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수치해석기법을 이용한 사이클론 집진기 내 유동 특성에 관한 연구
임태균(T.G. Lim),전완호(W.H. Jeon),김재우(J.W. Kim),박준철(J.C. Park),이정호(J.H. Lee),이상철(S.C Lee) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.10
A cyclone separator is a relatively simple structure to separate particles by turning flow which has the centrifugal force. However, complex flow fields lead to a difficult understanding of the detailed phenomenon of particle removal. In this study, a numerical analysis was performed to confirm flow characteristics and particle behavior in the cyclone separator by using commercial CFD program SC/Tetra. The collection efficiency of this study showed good agreement with experimental data for particle diameter more than 4㎛.
수치해석기법을 이용한 노트북 소형 냉각팬의 유동 및 소음 특성에 관한 연구
전완호(W.H. Jeon),임태균(T.G. Lim),御法川?(Gaku Minorikawa),宮原雅晴(Masaharu Miyahara) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.10
In recent years, the size of a notebook gets thinner and smaller. Its inner size makes problems in cooling fan performance, system installation condition, and so on. In this study, a small turbofan was installed in the very narrow gap like a notebook system, in order to generate similar condition to a real product. Experiments were performed to measure the fans performance and the flow and noise characteristics, results were compared with computational ones. CFD simulation predicted P-Q curve under about 5% error in high flowrate and its trend agreed with experiment data over the flow range. The noise was measured at a distance of 100 mm from a rotation axis direction of an impeller. The measured data corresponded well with computational ones of broadband and BPF noise analyzed by a commercial program(FlowNoise).
CAA를 이용한 소형 직류팬의 유동소음 및 예측에 관한 연구
전완호(W. H. Jeon),임태균(T. G. Lim),홍현기(H. K. Hong),御法川 學(Gaku Minorikawa) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.11
The paper describes the prediction method for the unsteady flow field and the aeroacoustic noise of an small axial fan. The prediction method is comprised of various CFD conditions and acoustic analogy by using Ffowcs Williams-Hawkings equation. The tested fan was an axial fan with impeller outside diameter 170 mm and 5 blades. Virtual anechoic room which has same size with real one was used for CFD. URANS and LES turbulence models were used and optimized mesh was selected with mesh dependence study. Calculation conditions were also studied such as time step and sampling time of noise analysis. In this paper, we got optimum analysis conditions and computational results, their results were compared with measured ones.
전완호(W. H. Jeon),임태균(T. G. Lim),御法川 ?(Gaku Minorkkawa),宮原 雅晴(Masaharu Miyahara) 한국소음진동공학회 2013 한국소음진동공학회 학술대회논문집 Vol.2013 No.10
In recent years, a notebook like an ultrabook gets thinner. Its thickness causes problems in cooling fan performance, system installation condition, and so on. In this study, we installed a small turbofan in notebook system with very narrow gap in order to generate similar condition to a real product. Experiments were performed to measure the fan`s performance and the flow and noise characteristics, its results were compared with computational ones. Prediction of P-Q curve using CFD showed under about 5% error in high flow rate and its trend was agreed with experimental one over the flow field. Experimental data to measure the noise at a distance of 100 mm from a rotation axis direction of an impeller corresponded well with computational ones of broadband and BPF noise. The noise experiments to measure at a distance of 100 mm from a rotation axis direction of an impeller corresponded well with computational ones of broadband and BPF noise. Especially, tip part of impeller blade and part of exit and bottom near cut off of a casing were dominant noise source in an analysis by a commercial program(FlowNoise)
범용 유동해석 데이터 형식을 이용한 유동소음 수치해석 프로그램 개발
최익황(I. H. Choi),김연호(Y. H. Kim),김준희(J. H. Kim),임태균(T. G. Lim),전완호(W. H. Jeon) 대한기계학회 2017 대한기계학회 춘추학술대회 Vol.2017 No.11
Recently, the noise problem has been recognized as a serious problem in addition to pollution such as fine dust due to industrialization. In this paper numerical analysis methods using computational fluid dynamics (CFD) and computational aeroacoustics (CAA) was performed using the CFD general notation system (CGNS) and developed the S/W for visualizing the analyzed result of flow noise. The aerodynamic noise analysis S / W has been developed to deal larger models and larger grids.
헬리콥터 로터 블레이드 제빙시스템 설계를 위한 블레이드 제빙해석 기법 연구
박남은(N.E. Park),우철훈(C.H. Woo),이석준(S.J. Yee),이재복(J.B. Yi),임태균(T.G. Lim) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
When the helicopter is flighting through icing condition, the ice could be accreted on fuselage and blades. The ice on blade could deform the blade configuration and increase the weight of blade. The unstable motions of blade make decreasing of performance, handling quality and structural stability due to the abnormal weight increase and configuration change. The helicopter deicing system is required to avoid risk by icing. Generally, the engine intake and the pitot sensor are adapted anti-icing system, but the rotor blade uses deicing system because the large size heater mat of blade needs a lot of power consumption. The anti-icing system is always active heater mat in icing condition; the deicing system is run alternately by on/off time sequence to avoid ice accretion on blade. Especially, due to the composite blade is weak by heat, over heat could make weak brittleness of blade. Thus, the de-icing system should be designed not only eliminate the ice on leading edge but also not damage the blade by heat source. First of all, the icing region estimation on blade is needed to design of rotor blade deicing system. In this paper, air flow field and multi-phase fluid analysis was performed by the commercial CFD s/w, SC/Tetra to calculate the collection efficiency around objects. The ice accretion analysis was performed by developed in-house code, ASTROD based on Messinger thermodynamic model. The computation result shows good estimations of icing region and ice thickness. In this study, de-icing situation is simplified that the blade surface adjoin with ice and thermal conduction occur at that interface. To analysis of convection on exterior surface of ice and internal heat power from heater mat by numerical method, discrete computational nodes of ice covered blade and consider phase change at the interface blade and ice. The numerical analysis result compared with ice wind tunnel test data of the blade to evaluate. The numerical method results show similar with experimental data about time to eliminate the ice and temperature of off-time range.
로터 블레이드 제빙 시스템 설계를 위한 예측 코드 개발 및 결빙 풍동 시험
우철훈(C.H. Woo),김경삼(K.S. Kim),이석준(S.J. Yee),이재복(J.B. Yi),임태균(T.G. Lim),김정일(J.I. Kim),박남은(N.E. Park) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.11
When the helicopter is flighting through icing condition, the ice could be accreted on fuselage and blades. The ice on blade could deform the blade configuration and increase the weight of blade. The unstable motions of blade make decreasing of performance, handling quality and structural stability due to the abnormal weight increase and configuration change. The helicopter deicing system is required to avoid risk by icing. To protect the icing, the anti-icing system or the deicing system is used. Generally, the intake, the pitot sensor are adapted the anti-icing system, but the rotor blade uses deicing system because the large size heater mat of blade needs a lot of power consumption. The anti-icing system always actives heater mat in icing condition; the deicing system is run alternately by on/off time sequence to avoid ice accretion on blade. The design concepts of deicing system are needed estimation of heater mat location, scheduling on/off time sequence to avoid ice accretion, fixing of power consumption of heater mat. First of all, the icing region estimation on blade is needed to design of rotor blade deicing system. In this paper, air flow field and multi-phase fluid analysis was performed by the commercial CFD s/w, SC/Tetra to calculate the collection efficiency around objects. The ice accretion analysis was performed by developed in-house code, ASTROD based on Messinger thermodynamic model. The computation results show good estimation of ice accretion shape and ice thickness. The development of computational tool for icing/deicing is just one part of deicing system design process. The understanding of physical phenomenon of icing and deicing on blade surface is needed for design of deicing system. The icing/deicing wind tunnel test was performed to evaluate the function of deicing system of rotor blade that showed the phase changing on blade surface from ice to water at 0℃. And the deicing system design information was acquired from experimental results by on/off time scheduling.