• 설비공학논문집
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• 제11권2호
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• pp.157-166
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• 1999

Numerical calculations of turbulent natural convection in an enclosure of the 20 kYA oil-immersed transformer model are presented. The transformer is modelled as two concentric cylinders with different heights and diameters. The thermal boundary layers are well represented in the temperature distributions along the wall of the transformer model. The flow stratification between the hot and cold walls can not be seen in the transformer model. The turbulence eddy viscosity has its maximum at the center of the core and its maximum values at the top of the core are larger than those at the bottom of the core.

• 대한조선학회지
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• 제21권2호
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• pp.9-17
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• 1984

Laminar and turbulent boundary layers on a rotating sector and a helical blade are calculated by differential method. The estimation of three dimensional viscous flows provide quite useful informations for the design of propellers and turbo-machinery. A general method of calculation is presented in this paper. Calculated laminar boundary layer on a sector shows smooth development of flows from Blasius' solution at the leading edge to von Karman's solution of a rotating disk at the down-stream. Eddy viscosity model is adopted for the calculation of turbulent flows. Turbulent flows on a rotating blade show similar characters as laminar flows. But cross-flow angle of turbulent flows are reduced in comparison with laminar boundary layers. Effects of rotation make flow structures significantly different from two-dimensional flows. In the range of Reynolds number of model scale propellers, large portion of the blade are still in the transition region from laminar to turbulent flows. Therefore viscous flow pattern might be quite different on the blade of model propeller. The present method of calculation is to be useful for the research of scale effects, cavitation, and roughness effects of propeller blades.

• 대한토목학회논문집
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• 제13권3호
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• pp.193-206
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• 1993

쇄파대(碎波帶)에서 undertow에 관한 해석적(解釋的) 모형(模型)을 제시(提示)하였다. 유도(誘導)된 기초방정식(基礎方程式)의 각 항(項)은 크기 비교(比較)로 평가(評價)되었으며, 이에 따라 난류법선응력(亂流法線應力)와 streaming velocity 항(項)이 무시(無視)될 수 있었다. undertow의 기동력(起動力)이 되는 파종성분(波動成分)의 각 항(項)은 Chebyshev 4차(次) 다항식(多項式)으로 근사(近似)한 파형(波形)으로 산정(算定)하였다. 그리고 과동점성계수(過動點性係數)의 연직분포(鉛直分布)를 3가지 형태(形熊)의 함수(凾數)로 가정(假定)하였으며, 과동점성계수(過動點性係數)의 상수(常數)는 새로운 경계조건(境界條件)을 도입(導入)하여 결정(決定)하였다. 그 결과(結果), undertow의 해(解)를 구하는데 필요한 인력(入力) 매개변수(媒介變數)가 간단화(簡單化) 되었다. 여러가지 수리실험자료(水理實驗資料)와 본(本) 모형(模型)의 해(解)를 비교(比較)한 결과(結果), 저면경사(底面傾斜)가 완만(緩慢)할수록 그리고 과동점성계수(過動點性係數)의 연직분포(鉛直分布)를 선형함수(線形凾數)로 가정(假定)하였을 때 좋은 결과(結果)를 나타내었다.

• 대한기계학회논문집B
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• 제24권11호
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• pp.1523-1534
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• 2000

The performance of a number of existing dynamic subgrid-scale(SGS) models is evaluated in large-eddy simulations(LES) of two prototype transitional and turbulent shear flows, a planar jet and a channel flow. The dynamic SGS models applied include the dynamic Smagorinsky model(DSM);Germano et al. 1991, Lully 1992), the dynamic tow-component model(DTM; Akhavan et al. 2000), the dynamic mixed model(DMM;Zang et al, 1993). and the dynamic two-parameter model(DTPM; Salvetti & Banerjee 1995). The results are compared with those for DNS for their evaluation. The LES results demonstrate the superior performance of DTM with use of a sharp cutoff filter and DMM with use of a box filter, as compared to their respect counterpart DSM, in predicting the mean statistics, spectra and large-scale structure of the flow, Such features of DTM and DMM derive from the construction of the models in which tow separate terms are included to represent the SGS interactions; a Smagorinsky edd-viscosity term to account for the non-local interactions, and a local-interaction term to account for the nonlinear dynamics between the resolved and subgrid scales in the vicinity of the LES cutoff. As well, overall the SGS models using a sharp cutoff filter are more successful than those using a box filter in capturing the statistics and structure of the flow. Finally, DTPM is found to be compatible or inferior to DMM.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2010년도 제34회 춘계학술대회논문집
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• pp.190-193
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• 2010

고성능 액체로켓의 핵심 요소인 고압 연소기에 사용되는 분사기에 대한 혼합 및 연소 특성을 도출하기 위하여 초임계 상태에 적용되는 혼합 및 연소모델을 수치적으로 연구하였다. 난류모델은 LES(Large Eddy Simulation)를 기반으로 하였고, 난류연소모델은 혼합분율(Z)을 이용한 Laminar Flamelet Model을 사용하였다. 그리고 초임계 영역의 상태량을 계산하기위해 Soave Redlich-Kwong 상태 방정식, 점성계수와 열전도도에 대하여 Chung이 제안한 고압상태 혼합물에 대한 방정식, 확산계수에 대하여 Fuller 이론에 Takahashi가 제안한 고압상태의 특징을 고려한 식을 적용하였다. 계산결과는 선행연구자의 결과와 비교하였고, LOx post 후방에 발생되는 와류에 따른 보염영역에 대하여 연구하였다.

• Nuclear Engineering and Technology
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• 제53권11호
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• pp.3625-3634
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• 2021

The crossflow is the key phenomenon in turbulent flow inside rod bundles. In order to establish confidence on application of computational fluid dynamics (CFD) to simulate the crossflow in rod bundles, three Reynolds-Averaged Navier Stokes (RANS) models i.e. the realizable k-ε model, the k-ω SST model and the Reynolds stress model (RSM), and the Large Eddy simulations (LES) with the Wall-Adapting Local Eddy-viscosity (WALE) model are validated based on the Particle Image Velocimetry (PIV) flow measurement experiment in a 5 × 5 rod bundle. In order to investigate effects of periodic boundary condition in the gap, the numerical results obtained with four inner subchannels are compared with that obtained with the whole 5 × 5 rod bundle. The results show that periodic boundaries in the gaps produce strong errors far downstream of the spacer grid, and therefore the full 5 × 5 rod bundle should be simulated. Furthermore, it can be concluded, that the realizable k-ε model can only provide reasonable results very close to the spacer grid, while the other investigated models are in good agreement with the experimental data in the whole downstream flow in the rod bundle. The LES approach shows superiority to the RANS models.

• 대한기계학회논문집
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• 제18권9호
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• pp.2443-2453
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• 1994

The structure of turbulence of fully developed flow through four concentric annuli with the rough outer wall was investigated experimentally for a Reynolds number range Re=15, 000-93, 000. Turbulence intensities were measured in three(u, v, w) directions, and turbulence shear stresses in annuli of radius=0.13, 0.26, 0.4 and 0.56, respectively. Due to the square roughness element attached periodically along the axial direction, the radial velocity fluctuations show similar distribution regardless of the different .alpha.cases. However, the axial and circumferential velocity fluctuation profiles demonstrate the longitudinal turbulence structures are strongly influenced by the .alpha. values. The turbulent eddy viscosity deduced form mean velocity distributions and the measured Reynolds shear stresses are also presented and discussed.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2010년도 제35회 추계학술대회논문집
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• pp.19-23
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• 2010

초임계 환경에서 작동하는 액체 로켓 엔진의 케로신 스월 인젝터에서 케로신 물성치에 따른 인젝터 내외에서의 분사 특성을 연구하였다. 케로신의 물성치를 계산하기 위해 surrogate 모델이 적용되었다. 난류 수치 모델은 large eddy simulation을 기반으로 하였으며 SRK 상태 방정식, Chung의 기법을 포함하고 있다. 초임계 환경의 수치 해석 결과는 천이 임계 조건의 결과와 비교되었으며 스월 인젝터 내부의 액막과 중심부 사이의 밀도 및 점성 계수 분포의 차이가 관찰되었다.

• Nuclear Engineering and Technology
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• 제26권3호
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• pp.345-354
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• 1994

수치 해석을 통하여 이차유동을 포함한 핵연료봉 주위의 난류 유동장을 예측하였다. 등방성 난류와 점성계수 모델과 이차 유동을 모사하기 위해 단순화된 대수응력모델을 사용하여 난류 운동 에너지 (k)와 난류 에너지 소멸률($\varepsilon$)의 이 방정식 모델과 운동량 방정식을 유한 차분법으로 풀어 유동장내의 평균속도, 이차유동, 난류 운동 에너지, 난류 응력 분포 등을 구하였다. 수치해석 예측치를 실험데이타와 비교하여 만족할만한 결과를 얻었고 유동장내에서 이차유동의 영향을 확인하였다. 즉 이차유동이 절대 크기는 작더라도 대류 효과에 의해 큰 영향을 미치는 것을 본 연구를 통해 알 수 있었다.

• Journal of the Korean Society for Industrial and Applied Mathematics
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• 제3권2호
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• pp.161-171
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• 1999

Aerodynamic sensitivity analysis codes are developed via the hand-differentiation using a direct differentiation method and an adjoint method respectively from discrete two-dimensional compressible Navier-Stokes equations. Unlike previous other researches, Baldwin-Lomax algebraic turbulence model is also differentiated by hand to obtain design sensitivities with respect to design variables of interest in turbulent flows. Discrete direct sensitivity equations and adjoint equations are efficiently solved by the same time integration scheme adopted in the flow solver routine. The required memory for the adjoint sensitivity code is greatly reduced at the cost of the computational time by allowing the large banded flux jacobian matrix unassembled. Direct sensitivity code results are found to be exactly coincident with sensitivity derivatives obtained by the finite difference. Adjoint code results of a turbulent flow case show slight deviations from the exact results due to the limitation of the algebraic turbulence model in implementing the adjoint formulation. However, current adjoint sensitivity code yields much more accurate sensitivity derivatives than the adjoint code with the turbulence eddy viscosity being kept constant, which is a usual assumption for the prior researches.