• Proceeding of EDISON Challenge
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• 2015.03a
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• pp.585-589
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• 2015

본 연구에서는 이중압축램프의 초음속 유동에서 발생하는 충격파 경계층 상호작용을 EDISON_CFD로 해석하기로 한다. 이중압축램프에선 역압력 구배로 인하여 경계층이 박리가 일어나게 되고 박리된 경계층이 다시 이중압축램프에 부착되어 생겨난 박리영역을 관찰할 수 있다. 박리영역의 앞뒤로 유동의 방향이 바뀌게 되면서 압축 팬(compression fan)과 재부착 팬(reattachment fan)이 충격파를 발생시키고 이중압축램프전방의 충격파와 만나서 복잡한 유동 구조를 가지게 됨을 확인하였다. 이와 같은 층류에서 난류, 박리와 재부착의 영역에서의 해석하기 위해선 해석자의 난류모델이 중요하다. $15^{\circ}-30^{\circ}$, $15^{\circ}-45^{\circ}$의 두 종류의 이중압축램프를 $k-{\omega}$ SST 난류 모델과 ${\gamma}-Re_{\theta}$ 천이 모델로 계산을 EDISON_CFD로 수행하였다. 난류 모델의 차이를 표면마찰계수, 압력계수, 마하수로 비교하여 차이점을 분석하였다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.8 no.3
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• pp.241-249
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• 1984

두 개의 긴 수직평판핀을 가진 등온수평원통으로 부터의 자연대류 열전달을 2차원 유한차분법에 의한 수치해석으로 연구하였다. 축방향의 두 수직평판핀을 가진 수평원통으로 부터의 열전달은 Ra=$10^{6}$, Pr=5 및 무차원 $K_{f}$t/KD=0.5인 경우에 보통 원통에서의 열전도보다 5.32% 증가되었다. Ra와 Pr가 증가하면 국소핀 누셀트수는 증가하고 무차원핀 온도는 감소된다. 그 러나 무차원핀 변수가 증가하면 국소핀 누셀트수와 무차원핀 온도분포는 증가된다. 최대국소핀 누셀트수는 Ra=$10^{6}$인 경우에 상향핀과 하향핀의 (r-r$_{0}$)=0.1-0.2에서 존재한다. 수 직핀을 가진 원통주위에서 부력 유도된 유동은 보통 원통에서 보다 더욱 활발하였다. 따라서 Ra=$10^{6}$ , Pr=5인 경우에 핀 근방에서의 무차원 무차원반경 방향 속도는 보통원통의 경 우보다 큰 값을 가진다.다.다.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.1
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• pp.38-46
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• 2022

One of the main goal of gas turbine rim seal research is to prevent thermal damage at rotor-stator disk by preventing hot gas of main flow in turbine passage. To increase sealing performance, several studies related to the improvement of rim seal configuration have been conducted. In addition, research based on actual operating condition is needed in order to apply effective turbine rim seal configuration. In this study, numerical simulation was conducted with variation of rotor rim seal thickness. Radial and axial expansion cases were tested numerically in this study. As a result, the cases showed different pressure distribution, sealing performance and flow characteristics according to the amount of secondary flow.

• Computational Structural Engineering
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• v.4 no.4
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• pp.135-144
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• 1991

The finite element technique incorporatating infinite elements is applied to analyzing the general three dimensional wave-structure interaction problems within the limits of linear wave theory. The hydrodynamic forces are assumed to be inertially dominated, and viscous effects are neglected. In order to analyze the corresponding boundary value problems efficiently, two types of elements are developed. One is the infinite element for modeling the radiation condition at infinity, and the other is the fictitious bottom boundary element for the case of deep water. To validate those elements, numerical analyses are performed for several floating structures. Comparisons with the results by using other available solution methods show that the present method incorporating the infinite and the fictitious bottom boundary elements gives good results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.3
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• pp.1-9
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• 2005

The interaction between hypersonic free stream and side jet flow at high altitudes is investigated by using the direct simulation Monte Carlo (DSMC) method. In order to alleviate the difficulty associated with the large density difference between the free stream and the side jet flow and to simulate the two flows simultaneously, a weighting factor technique is applied. For validation, the corner flow over a pair of plates perpendicularly attached is calculated with and without a side jet, and the results are compared with experiment. For a more realistic configuration, the flow past a blunted cone cylinder shape is solved. The leeward or windward jet is injected into the free stream and the effect on the aerodynamic force and moment is observed at various flow angles. The lambda shock effect and the wake structure are studied in terms of the surface pressure differential. A higher interaction between the free stream and the side jet flow is observed when the side jet is injected in the windward direction.

• Journal of the Society of Naval Architects of Korea
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• v.34 no.4
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• pp.148-157
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• 1997

In this paper, the flow around a V-shaped plate positioned against horizontal flow is numerically simulated by using finite volume method and experimentally visualized in two dimensional tank by dye injection method. The upwelling flow artificially induced by V-shaped plate mixes the stratified stagnant flow. It can be applied to mitigate the eutrophication and stratification of sea in the vicinity of offshore structures.

• Composites Research
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• v.15 no.6
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• pp.1-7
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• 2002

In VARTM process where a sacrificial medium is used to facilitate the resin flow, the velocity of resin varies drastically between the sacrificial medium and the fiber preform. Although the thickness-to-length ratio of a VARTM product is usually small, a 3-D analysis is prerequisite to analyze the lead-lag flow in the two different media. The problem associated with the full 3-D analysis is the CPU time. A full 3-D numerical mesh comprising large number of nodes requires an impractical CPU time on average computer platforms. In this study, a dual-scale analysis technique was developed. The flow analysis for the entire calculation domain was conducted in 2.5-D, and the 3-D analysis was performed for a small area of special concern. In some numerical examples, the local 3-D analysis could discover an eccentric flow pattern as well as the lead-lag flow that will inevitably be neglected in 2.5-D simulations. The global-local analysis technique practiced in this study can be used to analyze the intricate flow of resin through non-uniform media in affordable CPU times.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.34 no.10
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• pp.917-923
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• 2010

Direct numerical simulation (DNS) of a spatially developing turbulent boundary layer (TBL) with regularly arrayed cubical roughness elements was performed to investigate the effects of three-dimensional (3D) surface elements. The staggered cubes downstream were periodically arranged in the streamwise and spanwise directions with pitches of $p_x$/k=8 and $p_z$/k=2, where $p_x$ and $p_z$ are the streamwise and spanwise spacings of the cubes; the roughness height (k) was k=$1.5{\theta}_{in}$, where ${\theta}_{in}$ is the momentum thickness at the inlet. Spatially developing characteristics over the 3D cubical roughness were compared with the data obtained from the DNS over the two-dimensional (2D) rod roughened wall and smooth wall. Introduction of the cubical roughness on the TBL affected the turbulent Reynolds stresses not only in the roughness sublayer but also in the outer layer; and these effects are consistent with those observed over the 2D rough wall.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.7
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• pp.32-40
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• 2003

An experimental research has been carried out for flow visualizations of the shock wave/turbulent boundary-layer interaction control utilizing the aeroelastic flaps, Spark shadowgraphs, kerosene-lampblack tracings for the surface streakline pattern, and interference fringe patterns over a thin oil-film applied at the downstream of the shock interactions have been obtained , Effects of variation of the shapes and thicknesses of the flaps are tested, and all the results are compared to the solid-wall reference case without flow-control mechanism , From the qualitative observation of the variation of skin friction utilizing the interference fringe patterns over the silicone oil-film, a strong spanwise variation of the skin friction with a narrow and long region of separation has been noticed near the centerline behind the shock structure, which phenomenon demonstrate a strong three-dimensionality of the shock interaction flows, Influence of the shape of the cavity under the flaps to the shock interaction is also tested, and it is observed that the shape of the cavity is not negligible.

• Journal of the Korean Institute of Gas
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• v.15 no.3
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• pp.53-57
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• 2011

The present study has been carried out to analyze the flow characteristics of a heat recovery steam generator with the change of inlet flow conditions by using numerical flow analysis. The inlet of HRSG corresponds the outlet of gas turbine exit and the flow after gas turbine has strong swirl flow and turbulence. The inlet flow condition of HRSG should be included the exit flow characteristics of gas turbine. The present numerical analysis adopted the flow analysis result of gas turbine exit flow as a inlet flow condition of HRSG analysis. The computational flow analysis result of gas turbine exit shows that the maximum axial velocity appears near circular duct wall and the maximum turbulent kinetic energy and dissipation rate exist relatively higher gradient region of axial velocity. The comparison of flow analysis will be executed with change of inlet turbulent flow condition. The first case is using the inlet turbulent properties from the result of computational analysis of gas turbine exit flow, and the second case is using the assumed turbulent intensity with the magnitude proportional to the velocity magnitude and length scale. The computational results of flow characteristics for two cases show great difference especially in the velocity field and turbulent properties. The main conclusion of the present study is that the flow inlet condition of HRSG should be included the turbulent properties for the accurate computational result of flow analysis.