• 유체기계공업학회:학술대회논문집
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• 2004.12a
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• pp.590-595
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• 2004

Turbo fan as an air moving device is widely used for its silent characteristics and high efficiency relative to the other centrifugal multi blade impeller. In general, turbo fan is installed with a scroll casing for energy conversion from kinetic one to pressure energy. However, a turbo fan without scroll casing is considered as a present model that is proposed model for compact design of a product In detail, the model has only 4 cutoffs as guiders for 4 separated outlets. Specially, equal distribution of flow rate generated by the model blower is main interest in this investigation. The optimal position of the guider is found by reducing abnormal flows such as reverse flow in each outlet.

• The KSFM Journal of Fluid Machinery
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• v.12 no.2
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• pp.52-57
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• 2009

The effects of number of blades on the hydraulic performance of the inducer were studied using a computational method. Inducers with number of blades from 2 to 4 were used for computations and the hydraulic performances of the inducers were compared. The computational results showed that the hydraulic performance decreased due to the increase of the skin friction loss at blade passages as the blade number increased. The results also showed that the strength of the backflow became weak because of the decrease of unfavorable pressure gradient as the blade number increased.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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• 1986.11a
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• pp.52-55
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• 1986

최근 난류상태에서 운전되는 베어링의 사용이 많아짐에 따라, 윤활문제에서도 난류영역에 관한 연구의 필요성을 느끼게 되었다. 베어링내의 흐름이 난류상태가 되면 마찰손실의 증가등 증류상태에 비해 여러가지의 윤활특성이 달라지는데, 특히 마찰열에 의한 윤활제의 온도증가는 베어링성능변화에 크나큰 영향을 줄 것으로 예측된다. 일반적으로 유막내에서의 온도변화가 그다지 없는 경우는 재래의 등점도이론으로 어느정도 성능예측이 가능하나, 온도변화가 지배적인 경우에는 점도변화를 고려한 THD해석이 성능예측에 보다 유용하다고 알려져 있으며 이에대한 많은 연구가 수행되고 있다. 이들 해석은 실제 온도상승이 가장 큰 벽면에 인접한 영역에 대해서 불완전하며, 편심율이 큰 경우에서와 같이 축 방향의 유동이 크거나, 역류가 발생하는 경우에는 적응이 곤란하다. 본 연구에서는 이런 점을 개선하기 위해 $\kappa-\varepsilon$모델을 이용한 저어널베어링에서의 3차원 THD해석을 행하였다.

• Journal of Biomedical Engineering Research
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• v.19 no.3
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• pp.297-303
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• 1998

The sinus distal to the prosthetic heart valve influences the valve closure behavior and velocity field near the valve, therefore affects the hydrodynamic performance of the prosthetic heart valve. In order to study the effects of valve distal geometry on the hydrodynamic performance of the prosthetic valves, mechanical bileaflet valve(SJMV), monoleaflet polymer valve(MLPV) and trileaflet polymer valve(FTPV) are inserted in the test sections which have the straight and the sinus shape distal to the valve. Leakage volumes and systolic mean pressure drops are measured in the pulsatile mock circulation flow loop. Leakage volumes are slightly less and systolic mean pressure drops are higher in the sinus test section comparing to those in the straight test section, but the differences are statistically insignificant. Flow waveforms are analyzed in order to predict the valve closure behavior. The distal sinus does not affect the closure of the MLPV, but early valve closure of SJMV is observed in the sinus test section. This effect is more significant in FTPV, and the reverse flow peak of FTPV is reduced in the sinus test section. Therefore the sinus distal to the valve can reduce the reverse flow jet caused by sudden valve closure.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.2
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• pp.1-9
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• 2003

In the present study, a 3-D Parallel DSMC method in developed on unstructured meshes for the efficient simulation of rarefied gas flows. Particle tracing between cells in achieved based on a linear shape function extended to three dimensions. For high parallel efficiency, successive domain decomposition is applied to achieve load balancing between processors by accounting for the number of particles. A particle weighting technique is also adopted to handle flows containing gases of significantly dirrerent number densities in the same flow domain. Application is made for flow past a 3-D delta wing and the result is compared with that from experiment and other calculation. Flow around a rocket payload at 100km altitude is also solved and the effect of plume back flow from the nozzle in studied.

• Journal of Aerospace System Engineering
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• v.12 no.5
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• pp.8-15
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• 2018

The geostationary satellite uses a liquid apogee engine, to obtain a required velocity increment to enter a geostationary orbit. However, as the liquid apogee engine operates in the vacuum, a considerable disbursement of exhaust plume flow, from the liquid apogee engine can trigger a backflow. As this backflow may possibly collide with the satellite directly, it can cause adverse effects such as surface contamination, thermal load, and altitude disturbance, that can generate performance reduction of the geostationary satellite. So, this study investigated exhaust plume behavior of 400 N grade liquid apogee engine numerically. To analyze exhaust plume behavior in vacuum condition, the DSMC (Direct Simulation Monte Carlo) method based on Boltzmann equation is used. As a result, thermal fluid characteristics of exhaust plume such as temperature and number density, are observed.

• Journal of Energy Engineering
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• v.25 no.4
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• pp.152-158
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• 2016

Nitrogen oxide is generated by the chemical reaction of oxygen and nitrogen in higher temperature environment of combustion facilities. The NOx reduction equipment is generally used in the power plant or incineration plant and it causes enormous cost for the construction and maintenance. The flue gas recirculation method is commonly adopted for the reduction of NOx formation in the combustion facilities. In the present study, the computational fluid dynamic analysis was accomplished to elucidated the cold flow characteristics in the flue gas recirculation burner with coanda nozzles in the flue gas recirculation pipe. The inlet and outlet of flue gas recirculation pipes are directed toward the tangential direction of circular burner not toward the center of burner. The swirling flow is formed in the burner and it causes the reverse flow in the burner. The ratio of flue gas recirculation flow rate with the air flow rate was about 2.5 for the case with the coanda nozzle gap, 0.5mm and it was 1.5 for the case with the gap, 1.0mm. With the same coanda nozzle gap, the flue gas recirculation flow rate ratio had a little increase when the air flow rate changes from 1.1 to 2.2 times of ideal air flow rate.

• The Magazine of the Society of Air-Conditioning and Refrigerating Engineers of Korea
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• v.17 no.4
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• pp.418-425
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• 1988

Since conventional computer program is workable only with velocity boundary condition, in practical fluid passage such as clean room which usually have wide inlets and outlets, it is not easy to measure velocity itself because of its vector property. Furthermore a certain assumption of velocity at boundaries may lead to physically unreasonable results. From this motivation, we have developed a computer program to predict whole flow field imposed on pressure-based boundary condition which can be measured by relatively simple method. The only additional velocity boundary condition that should be imposed on to make the problem unique, are no slip condition at all walls and zero cross stream velocity at inlet. The result of present study was compared with that by Bernoulli equation being used practically. They were coincident well each other within 5%, therefore the validity of the present method is proved. In the present work, the flow field in a clean room subject to pressure-based boundary conditions at an inlet and two exits was predicted numerically. The pressure difference between the inlet and the left exit which keeps relatively low pressure among two exits is fixed as 150[Pa] and the pressure at the right exit is varied from zero to 150[Pa] by the increment of 25[Pa]. For each cases the flow characteristics in the clean room, the velocity profile at the inlet, and the flow rate through the two exits was predicted. The flow rate through the right exit imposed on relatively higher pressure than the left exit decreased linearly according to the increase of pressure of the right exit. When the pressure of the right exit is increased enough to cause back flow at the exit, the flow rate is rapidly decreased.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.20 no.7
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• pp.2386-2396
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• 1996

A numerical simulation has been performed for isothermal and reacting flows in an exisymmetric, bluff-body research combustor. The present formulation is based on the density-weighted averaged Navier-Stokes equations together with a k-epsilon. turbulence model and a modified eddy-breakup combustion model. The PISO algorithm is employed for solution of thel Navier-Stokes system. Comparison between measurements and predictions are made for a centerline axial velocities, location of stagnation points, strength of recirculation zone, and temperature profile. Even though the numerical simulation gives acceptable agreement with experimental data in many respects, the present model is defictient in predicting the recoveryt rate of a central near-wake region, the non-isotropic turbulence effects, and variation of turbulent Schmidt number. Several possible explanations for these discrepancies have been discussed.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.6
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• pp.75-81
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• 2014

The flame deflector should be constructed to minimize the induced environmental effects on the launch vehicle and to minimize the exhaust impingement effects on the launch complex structures during the lift-off operation. Therefore, it should be designed to avoid recirculation and reverse flow of rocket exhaust plumes. The circumstance around launch complex and characteristics of launch vehicle should be taken into consideration for the flame deflector design. In this paper, we designed the flame deflector reflecting KSLV-II 1st engine characteristics and analyzed the effect of exhaust plumes related to change geometry by means of computational flow analysis.