• 한국전산응용수학회:학술대회논문집
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• 한국전산응용수학회 2003년도 KSCAM 학술발표회 프로그램 및 초록집
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• pp.1-1
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• 2003

In this talk, a reduced-order modeling methodology based on centroidal Voronoi tessellations (CVT's)is introduced. CVT's are special Voronoi tessellations for which the generators of the Voronoi diagram are also the centers of mass (means) of the corresponding Voronoi cells. The discrete data sets, CVT's are closely related to the h-means clustering techniques. Even with the use of good mesh generators, discretization schemes, and solution algorithms, the computational simulation of complex, turbulent, or chaotic systems still remains a formidable endeavor. For example, typical finite element codes may require many thousands of degrees of freedom for the accurate simulation of fluid flows. The situation is even worse for optimization problems for which multiple solutions of the complex state system are usually required or in feedback control problems for which real-time solutions of the complex state system are needed. There hava been many studies devoted to the development, testing, and use of reduced-order models for complex systems such as unsteady fluid flows. The types of reduced-ordered models that we study are those attempt to determine accurate approximate solutions of a complex system using very few degrees of freedom. To do so, such models have to use basis functions that are in some way intimately connected to the problem being approximated. Once a very low-dimensional reduced basis has been determined, one can employ it to solve the complex system by applying, e.g., a Galerkin method. In general, reduced bases are globally supported so that the discrete systems are dense; however, if the reduced basis is of very low dimension, one does not care about the lack of sparsity in the discrete system. A discussion of reduced-ordering modeling for complex systems such as fluid flows is given to provide a context for the application of reduced-order bases. Then, detailed descriptions of CVT-based reduced-order bases and how they can be constructed of complex systems are given. Subsequently, some concrete incompressible flow examples are used to illustrate the construction and use of CVT-based reduced-order bases. The CVT-based reduced-order modeling methodology is shown to be effective for these examples and is also shown to be inexpensive to apply compared to other reduced-order methods.

• 한국전산유체공학회지
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• 제21권4호
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• pp.61-70
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• 2016

Dong-tan Station, shared by high-speed railway and urban express railway, is a very complicated underground station having 6 tracks together with barrier and shafts between them, therefore it seems very hard to investigate the aerodynamic effects including the pressure variation and train gust in the station when a high-speed train runs through it. In this study, the aerodynamic effects on the structures and platform passengers when a high-speed train runs through an underground station have been studied using Computational Fluid Dynamics. STAR-CCM+ has been employed for numerical simulation based on Navier-Stokes equation and 2-equation turbulence model and moving mesh scheme supported by STAR-CCM+ has also been used to represent the relative motion between a train and station. Based on the simulation results, the unsteady flow fields in the underground station induced by the high-speed train have been analyzed and the pressures on the PSDs and pressure variation at the platform have quantitatively assessed.

• 한국음향학회지
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• 제36권6호
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• pp.371-377
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• 2017

에어컨의 성능은 분리형 실외기의 냉각 성능과 밀접한 관련이 있으며, 그에 따라 대다수의 관련 선행 연구에서는 실외기 내부 축류팬의 단독 성능에 대한 연구를 진행하였다. 하지만 축류팬을 제외한 실외기 내부 여러 구성요소의 영향에 대한 연구는 부족한 실정이다. 따라서 본 논문에서는 여러 요소 중 팬 오리피스가 실외기 유동 성능에 미치는 영향을 수치적으로 분석하였다. 고정밀 유동장 해석을 위해 약 1800만 개의 격자로 구성된 가상 팬 테스터를 개발하고, V-LES의 일종인 비정상 RANS(Reynolds-averaged Navier-Stokes) 방정식을 CFD(Computational Fluid Dynamics) 기법에 기초하여 해석하였다. 수치 해석의 유효성을 확인하기 위해서 실험을 통해 측정한 실외기 시스템의 P-Q 곡선을 가상 팬 테스터를 사용한 수치 해석 결과와 비교하였다. 유효성을 검증한 수치 기법을 이용하여 실외기 유량 성능을 최대화할 수 있는 오리피스 형상 최적 설계를 수행하였다.

• 한국음향학회지
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• 제40권6호
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• pp.555-565
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• 2021

본 연구의 목표는 냉장고 냉동실 냉기순환용으로 사용되는 후향익 원심팬 시스템을 대상으로 익형의 형상을 최적설계 하여 유동성능 및 소음성능을 향상시키는 것이다. 대상 시스템은 전형적인 원심팬 시스템에서 사용되는 스크롤 하우징 형상 없이 두 개의 Volute가 후면 덕트 시스템과 연계하여 냉기를 공급한다는 특성을 가지고 있다. 먼저 팬 시스템의 유동 및 소음성능을 실험적으로 평가하였다. 유동실험에서 팬 성능 시험기를 사용하여 P-Q 곡선을 도출할 수 있었으며, 무향실에서 소음실험을 통해 소음 스펙트럼을 측정하였다. 다음으로, 3차원 비정상 Navier-Stokes 방정식을 전산유체역학을 사용하여 수치해석하여 유동 특성을 분석하였으며, 예측한 유동장을 입력값으로 Ffowcs Willams-Hawkings방정식을 이용해 소음해석을 수행하였다. 수치해석결과는 실험 결과와 비교를 통해 그 유효성을 검증하였다. 검증된 수치해석 기법을 기반으로 반응표면법의 2인자 중심합성법을 통해 유량이 최대가 되는 입구각 및 출구각을 도출하였다. 마지막으로 최적화된 팬을 대상으로 시제품을 제작하여 실험한 결과 개선된 유량 성능 및 소음성능을 확인하였다.

• 한국음향학회지
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• 제42권3호
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• pp.250-261
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• 2023

본 연구에서는 펌프젯 추진기를 대상으로 공동, 비공동 조건에서의 유동 소음원을 규명하기 위하여 추진기의 각 구성품인 덕트와 스테이터, 로터에 의한 소음 기여도를 평가하였으며, 공동과 비공동 조건에서의 소음 수준을 비교하였다. 대형 캐비테이션 터널 내 Suboff 잠수함 선형과 펌프젯 추진기를 대상으로 균일혼상류 가정의 비정상 비압축성 Reynolds averaged Navier-Stokes(RANS) 방정식을 적용하였으며, 이상 유동을 모사하기 위해 Volume of Fluid(VOF) 기법과 Schnerr-Sauer 공동 모델을 적용하였다. 유동해석 결과를 기반으로 수중방사소음을 예측하기 위해 Ffowcs Williams and Hawkings(FW-H) 방정식 기반의 음향상사법을 적용하였으며, 덕트와 스테이터, 로터로 구성된 3개의 비투과성 적분면과 추진기를 감싸는 형태의 2가지 투과성 적분면을 선정하여 소음 기여도를 평가하였다. 소음 예측결과로부터 스테이터는 전체 소음에 대한 직접적인 기여도는 낮으나 덕트와 로터에서의 유동 박리에 의한 소음원 형성에는 영향을 미치는 것을 확인하였으며, 유동이 박리되는 연직상방과 우측방향으로 소음이 크게 방사되었다. 또한 로터에서는 날개의 흡입면과 압력면 간의 압력 섭동에 의해 추진방향으로 소음이 크게 방사되었으며, 투과성적분면을 통해 체적 소음원인 공동의 효과를 반영할 수 있음을 확인하였다.

• 한국수소및신에너지학회논문집
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• 제31권3호
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• pp.328-336
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• 2020

In the Francis turbine, the leakage flow through the runner gaps which are between the runner and the stator structure influences the internal flow and hydraulic performance. Thus, the investigation for the flow characteristics induced by the runner gaps is important. However, the runner gaps are often disregarded by considering the time and cost of the numerical analysis. Therefore, in this study, the flow characteristics according to runner gaps of the Francis turbine model were investigated including the leakage flow of the runner cone. The three-dimensional unsteady Reynolds-averaged Navier-Stokes analyses were conducted using a scale-adaptive simulation shear stress transport as a turbulence model for observing the influence of the leakage flow on the internal flow and hydraulic performance. The efficiencies were decreased slightly with runner gaps; and the complicated flows were captured in the gaps.

• Wind and Structures
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• 제30권4호
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• pp.325-338
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• 2020

In this paper, the improvement of the anti-snow performance of a high-speed train (HST) is studied using the unsteady Reynolds-Averaged Navier-Stokes simulations (URANS) coupled with the Discrete Phase Model (DPM). The influences of the proposed flow control scheme on the velocity distribution of the airflow and snow particles, snow concentration level and accumulated mass in the bogie cavities are analyzed. The results show that the front anti-snow structures can effectively deflect downward the airflow and snow particles at the entrance of the cavities and alleviate the strong impact on the bogie bottom, thereby decrease the local accumulated snow. The rotational rear plates with the deflecting angle of 45° are found to present well deflecting effect on the particles' trajectories and force more snow to flow out of the cavities, and thus significantly reduce the accretion distribution on the bogie top. Furthermore, running speeds of HST are shown to have a great effect on the snow-resistance capability of the flow control scheme. The proposed flow control scheme achieves more snow reduction for HST at higher train's running speed in the cold regions.

• 한국수자원학회논문집
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• 제54권11호
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• pp.1011-1019
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• 2021

본 연구에서는 제방 형태의 보를 월류하는 수중도수와 잠긴흐름을 수치모의 하였다. 수치모의를 위하여 URANS 방정식을 해석하였으며, 난류폐합식으로 k-𝜔 모형을 사용하였다. 기존의 실험결과를 이용하여 수치모형을 검증하였는데, 모의된 롤러의 형상, 자유수면, 그리고 평균유속분포가 실험결과와 비교적 잘 일치하는 것을 확인하였다. 수중도수와 잠긴흐름에서 물의 체적비 분포를 비교하였으며, 각 흐름에 대한 2중 평균된 체적비의 특성을 제시하였다. 수치모의를 이용하여 보의 길이, 유량, 그리고 하류 수위에 따라 수중도수에서 잠긴흐름으로 천이되는 조건을 검토하였으며, 천이가 발생할 때의 상대 월류수심을 침수비의 함수로 제시하였다.

• Wind and Structures
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• 제20권4호
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• pp.549-564
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• 2015

The three-dimensional unsteady incompressible Reynolds-averaged Navier-Stokes equations and k-${\varepsilon}$ double equations turbulent model were used to investigate the effect on the measurements of anemometers due to a passing high-speed train. Sliding mesh technology in Fluent was utilized to treat the moving boundary problem. The high-speed train considered in this paper was with bogies and inter-carriage gaps. Combined with the results of the wind tunnel test in a published paper, the accuracy of the present numerical method was validated to be used for further study. In addition, the difference of slipstream between three-car and eight-car grouping models was analyzed, and a series of numerical simulations were carried out to study the influences of the anemometer heights, the train speeds, the crosswind speeds and the directions of the induced slipstream on the measurements of the anemometers. The results show that the influence factors of the train-induced slipstream are the passing head car and tail car. Using the three-car grouping model to analyze the train-induced flow is reasonable. The maxima of horizontal slipstream velocity tend to reduce as the height of the anemometer increases. With the train speed increasing, the relationship between $V_{train}$ and $V_{induced\;slipstream}$ can be expressed with linear increment. In the absence of natural wind conditions, from the head car arriving to the tail car leaving, the induced wind direction changes about $330^{\circ}$, while under the crosswind condition the wind direction fluctuates around $-90^{\circ}$. With the crosswind speed increasing, the peaks of $V_X,{\mid}V_{XY}-V_{wind}{\mid}$ of the head car and that of $V_X$ of the tail car tend to enlarge. Thus, when anemometers are installed along high-speed railways, it is important to study the effect on the measurements of anemometers due to the train-induced slipstream.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.91-93
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• 2003

A comprehensive numerical study is carried out to investigate for the understanding of the flow evolution and flame development in a supersonic combustor with normal injection of ncumally injecting hydrogen in airsupersonic flows. The formulation treats the complete conservation equations of mass, momentum, energy, and species concentration for a multi-component chemically reacting system. For the numerical simulation of supersonic combustion, multi-species Navier-Stokes equations and detailed chemistry of H2-Air is considered. It also accommodates a finite-rate chemical kinetics mechanism of hydrogen-air combustion GRI-Mech. 2.11[1], which consists of nine species and twenty-five reaction steps. Turbulence closure is achieved by means of a k-two-equation model (2). The governing equations are spatially discretized using a finite-volume approach, and temporally integrated by means of a second-order accurate implicit scheme (3-5).The supersonic combustor consists of a flat channel of 10 cm height and a fuel-injection slit of 0.1 cm width located at 10 cm downstream of the inlet. A cavity of 5 cm height and 20 cm width is installed at 15 cm downstream of the injection slit. A total of 936160 grids are used for the main-combustor flow passage, and 159161 grids for the cavity. The grids are clustered in the flow direction near the fuel injector and cavity, as well as in the vertical direction near the bottom wall. The no-slip and adiabatic conditions are assumed throughout the entire wall boundary. As a specific example, the inflow Mach number is assumed to be 3, and the temperature and pressure are 600 K and 0.1 MPa, respectively. Gaseous hydrogen at a temperature of 151.5 K is injected normal to the wall from a choked injector.A series of calculations were carried out by varying the fuel injection pressure from 0.5 to 1.5MPa. This amounts to changing the fuel mass flow rate or the overall equivalence ratio for different operating regimes. Figure 1 shows the instantaneous temperature fields in the supersonic combustor at four different conditions. The dark blue region represents the hot burned gases. At the fuel injection pressure of 0.5 MPa, the flame is stably anchored, but the flow field exhibits a high-amplitude oscillation. At the fuel injection pressure of 1.0 MPa, the Mach reflection occurs ahead of the injector. The interaction between the incoming air and the injection flow becomes much more complex, and the fuel/air mixing is strongly enhanced. The Mach reflection oscillates and results in a strong fluctuation in the combustor wall pressure. At the fuel injection pressure of 1.5MPa, the flow inside the combustor becomes nearly choked and the Mach reflection is displaced forward. The leading shock wave moves slowly toward the inlet, and eventually causes the combustor-upstart due to the thermal choking. The cavity appears to play a secondary role in driving the flow unsteadiness, in spite of its influence on the fuel/air mixing and flame evolution. Further investigation is necessary on this issue. The present study features detailed resolution of the flow and flame dynamics in the combustor, which was not typically available in most of the previous works. In particular, the oscillatory flow characteristics are captured at a scale sufficient to identify the underlying physical mechanisms. Much of the flow unsteadiness is not related to the cavity, but rather to the intrinsic unsteadiness in the flowfield, as also shown experimentally by Ben-Yakar et al. [6], The interactions between the unsteady flow and flame evolution may cause a large excursion of flow oscillation. The work appears to be the first of its kind in the numerical study of combustion oscillations in a supersonic combustor, although a similar phenomenon was previously reported experimentally. A more comprehensive discussion will be given in the final paper presented at the colloquium.