• Journal of Mechanical Science and Technology
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• 제18권2호
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• pp.302-312
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• 2004

This work developed improved slip factor model and correction method to predict flow through impeller in forward-curved centrifugal fan. Both steady and unsteady three-dimensional CFD analyses were performed to validate the slip factor model and the correction method. The results show that the improved slip factor model presented in this paper could provide more accurate predictions for forward-curved centrifugal impeller than the other slip factor models since the present model takes into account the effect of blade curvature. The correction method is provided to predict mass-averaged absolute circumferential velocity at the exit of impeller by taking account of blockage effects induced by the large-scale backflow near the front plate and flow separation within blade passage. The comparison with CFD results also shows that the improved slip factor model coupled with the present correction method provides accurate predictions for mass-averaged absolute circumferential velocity at the exit of impeller near and above the flow rate of peak total pressure coefficient.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1995년도 창립기념학술대회
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• pp.30-36
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• 1995

An axisymmetric flow induced by a train moving into a tunnel is numerically simulated. The effect of train shape on wavefront of a compression wave created by a train is investigated parametrically using several model trains having the same nose shape but different blockage. The zonal method combined with the Fortified Solution Algorithm (FSA) is employed as a numerical algorithm to solve this moving body problem. The computational result is compared with the experimental data. Good agreement is obtained, which justifies the present computational approach. The compression waves created by the model trains are compared and the result shows that the pressure gradient of the wavefront of the compression wave becomes small in the case of small blockage even though the nose shape is same. The wavefront is not determined solely by the cross-sectional area distribution of the train nose.

• 항공우주시스템공학회지
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• 제9권4호
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• pp.67-72
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• 2015

The analysis has been performed on the blockage effect at the propellant flow passage in a liquid rocket engine. This simulates an example of emergency situation where flow passage is partially blocked. The analysis method has been validated by predicting the pump head and flow rate within 1% precision against the measured data of turbopump-gas generator coupled test. When the oxidizer passage is reduced it is predicted that the mixture ratio decreases, the oxidizer pump head increases and the gas generator pressure increases. When the fuel passage is reduced it is predicted that the mixture ratio increases, fuel flow rate decreases and the fuel pump head increases.

• International Journal of Naval Architecture and Ocean Engineering
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• 제9권2호
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• pp.227-237
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• 2017

In this paper, we investigated physical characteristics of an artificial supercavity generated behind an axisymmetric cavitator. Experiments for the same model were carried out at two different cavitation tunnels of the Chungnam National University and the University of Minnesota, and the results were compared and verified with each other. We measured pressures inside the cavity and observed the cavity formation by using a high-speed camera. Cavitation parameters were evaluated in considering blockage effects of the tunnel, and gravitational effects on supercavity dimensions were examined. Cavity dimensions corresponding to the unbounded cavitation number were compared. In addition, we investigated how artificial supercavitation develops according to the combination of injection positions and direction.

• 항공우주시스템공학회지
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• 제2권4호
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• pp.7-12
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• 2008

Averaged heat transfer coefficients were measured in a turbine blade internal cooling passage model with three blockage walls. Each blockage wall was equipped with 9 staggered holes or slots in order to create different shaper of repeated jet impingement. The effect of jet shape on the averaged heat transfer coefficient was studied by the copper-thermocouple method and three Reynolds number of 10,000, 20,000, and 30,000 were tested. Results showed that the repeated stagger jets could increase the averaged heat transfer coefficient by at least 9 times compared to the smooth channel cases. Due to the large pressure drop induced by the repeated jet impingement, the thermal performance was less than 1 for all cases and decreased as the Reynolds number increased. Among the tested cases, the widest slot showed the best thermal performance. The measurement results showed that the thermal performance of the heat transfer augmentation by repeated stagger jets could be improved by altering the jet shape, and other shape of impingement jet will be studied in near future.

• 한국가스학회지
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• 제3권3호
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• pp.23-28
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• 1999

밀폐공간 내에 블록을 조합하여 부피와 표면적이 다르게 내용물을 채우고 용기 부피에 대한 내용물의 부피와 내용물의 표면적을 변화시키면서 LPG 또는 NG와 공기 혼합가스의 폭발특성을 측정하여 밀폐공간 내부에 있는 내용물의 부피와 표면적의 변화가 폭발특성에 미치는 영향을 해석하고자 하였다. 폭발용기는 가로 세로 높이가 각각 $100cm{\times}60cm{\times}45cm$인 부피 270리터의 금속 용기이며, 용기 내 가연성 혼합가스는 전기 스파크로 착화시켰고, strain형 압력센서로 폭발압력을 측정하였다. 실험 결과 부피봉쇄율이 증가할수록 폭발압력이 감소하였으며, 내용물의 표면적의 증가에 따라서도 폭발압력이 낮아졌으며, 이러한 폭발압력의 감소 경향은 표면적의 증가에 대한 영향보다 부피의 증가에 의한 영향이 더욱 크게 나타났다.

• 한국항공우주학회지
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• 제34권4호
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• pp.11-16
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• 2006

유체 공급배관내의 압력진동을 감쇠할 수 있는 방법으로 배관내에 오리피스를 설치하는 방법을 채택하여, 그 압력진동 감쇠효과를 수치해석을 통해 조사하였다. 본 연구에서는, 압력진동의 진폭이 작다는 가정에 기초하여 오리피스의 음향학적 감쇠효과에 초점을 맞추었다. 오리피스의 위치에 따른 계산 결과로부터 압력진동의 마디, 즉 속도진동의 배가 되는 위치에 오리피스를 설치할 때 가장 효과적으로 압력 진동이 감쇠되었다. 이에 반해서, 오리피스를 압력진동의 배에 설치한 경우에는 오리피스의 설치 효과가 아주 미약하였다. 오리피스의 유로 봉쇄율이 증가함에 따라 감쇠효과는 단조적으로 증가하였고, 오리피스의 두께가 증가할수록 공진성을 약화시켜 감쇠효과가 크게 나타났다. 또한, 직경이 작은 배관에서 감쇠 효과가 더 크게 나타났다.

• 대한기계학회논문집B
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• 제25권8호
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• pp.1113-1121
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• 2001

Effects of gap sizes(3.9 and 15mm) of vertical annuli and the bottom blockage on the nucleate pool boiling heat transfer at atmospheric pressure condition have been examined experimentally, and the results were compared to those with a single tube without confinement. The annular geometry resulted in significant increase in heat transfer coefficient. The effect is much enhanced with the bottom blockage. The heat transfer coefficient for the closed bottom condition is three times greater than the unconfined tube at 30kW/㎡ when the gap size is 3.9mm. However, with further increase of the heat flux much more than 70kW/㎡, all these effects were diminished.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2002년도 춘계 학술대회논문집
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• pp.79-87
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• 2002

The present work analyzed the effect of mixing vane shape on the flow structure and heat transfer downstream of mixing vane in a subchannel of fuel assembly, by obtaining velocity and pressure fields, turbulent intensity, flow-mixing factors, heat transfer coefficient and friction factor using three-dimensional RANS analysis. NJl5, NJ25, NJ35, NJ45, which were designed by the authors, were tested to evaluate the performances in enhancing the heat transfer. Standard $\kappa-\epsilon$ model is used as a turbulence closure model, and, periodic and symmetry conditions are set as boundary conditions. The flow blockage ratio is kept constant, but the twist angle of mixing vane is changed. The results with three turbulence models( $\kappa-\epsilon$, $\kappa-\omega$, RSM) were compared with experimental data.

• 한국유체기계학회 논문집
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• 제18권5호
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• pp.5-12
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• 2015

This paper presents a numerical investigation of the effect of the dihedral stator on the loss in a transonic axial compressor. Four stator geometries with different stacking line variables are tested in the flow simulations over the whole operating range. It is found that a large shroud loss at the rotor outlet and the subsequent shroud corner separation in the stator passage occur at low mass flow rate. The hub dihedral stator and bowed blade generate unexpected hub-corner-separation, thereby causing a large total pressure loss over the entire operating range. However, the corresponding blockage forces the high momentum flow near the hub to divert toward the upper part of the passage suppressing the negative axial velocity region. The dihedral stator increases deflection angle and secondary vorticity near the endwall where the dihedral is applied. As a result, the endwall loss which is related to the endwall relative velocity decreases.