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박준영(JunYoung Park),백제현(JeHyun Baek) 대한기계학회 2002 대한기계학회 춘추학술대회 Vol.2002 No.5
In this paper, the development and validation of a three-dimensional, parallel, unsteady Navier-Stokes<br/> code for predicting the unsteady effects due to stator/rotor interaction in one-stage turbomachinery are<br/> conducted. The solver is parallelized using domain decomposition and Message Passing Interface(MPI)<br/> standard to overcome the limitation of memory and save the CPU time in three-dimensional unsteady<br/> calculation. A sliding mesh interface approach has been implemented to exchange flow information between<br/> blade rows. The numerical results are compared to validate the accuracy of code with experimental data<br/> wherever possible in UTRC LSRR one-stage turbine. The comparison shows a good agreements.
최민석(Minsuk Choi),백제현(Jehyun Baek) 한국유체기계학회 2004 유체기계 연구개발 발표회 논문집 Vol.- No.-
A three-dimensional computation was conducted to understand effects of the inlet boundary layer thickness on the loss mechanism in a low-speed axial compressor operating at the design condition(φ=85%) and near stall condition(φ=65%). At the design condition, the flow phenomena such as the tip leakage flow and hub corner stall are similar independent of the inlet boundary layer thickness. However, when the axial compressor is operating at the near stall condition, the large separation on the suction surface near the casing is induced by the tip leakage flow and the boundary layer on the blade for thin inlet boundary layer but the hub corner stall is enlarged for thick inlet boundary layer. These differences of internal flows induced by change of the boundary layer thickness on the casing and hub enable loss distributions of total pressure to be altered. When the axial compressor has thin inlet boundary layer, the total pressure loss is increased at regions near both casing and tip but decreased in the core flow region. In order to analyze effects of inlet boundary layer thickness on total loss in detail, using Denton's loss models, total loss is scrutinized through three major loss categories in a subsonic axial compressor such as profile loss, tip leakage loss and endwall loss.
축류형 유체 기계에서 팁 누설 유동 해석을 위한 난류 모델 성능 비교
이공희(Gonghee Lee),백제현(Jehyun Baek) 대한기계학회 2003 대한기계학회 춘추학술대회 Vol.2003 No.4
It is well-known that high anisotropic characteristic of turbulent flow field is dominant inside tip leakage<br/> vortex. This anisotropic nature of turbulence invalidates the use of the conventional isotropic eddy viscosity<br/> turbulence model based on the Boussinesq assumption. In this study, to check whether an anisotropic<br/> turbulence model is superior to the isotropic ones or not, the results obtained from steady-state Reynolds<br/> averaged Navier-Stokes simulations based on the RNG k-e and the Reynolds stress model in two test cases,<br/> such as a linear compressor cascade and a forward-swept axial-flow fan, are compared with experimental data.<br/> Through the comparative study of turbulence models, it is clearly shown that the Reynolds stress model,<br/> which can express the production term and body-force term induced by system rotation without any modeling,<br/> should be used to predict the complex tip leakage flow, including the locus of tip leakage vortex center,<br/> quantitatively.
김성수(Sungsu Kim),백제현(Jehyun Baek),최민석(Minsuk Choi) 한국전산유체공학회 2002 한국전산유체공학회 학술대회논문집 Vol.2002 No.-
This paper presents the result of numerical simulation of particles trace following melted zinc movement with nitrogen gas injection. The code of the computational fluid dynamics for numerical analysis was performed using FLUENT related to CFD, As application model, there was applied Eulerian multiphase model for simulation of melted zinc movement at first and then was used stochastic tracking technique for particles trace secondarily. Numerical simulation results are shown that particles move to the same direction as the movement of melted zinc.