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MLP 기법을 이용한 H<SUB>2</SUB>/CO/Air 초음속 동축 난류 화염 해석
최정열(J.-Y. Choi),김규홍(K.-H. Kim),한상훈(S.-H. Han) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.11
A MLP(Multi-Dimensional Limiting Procedure) scheme is applied for a supersonic turbulent combustion flow field developed for the multi-dimensional high resolution analysis of compressible flow field. LES (Large Eddy Simulation) is dominantly used for the turbulent combustion studies in these days since the turbulent combustion is governed by fuel/air mixing controlled by small scale eddy motion in fuel/air mixing layer. Present study demonstrate the superiority and efficiency of MLP scheme in compared previous 3<SUP>rd</SUP> order MUSCL scheme and 5<SUP>th</SUP> order WENO scheme by applying MLP scheme to the hybrid RANS/LES study of supersonic turbulent combustion flow field where high resolution shock capturing scheme is essential.
한상훈(S.H. Han),변재윤(J.Y. Byeon),김규홍(K.H. Kim) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
Numerical analysis of 150kW Huels-type arc jet was performed using compressible Navier-Stokes CFD code. To consider chemical reaction by high temperature, the flow was assumed to be chemical equilibrium states. As a turbulence and a radiation model, the two-equation k-epsilon model and the 3-band radiation model were adopted, respectively. Mass flow rate and current density were given as conditions for calculations. In this study, two kinds of mechanisms for injection of air flow wire considered. One is that air is provided by left wall surface and the other is that air is injected from upper wall surface. The pressure, density and temperature contours of two cases were compared and heat transfer rates were estimated. The numerical results of two cases were not much different to each other. However, in real 150KW device, air is injected from upper wall surface with swirl. To calculate more accurately, swirl effect is must be considered.
성두현(D. H. Sung),장윤석(Y. S. Jang),곽태영(T. Y. Kwak),정광호(K. H. Jung),백승배(S. B. Baek),한상훈(S. H. Han) 유공압건설기계학회 2019 유공압건설기계학회 학술대회논문집 Vol.2019 No.6
유압호스의 비선형적 재료특성과 인가되는 압력의 변화로, 호스 경로예측의 정합도가 높지 않은 것이 현실이다. 또한 CATIA 에서 Flexible Part 의 궤적은 최소 곡률반경으로 결정되는데, 중력과 유압호스 고유의 물성치가 적용되지 않아, 설계자 의도와 설계 숙련도에 따라 모델링 상호스궤적이 달라지게 된다. 이러한 이유들로 실물과 모델링의 정합성이 떨어져 품질 및 조립 문제의 발생가능성이 높아지게 되었고, 그에 따라 설계 변경량이 막대하였다. 따라서 유압호스의 고유 물성치로 궤적을 예측하는 Simulation Tool 이 필요하게 되었고, IPS(Industrial Path Solutions) 의 도입으로 기존 CATIA 설계 결과물보다 더욱 실물에 정합한 설계안을 얻을 수 있게 되었다. 본 논문을 통해 IPS Simulation Tool 의 도입목적과 유압호스 물성치를 소개하고, 역추적 기법으로 구축한 물성치 Data Base 에 대한 검증과 설계적용 사례, 추후 연구계획들을 설명한다.
액체로켓 엔진 연소장치 개발에 있어서의 전산유체역학 적용 사례
조미옥(M. Joh),김성구(S.-K. Kim),한상훈(S.H. Han),최환석(H.-S. Choi) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
This paper provides a brief introduction to application examples of the computational fluid dynamics to development of combustion devices for domestic liquid-propellant rocket engines. It is demonstrated that multi-dimensional flow analysis and multi-disciplinary combustion/cooling performance analysis can be effectively applied to provide key information on some performance-related design issues for thrust chambers and gas generators. Efforts are being made to understand complex physical phenomena inside these combustion devices, especially near the injection plate, by resolving mixing/combustion characteristics of LOX/kerosene with taking the geometry of liquid-liquid coaxial swirl injectors into consideration.