural characteristics of a SMART rod bundle under the effect of a coolant were investigated. The turbulence model of the BSL Reynolds stress model was used to model the coolant flow, and a fluid solid interaction simulation was conducted. First, fuel rod vibration analysis was performed to confirm the natural frequency of the fuel rod, which was supported by spacer grid assemblies, and this was compared with experimental results. From the experimental results, the natural frequency was found to be 48 Hz, and the error compared with the simulation results was 2%. The pressure drop at the rod bundle was calculated and compared with the experimental data; it showed an error of 8%, demonstrating the simulation accuracy. In the flow analysis, the flow velocity and secondary flow at different domains were calculated, and vortex generation was also observed. Finally, through the fluid solid interaction analysis, the fuel rod displacements caused by flow-induced vibrations were calculated. Then, calculated displacement PSD at maximum displacement happed point.

• Proceedings of the Korea Water Resources Association Conference
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• 2017.05a
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• pp.311-316
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• 2017

기후변화는 물 관리 측면에서 많은 변화를 일으키는 것으로 보고되고 있다. 주로 강우의 패턴을 변화시키며, 가용수자원의 지역적 편중을 심화시킨다. 기후변화에 적응하며 안정적이고 균등한 용수확보를 위해서는 홍수와 가뭄을 고려한 연속적인 물 순환 해석기술이 필요하다. 강우유출분석은 강우사상에 대한 수문순환과정을 통해 유출량을 산출하는 것으로, 주로 직접유출과 중간유출이 이에 해당된다. 강우발생 이후 무강우기간에 대해서는 기저시간 이후에 발생되는 유출량의 정량적 산출이 필요하다. 기저유출은 강우 발생 시점에 급격히 발생하기보다는 선행강우에 따른 유역 내 지하수위 분포와 대수층의 특성, 하천수위에 따라 다양한 패턴으로 나타나기 때문에 지하수대의 수리학적 성분들을 반영할 수 있어야 한다. 이를 위해서는 강우유출모의 시 지표유출량 산정과 지하수유동해석을 통한 기저유출량 산정이 동시에 이루어져야 한다. 최근 국내외에서는 다양한 형태의 수문모형과 MODFLOW를 연계한 장기유출분석에 대한 연구가 활발하게 진행되고 있다. 본 연구에서 활용한 K-DRUM(K-water Distribution Runoff Model)은 K-water에서 자체 개발한 물리적 기반의 분포형 강우유출모형으로 강우유출, 유사, 기초수질항목에 대한 3차원 분석이 가능하다. 본 모형의 A층(표층)은 지표유출을 고려한 운동파법이 적용되었고, B층과 C층(중간층), D층(지하수층)은 선형저류법이 적용되었다. MODFLOW(A Modular Three-Dimensional Finite-Difference Ground Water Flow Model)는 1980년대 USGS(United State Geolog ical Survey)에서 개발된 가장 범용적으로 사용되는 지하수유동모형이며, 모듈화 된 구조를 갖고 있어 다양한 패키지 중 필요로 하는 기능을 독립적으로 모의할 수 있는 장점이 있다. 본 연구에서는 향후 기후변화에 따른 강우의 불확실성에 대비한 유역의 장기 물순환 해석을 위해 강우유출모형인 K-DRUM과 지하수유동모형인 MODFLOW를 연계하고자한다. 연계방법은 K-DRUM에서 계산된 D층으로 침루되는 양을 MODFLOW의 함양량으로 적용하고, MODFLOW에서 산출된 기저유량을 K-DRUM의 하천유출에 적용하는 것이다. 본 연구의 성과를 갈수기 유출해석에 적용하면 정확성을 크게 향상시킬 수 있을 것으로 판단된다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.8 no.5
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• pp.984-990
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• 2007

The objective of this study is the estimation of the $O_2$ concentration range, the thermal behavior by high temperature exhaust gas and durability of exhaust manifold by the coupling analysis of CFD and structure analysis. This estimation results is used the guideline to the optimum design of exhaust manifold.

• 기계와재료
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• v.23 no.3
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• pp.16-29
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• 2011

결정 합금 대비 비정질 합금은 높은 경도를 갖기 때문에 마모 저항성도 좋고 내부 식성 등 환경에 대한 저항성도 월등하며, 또한 과냉된 액상 상태까지 재가열하게 되면 낮은 점성도를 갖게 되므로 복잡한 3차원적인 형상을 가지는 부품을 환경에 대한 저항성, 피로 저항성, 강도 및 경도 등을 모두 고려하여 높은 정밀도를 가지고 제조하는 것이 가능하므로 우수한 물성을 갖는 구조 및 기능성 재료로의 다양한 응용이 타진되고 있다. 이러한 비정질 합금의 변형 거동에 대한 연구는 대부분 유리 천이 온도 이하에서의 전단 및 파단에 이르는 이른바 불균일 변형(Inhomogeneous Deformation) 거동에 대한 이해를 위한 실험 및 해석적 연구에 집중되어 왔다. 반면 상업화의 기반이 되는 고상 기반 2차 정형 성형은 과냉 액상 영역에서의 구조 완화 및 결정화롤 대표되는 미세 구조 제어 균일 변형(Homogeneous Deformation)에 대한 이해 없이는 불가능하므로, 이러한 관점에서 비정질 합금 특유의 점성 유동 특성을 이용한 균일 변형 응용 예시 및 미세구조 변화 연계 해석 기술의 현황을 소개하고자 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.12
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• pp.1139-1145
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• 2008

numerical study on the coupled fluid-structure for a rotor blade in hover was conducted. Computational fluid dynamics code with enhanced wake-capturing capability is coupled with a simple structural dynamics code based on Euler-Bernoulli's beam equation. The numerical results show a reasonable blade structural deformation and aerodynamic characteristics.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.7
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• pp.489-498
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• 2019

The airloads and structural loads of Light Civil Helicopter (LCH) rotor are investigated using a loose CFD/CSD coupling. The structural dynamics model for LCH 5-bladed rotor cwith elastomeric bearing and inter-bladed damper is constructed using CAMRAD-II. Either isolated rotor or rotor-fuselage model is used to identify the effect of the fuselage on the aeromechanics behavior at a cruise speed of 0.28. The fuselage effect is shown to be marginal on the aeromechanics predictions of LCH rotor, though the effect can be non-negligible for the tail structure due to the prevailing root vortices strengthened by the fuselage upwash. A lifting-line based comprehensive analysis is also conducted to verify the CFD/CSD coupled analysis. The comparison study shows that the comprehensive analysis predictions are generally in good agreements with CFD/CSD coupled results. However, the predicted comprehensive analysis results underestimate peak-to-peak values of blade section airloads and elastic motions due to the limitation of unsteady aerodynamic predictions. Particularly, significant discrepancies appear in the structural loads with apparent phase differences.