• Tribology and Lubricants
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• 제14권3호
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• pp.39-45
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• 1998

Reynolds equation, which describes behavior of fluid film in journal bearings, basically satisfies mass conservation. But, boundary conditions usually used with this equation, e.g. half Sommerfeld or Reynolds boundary conditions, cannot fulfill this natural law of conservation. In the case of connecting rod bearing, where applied load is dynamic and its magnitude is relatively large, such unrealistic boundary conditions have serious influence on calculation results, especially on lubricant flow rate or power disspation which are important parameters in thermal analysis. In this paper, mass-conserving boundary condition was applied in the finite element analysis of connecting rod bearings. Lubricant flow rate and power dissipation rate were calculated together with journal center locus, minimum film thickness and maxmium film pressure. These computation results were compared with those of the case of Reynolds boundary condition. Balance between inlet and outlet flow rate was well achieved in the case of mass-conserving boundary condition.

• 한국가시화정보학회:학술대회논문집
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• 한국가시화정보학회 2004년도 추계학술대회 논문집
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• pp.26-29
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• 2004

In this paper, we report the numerical and experimental solutions of the dynamic characteristics of a vortex ring in a circular cylinder generated by impinging a fluid blob from a hole on the bottom wall of the cylinder. We managed to visualize successfully the flow pattern shown on the vertical and horizontal planes by using a specially designed optical apparatus. Results of three-dimensional computation for the flow are shown to be in a satisfactory agreement with the experimental ones. We also report the experimental results which show a breaking of the axi-symmetric pattern after the vortex touches the free surface.

• 한국항공우주학회지
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• 제37권10호
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• pp.984-991
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• 2009

본 연구에서는 충격파 및 유동박리효과를 고려하여 항공기 동체-날개 형상(DLR-F4)에 대한 천음속 공탄성 응답해석을 수행하였다. 시간 영역에서 전산유체역학, 유한요소모델 및 전산구조동역학 기법을 활용한 유체-구조 연계시스템을 적용하여 공탄성 해석을 수행 하였으며, 이를 이용하여 비행체의 설계에 정확하고 유용한 결과를 제시할 수 있다. 천음속 영역에서 항공기 동체-날개 형상에 대해 비선형 비정상 공력해석을 수행하기 위하여 6면체 구조 격자를 생성하였고, Navier-Stokes 방정식을 적용하였다. 항공기 동체-날개 형상의 정적 및 동적 공탄성 응답 특성을 파악하였고, 항공기 설계 및 시험 연구자에게 실제적이고 유용한 결과를 제시할 수 있다.

• 대한조선학회논문집
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• 제44권1호
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• pp.8-15
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• 2007

In this paper, numerical calculations are performed to analyze the unsteady flow of NACA airfoil sections. In order to ease the flow computation for the fluid region changing in time, improve the quality of solution and simplify the grid generation for the oscillating foil flow, the computational method adopts a moving and deforming mesh with the multi-block grid topology. The multi-block, structured-unstructured hybrid grid is generated using the commercial meshing software Gridgen V15. The MDM (Moving & Deforming Mesh) and the UDF (User Define function) function of FLUENT 6 are adopted for computing turbulent flows of the foil in pitching motion. Computed unsteady lift and drag forces are compared with experimental data. in general, the characteristics of unsteady lift and drag of the experiments are reproduced well in the numerical analysis.

• 한국윤활학회:학술대회논문집
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• 한국윤활학회 2004년도 학술대회지
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• pp.99-107
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• 2004

Lubrication characteristics between a cylinder block and a valve plate for high speed bent-axis type hydraulic pump play an important role in volumetric efficiency and durability of pump. In this paper, a finite element method is presented for the computation of the pressure distribution between a cylinder block and a valve plate for high speed bent-axis type hydraulic pump. Also, a Runge-Kutta method is applied to simulate the cylinder block dynamics of three-degrees of freedom motion. From the results of computation, we can draw two major conclusions. One is related to the fluid film characteristics between a cylinder block and a valve plate and the other is related to the average leakage that is determined by the pressure gradient and the clearance near the discharge port. The numerical results of cylinder block dynamics were compared with the experimental results using eddy-current type gap sensors those are fixed at a pump housing.

• Coupled systems mechanics
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• 제7권2호
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• pp.233-254
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• 2018

In order to reduce the dependency on fossil fuels, a policy to increase the production capacity of wind turbine is set up. This can be achieved with increasing the dimensions of offshore wind turbine blades. However, this increase in size implies serious problems of stability and durability. Considering the cost of large turbines and financial consequences of their premature failure, it is imperative to carry out numerical simulations over long periods. Here, an energy-conserving time-stepping scheme is proposed in order to ensure the satisfying computation of long-term response. The proposed scheme is implemented for three-dimensional solid based on Biot strain measures, which is used for modeling flexible blades. The simulations are performed at full spatial scale. For reliable design process, the wind loads should be represented as realistically as possible, including the fluid-structure interaction (FSI) dynamic effects on wind turbine blades. However, full-scale 3D FSI simulations for long-term wind loading remain of prohibitive computation cost. Thus, the model to quantify the wind loads proposed here is a simple, but not too simple to be representative for preliminary design studies.

• 한국음향학회지
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• 제39권4호
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• pp.364-370
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• 2020

우주 발사체의 초음속 플룸으로부터 발생하는 고강도 소음은 발사체에 음향하중으로 작용하여 전장품이나 탑재 위성의 오작동 및 고장을 유발한다. 음향하중을 발생시키는 로켓/제트소음의 예측은 초음속 난류 유동(소음원) 예측을 위한 전산유체해석과 음향(소음 전파) 해석이 결합된 모델이 주로 사용된다. 이때, 유동해석 시 계산영역 경계면에서 발생하는 반사파 아티팩트를 제거하기 위해 경계조건 외에 추가적으로 흡수층(sponge layer)과 같은 모델링이 적용된다. 하지만, 해석 대상에 따라 흡수층의 파라미터 최적화 연구가 선행되어야 하고 더 큰 계산 영역을 필요로 하기 때문에, 이는 해석시간 증가의 주요 요인이 된다. 이에 본 논문에서는 계산효율을 증대시키기 위해 흡수층 대신 유동해석 결과에 존재하는 반사파 아티팩트를 두 개의 마이크로폰 기법을 기반으로 하여 제거하는 방법을 처음으로 제안하고, 이를 실제 소형 초음속 제트소음 해석 결과에 적용하였다.

• 유기물자원화
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• 제19권1호
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• pp.93-101
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• 2011

본 연구는 소각 시스템에 적용되는 반건식 반응기의 모델링 연구를 수행 하였다. 전산유체역학(CFD)을 이용하여 반건식 반응기에서 속도분포 온도분포를 조사하여 반응기의 최적 운전 조건을 조사하였다. 본 모델에 사용된 반응기의 직경은 3 m 이며 높이는 9 m 이다. 반응기로 유입되는 연소가스의 양은 $6,125Nm^3/hr$ 이며 반응기 유입 가스의 온도는 493K 이다. 반응기에 유입되는 소석회 양은 151 kg/hr 이다. 반응기의 입구 형상이 변하면 반응기 내의 온도가 변하며 반응기 내의 가스속도는 0.48 m/sec 에서 1.17m/sec 였으며, 반응기 출구의 가스속도는 6.9에서 7.42m/sec 였다. 모델링 결과에 의하면 반응기 내의 평균 가스 속도와 출구에서의 평균가스 속도는 각각 0.489 m/sec와 7.424 m/sec 였으며, 반응기 출구 온도는 448 K 였다.

• Journal of Advanced Research in Ocean Engineering
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• 제3권2호
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• pp.59-65
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• 2017

When an anchor is dropped into the sea, there exists a danger of collision on the pipeline and subsea cables in the seabed. This collision could cause huge environmental disasters and serious economic losses. In order to secure the safety of subsea structures such as pipelines and subsea cables from the external impact, it is necessary to estimate the exact external force through the anchor's terminal velocity on the water. FLUENT, a computational fluid dynamic program, was used to acquire the terminal velocity and drag coefficient computation. A half-symmetry condition was used in order to reduce the computational time and a moving deforming mesh technique also adapted to present hydrostatic pressure. The results were examined with the equation based on Newton's Second Law to check the error rate. In this study, three example cases were calculated by stockless anchors of 5.25 ton, 10.5 ton, and 15.4 ton, and for the onshore experiment dropped height was back calculated with the anchor's terminal velocity in the water.

• 한국군사과학기술학회지
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• 제10권4호
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• pp.12-19
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• 2007

In this study, nonlinear flow-induced vibration(flutter) analyses of a 2-DOF launch vehicle airfoil have been conducted in supersonic and hypersonic flow regimes. Advanced aeroelastic analysis system based on computational fluid dynamics and computational structural dynamics is successfully developed and applied to the present analyses. Nonlinear unsteady aerodynamic analyses considering strong shock wave motions are conducted using inviscid Euler equations. Aeroelastic governing equations for the 2-DOF airfoil system is solved by the coupled integration method with interactive CFD and CSD computation procedures. Typical wedge type airfoil shapes with initial angle-of-attacks are considered to investigate the nonlinear flutter characteristics in supersonic(15). Also, the comparison of detailed aeroelastic responses are practically presented as numerical results.