• 한국전산유체공학회:학술대회논문집
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• 2004.03a
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• pp.42-48
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• 2004

Numerical simulation of viscous compressible flow in turbomachinery cascade involves many problems due to the complex geometry of blade but also flow phenomena. In the present study, numerical investigations have been performed to examine the three-dimensional flow characteristics inside the transonic linear turbine cascades using a commercial code, FLUENT. Multi-block H-type grids are applied to the high-turning turbine rotor blades and comparisons with the experimental data and the numerical results have been done. In addition, the effects of turbulence models on the prediction of the endwall flows are analyzed in the sense of the flow compressibility.

• Proceedings of the KSME Conference
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• 2002.08a
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• pp.329-332
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• 2002

A theoretical study is made of the steady flow of a compressible fluid in a rapidly rotating finite cylinder. Flow is generated by imposing mechanical and/or thermal disturbances at the rotating endwall disks. Both the Ekman and Rossby numbers are small. A detailed consideration is given to the energy budget for a control volume in the Ekman boundary layer. A combination of physical variables, which is termed the energy contents, consisting of temperature and modified angular momentum, emerges to be relevant. The distinguishing features of a compressible fluid, in contrast to those of an incompressible fluid, are noted. For the Taylor-Proudman column to be sustained, in the interior, it is shown that the net energy transport between the solid disk wall and the interior fluid should vanish. Physical rationalizations are facilitated by resorting to the concept of the afore-stated energy content.

• Journal of computational fluids engineering
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• v.13 no.2
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• pp.27-41
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• 2008

An unstructured hybrid mesh flow solver has been developed for the simulation of three-dimensional steady and unsteady incompressible flow fields. The incompressible Navier-Stokes equations with an artificial compressibility method were discretized by using a node-based finite-volume method. For the unsteady time-accurate computation, a dual-time stepping method was adopted to satisfy a divergence-free flow field at each physical time step. An implicit time integration method with local time stepping was implemented to accelerate the convergence in the pseudo-time sub-iteration procedure. The one-equation Spalart-Allmaras turbulence model has been adopted to solve high-Reynolds number flow fields. The flow solver was parallelized to minimize the CPU time and to overcome the computational overhead. This method has been applied to calculate steady and unsteady flow fields around submarine configurations and a 3-D infinite cylinder. Validations were made by comparing the predicted results with those of experiments or other numerical results. It was demonstrated that the present method is efficient and robust for the prediction of steady and unsteady incompressible flow fields.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.31-32
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• 2002

임계노즐(critical nozzle)은 유동을 유로 최소단면부에서 초크시켜, 질량유량을 계측하기 위한 일종의 유체기구로, 최근 다양한 분야에서 널리 활용되고 있다. 압축성 기체역학의 관계식에 의하면, 임계노즐을 통하는 기체유동의 이론적인 질량유량은 노즐 목의 직경, 노즐 상류의 온도와 압력 그리고 기체의 비열비 등의 함수로 주어진다 그러나 실제 유동에서는 점성과 열전달 등의 초과로 인하여, 이론적 질량 유량과 실제유량의 비 즉 유출계수(discharge coefficient)의 값은 1.0으로 되지 않는다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.1-8
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• 2004

The objective of this study is convergence acceleration of multigrid Navier-Stokes solvers. This study has been performed to enhance the performance of preconditioned multi-stage time stepping method which is a popular smoother for the multigrid Navier-Stokes solvers. Comparative study on the convergence characteristics of the ADI and DDADI preconditioners has been conducted. It is shown that the DDADI preconditioner has better performance than the ADI by numerical tests on the 2-D compressible turbulent flows past airfoils. The Spalart-Allmaras turbulent model and the Baldwin-Lomax turbulent model have been compared with the multigrid calculations.

• Transactions of the Korean Society of Mechanical Engineers
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• v.11 no.3
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• pp.395-408
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• 1987

Turbulent flows in an axisymmetric reciprocating engine are numerically simulated at it's suction and compression stage. Amounts of heat transfer through the wall of the cylinder are also estimated. k-.epsilon. turbulence model is adopted and the law of the wall is applied at grid-points near the wall. More than 40 * 40 grids are reguried to reasonably predict flows and the 3-level finite difference scheme for the time derivative term appears to be effective rather than the 2-level scheme. Calculated mean velocity distributions shows good agreements with an available experimental data. The program reasonably simulates flow patterns and pressures throughout the suction and the compression stages of the reciprocating engine. Predicted intensities of turbulence are still deviated from measured data. Further researches for turbulence modeling are expected.

• Proceedings of the KSME Conference
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• 2005.11a
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• pp.80.2-80.2
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• 2005

• Proceedings of the KSME Conference
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• 2005.11a
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• pp.81.1-81.1
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• 2005

• The Korean Journal of Rheology
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• v.9 no.1
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• pp.16-26
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• 1997

사출 성형된 제품에서 발생하는 잔류응력은 최종 제춤의 기하학적 정밀도와 기계적 성질 및 열적 성질에 영향을 미친다. 사출성형된 제품의 잔류응력을 예측하기 위해서는 먼 저 열 및 유동장의 해석을 수행하여야 하고이를 위해서는 사출 성형의 세단계. 즉 충전, 보 압, 냉각을 모두고려해야한다. 검사체적 방법에 기초한 혼합 유한요소/유한차분방법을 사용 하는 수치 해석적 기법에 의하여 충전과정가 후충전 과정의 유동장 해서을 수행하였다. 일 반화된 헬레쇼 유동을 가정하였고 보압과 냉각과정시의 고본자의 압축성을 고려하였다. 점 도의 전단 변형률의 크기와 온도에 대한 의존성은 개선된 크로스 모델을 사용하여 나타내었 다. Tait에 의해 제안된 상태방정식은 고분자의 온도, 압력, 부피의 상호관계를 묘사하는 좋 은 방법을 제공하였다. 유동해석을 통하여 전 공정에 걸쳐서 온도와 압\ulcorner장의 변화에 대한 데이터를 얻었고 제품의 고체 응력해석의 입력 데이터로 사용하였다. 유한요소응력해석에는 평면 응력요소를 사용하였다. 다양한 형태의 금형에 대해서 공정 변수들을 달리하여 유동장 의 해석과 잔류응력의 계산을 수행하였다. 이로부터 공정조건과 유동장의 관계를 밝히고 최 종 제춤의 잔류 응력에의 영향을 고찰하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.6
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• pp.25-30
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• 2010

Dual throat nozzle(DTN) is recently attracting much attention as a new concept of the thrust vectoring technique. This DTN is designed with two throats, an upstream minimum and a downstream minimum at the nozzle exit, with a cavity in between the upstream throat and exit. In the present study, a computational work has been carried out to analyze the performance of a dual throat nozzle(DTN) at various mass flow rate of secondary flow and nozzle pressure ratios(NPR). Two-dimensional, steady, compressible Navier-Stokes equations were solved using a fully implicit finite volume scheme. The present computational results were validated with some experimental data available. Based upon the present results, The control effectiveness of thrust-vector is discussed in terms of the thrust coefficient and the discharge coefficient.