• 대한기계학회:학술대회논문집
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• 대한기계학회 2002년도 학술대회지
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• pp.479-482
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• 2002

Riblets with longitudinal grooves along the streamwise direction have been used as an effective flow control technique for drag reduction. A flexible micro-riblet with v-grooves of peak-to-peak spacing of $300{\mu}m$ was made using a MEMS fabrication process of PDMS replica. The flexible micro-riblet was attached on the whole surface of a NACA0012 airfoil with which grooves are aligned with the streamwise direction. The riblet surface reduces drag coefficient about $7.9{\%}\;at\;U_o=3.3m/s$, however, it increases drag about $8{\%}\;at\;U_o=7.0m/s$, compared with the smooth airfoil without riblets. The near wake has been investigated experimentally far the cases of drag reduction ($U_o\;=\;3.3 m/s$) and drag increase ($U_o\;=\;7 m/s$). Five hundred instantaneous velocity fields were measured for each experimental condition using the cross-correlation PIV velocity field measurement technique. The instantaneous velocity fields were ensemble averaged to get spatial distribution of turbulent statistics such as turbulent kinetic energy. The experimental results were compared with those of a smooth airfoil under the same flow condition. The micro-riblet surface influences the near wake flow structure largely, especially in the region near the body surface

• 대한조선학회논문집
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• 제32권2호
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• pp.43-55
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• 1995

평판 위에 놓여진 스트럿(strut) 주위의 난류유동을 MAC 방법에 의하여 수치계산하였다. 난류 모델은 Baldwin-Lomax 모델이며 평판과 스트럿의 접합부 부근에서의 처리를 위하여 Buleev의 m2ixing length를 도입하였다. 계산결과의 검증을 위하여 DTRC의 풍동 실험 결과와 비교하였다. 실험에서 나타난 horseshoe vortex가 계산에서도 재현되는 등 전반적으로 계산결과와 실험결과 간에 좋은 일치를 볼 수 있었다. 그러나 접합부에서 극히 가까운 부근과 스트럿의 후류에서는 불일치를 보여 이 곳에서의 난류모델의 개선이 필요한 것으로 보여졌다. 결론적으로 평판과 스트럿의 접합부 부근의 유동을 계산함에 있어서 Baldwin-Lomax 모델은 도입된 많은 단순화를 위한 가정에도 불구하고 실용적으로 유용한 결과를 주는 것으로 보여진다.

• 한국추진공학회지
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• 제17권1호
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• pp.61-69
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• 2013

핀틀 움직임에 의해 발생되는 큰 유동박리에 대해 적합한 2-방정식 난류모델의 압축성계수 보정모델을 판단하기 위하여 수치적 연구를 수행하였다. 난류모델은 저 레이놀즈수 k-${\varepsilon}$ 모델과 k-${\omega}$ SST 모델에 압축성 보정 모델(Wilcox와 Sarkar 모델)을 적용하여, 핀틀 노즐의 세부유동장을 관찰하고 노즐 벽면에서의 압력을 실험데이터와 비교 분석하였다. 마하디스크(Mach disk)의 위치와 박리영역에서의 압력 회복 형태는 난류모델에 따라 다르게 나타났으며, 각 난류모델에 압축성 보정을 적용하여 유동 박리 포획의 정확도를 개선하였다. 압축성이 보정된 k-${\varepsilon}$ 모델이 실험결과와 매우 잘 일치하였다.

• 한국해양공학회지
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• 제10권3호
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• pp.138-152
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• 1996

Many studies of heat transfer on the swirling flow or unswirled flow in a abrupt pipe expansion are widely carried out. The mechanism is not fully found evidently due to the instabilities of flow in a sudden change of the shape and appearance of turbulent shear layers in a recirculation region and secondary vortex near the corner. The purpose of this study is to obtain data through an experimental study of the swirling flow and heat transfer downstream of an abrupt expansion in a circular pipe with uniform heat flux. Experiments were carried out for the turbulent flow nd heat transfer downstream of an abrupt circular pipe expansion. The uniform heat flux condition was imposed to the downstream of the abrupt expansion by using an electrically heated pipe. Experimental data are presented for local heat transfer rates and local axial velocities in the tube downstream of an abrupt 3:1 & 2:1 expansion. Air was used as the working fluid in the upstream tube, the Reynolds number was varied from 60, 00 to 120, 000 and the swirl number range (based on the swirl chamber geometry, i.e. L/d ratio) in which the experiments were conducted were L/d=0, 8 and 16. Axial velocity increased rapidly at r/R=0.35 in the abrupt concentric expansion turbulent flow through the test tube in unswirled flow. It showed that with increasing axial distance the highest axial velocities move toward the tube wall in the case of the swirling flow abrupt expansion. A uniform wall heat flux boundary condition was employed, which resulted in wall-to-bulk temperatures ranging from 24.deg. C to 71.deg. C. In swirling flow, the wall temperature showed a greater increase at L/d=16 than any other L/d. The bulk temperature showed a minimum value at the pipe inlet, it also exhibited a linear increase with axial distance along the pipe. As swirl intensity increased, the location of peak Nu numbers was observed to shift from 4 to 1 step heights downstream of the expansion. This upstream movement of the maximum Nusselt number was accompanied by an increase in its magnitude from 2.2 to 8.8 times larger than fully developed tube flow values.

• Wind and Structures
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• 제11권5호
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• pp.345-359
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• 2008

An experimental investigation of the flow over the rectangular body located in close proximity to a ground board was reported using the particle image velocimetry (PIV) technique. The present experiments were conducted in a closed-loop open surface water channel with the Reynolds number, $Re_H=1.2{\times}10^4$ based on the model height. In addition to the PIV measurements, flow visualization studies were also carried out. The PIV technique provided instantaneous and time-averaged velocity vectors map, vorticity contours, streamline topology and turbulent quantities at various locations in the near wake. In the vertical symmetry plane, the upperbody flow is separated from the sharp top leading edge of the model and formed a large reverse flow region on the upper surface of the model. The flow structure downstream of the model has asymmetric double vortices. In the horizontal symmetry plane, identical separated flow regions occur on both vertical side walls and a pair of primary recirculatory bubbles dominates the wake region.

• 한국전산유체공학회지
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• 제13권3호
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• pp.21-27
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• 2008

The reactor head of a sodium-cooled fast reactor KALIMER-600 should be cooled during the reactor operation in order to maintain the integrity of sealing material and to prevent a creep fatigue. Analyzing turbulent natural convection flow in the cover gas region of reactor vessel with the commercial CFD code CFX10.0, the cooling requirement for the reactor head and the performance of the insulation plate were assessed. The results showed that the high temperature region around reactor vessel was caused by the convective heat transfer of Helium gas flow ascending the gap between the insulation plate and the reactor vessel inner wall. The insulation plate was shown to sufficiently block the radiative heat transfer from pool surface to reactor head to a satisfactory degree. More than $32.5m^3$/sec of cooling air flow rate was predicted to maintain the required temperature of reactor head.

• 해양환경안전학회지
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• 제27권1호
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• pp.145-152
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• 2021

본 연구의 목적은 슬리브 이음된 배관 사이의 간극과 Re가 변할 때 배관 내의 유동은 어떻게 변하는지 조사함으로써 조정관 설치 시에 압력손실과 난류 강도를 감소시킬 수 있는 배관 간극(Lp)을 파악하는 것이다. 슬리브 이음된 배관 두께(tp)는 5 mm로 고정하고 Lp는 10, 50, 100 및 200 mm로 하여 슬리브 이음부의 속도, 압력 분포, 재순환 영역에서의 재부착점 길이 및 Re와의 상관관계를 해석하였다. 상용 프로그램인 Ansys fluent 18.1을 이용하였고, Re의 범위는 200 ≤ Re ≤ 5,000으로 하여 층류에서 난류까지 슬리브 이음부의 유동 특성을 파악하였다. 슬리브 이음부의 확대비와 축소비는 각각 1.2와 0.83이였고 Lp가 일정할 때 Re가 커질수록 슬리브 하류 가장자리(edge)의 난류 강도와 압력 변화가 크게 나타났다. 이는 슬리브 벽면에서의 유동이 tp에 의해 흐트러지고 속도 에너지의 손실이 발생하면서 슬리브 이음부의 가장자리에 영향을 미친 것으로 판단된다. Lp가 10 mm 이하의 경우, Re가 증가함에 따라 가장자리의 난류 강도에는 큰 변화가 없었다. 재순환 영역에서의 재부착점은 Lp가 10 mm 이하에서 나타나지 않았으며 와(vortex)의 영향도 없었다. 3,000 ≤ Re의 경우, Lp가 증가함에 따라 슬리브 이음부 벽면에서의 재부착점 길이는 거의 일정하였다.

• 한국유체기계학회 논문집
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• 제19권2호
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• pp.21-26
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• 2016

The objective of present study is to assess the performance of the first stage compressor in a total 3-stage 5000 HP-level turbo compressor. CFD commercial code, CFX has been used to predict three-dimensional flow characteristics inside of the impeller. Shear Stress Transport (SST) model has been used to simulate turbulent flows through Reynolds-averaged Navier-Stokes (RANS) equations. Grid dependency has been also checked to get optimal grid distribution. Numerical results have been compared with the experimental test results to elucidate performance characteristics of the present compressor. In addition, flow characteristics of the impeller only have been studied for various blade configurations. Angular offset in leading edge of the blade has been selected for the optimal blade design. Performance characteristics in region of low mass flow rate and high pressure ratio between the impeller entrance and exit have been investigated for the selection of optimal blade design. Also, flow instability such as stall phenomena has been studied and anti-stall characteristics have been checked for various blade configurations in the operational window.

• 대한기계학회논문집B
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• 제22권9호
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• pp.1277-1289
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• 1998

The objective of the present study is to investigate experimentally the mean flow characteristics of the three-dimensional turbulent boundary layer over a rotating disk with an impinging jet at the center of the disk, which may be regarded as one of the simplest models for the flow in turbomachinery. A relatively strong radial outflow (crossflow) generated from the impinging jet is added to the radial outflow (crossflow) induced by the centrifugal force in order to create the three-dimensional boundary layer. A new calibration technique has been introduced to determine the velocity direction and magnitude using an I-wire probe, where the uncertainties are ${\pm}1.5^{\circ}$ and ${\pm}0.35\;m/s$, respectively, in the laminar boundary layer region, compared with the known exact solutions. The flow in the tangential direction is of similar type to that associated with a favorable pressure gradient, considering that no wake region appears in wall coordinate velocity profiles and the Clauser shape factor is between 4.0 and 5.3. The flow angle is significantly changed by the crossflow generated by the impinging jet.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 춘계학술대회논문집
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• pp.97-103
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• 2002

Vibration isolation technology using an air spring and laminated rubber bearing is widely used because it has excellent vibration isolation characteristics. In the part of that, we usually make use of the self-damped air suing. It is occupied two chambers, restrictor, diaphragm and load plate. Two chambers contain compressed air and the volume of chambers and the area of load plate give a definition of stiffness and load. The restrictor and the volume ratio of two chambers give a definition of damping ratio. The conventional model of restrictor is made of one orifice and it causes turbulent flow in the orifice at the region of large deflection. The stillness of air suing is larger and the damping is lower in the region of large deflection. In the multi-orifice case, the stiffness is similar to air spring with one orifice but damping ratio is larger than conventional air spring. And damping ratio is smaller than conventional air suing in small deflection region. Deflection is small in the region of high frequency so small damping is better than large damping. As a result, we can reduce the storage stiffness of air suing in the wide region of deflection and increase the damping ratio in the region of large deflection. After this, we will try to and the relation of Reynolds Number and Flow Resistance then we are going to make another restrictor for air spring to improve damping ratio and stiffness.