• 한국산학기술학회논문지
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• 제20권4호
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• pp.580-589
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• 2019

인도네시아는 전력 공급이 매우 부족한 현실에 처해 있으며, 이에 대한 해결책으로 화력발전소 건설 계획이 증가하고 있다. 화력발전소는 발전에 수반되는 엔진과 장비의 과열을 식히기 위해 냉각수 계통을 필요로 하며, 냉각수 계통 중 순환수 취수펌프장(circulating water pump chamber)은 일반적으로 ANSI (1998) 기준에 따라 설계된다. 본 연구에서는 인도네시아 K-석탄화력발전소의 순환수취수펌프장이 현장 여건상 ANSI (1998)의 확산각 설계기준 $20^{\circ}$를 만족시킬 수 없어, 수리적으로 안정된 흐름 및 구조물이 되도록 3차원 수치모형실험을 수행하였다. 수치모형으로 Flow-3D 모형을 이용하였다. Flow-3D 모형의 적용성을 검토하기 위해 Rodi (1997)의 사각형 구조물 주변에 형성되는 흐름 연구 결과와 금회 수치해석 결과를 비교하였다. 수치해석에서 도출된 종방향 유속 분포는 잘 일치함을 보여주고 있다. 순환수취수펌프장 내 설계유속을 만족시키기 위해 유속 저감에 유리한 사각형 형태의 배플을 적용하였다. 순환수취수펌프장으로 유입되는 유속이 1.5 m/s ~ 2.5 m/s로 분포되는 경우, 배플에서 분리흐름의 각도는 약 $15^{\circ}{\sim}20^{\circ}$로 발생하였다. 이를 고려하여 분리흐름 각도 이하로 하류에 배플을 배치함으로 Inlet bay 설계유속 0.5 m/s 이하를 만족시켰다.

• 한국전산유체공학회지
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• 제13권2호
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• pp.8-13
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• 2008

A supersonic viscous flow over a five-degree half-angle cone is studied computationally with three-dimensional Navier-Stokes equations. Steady asymmetric solutions show that the asymmetric flow separation is caused by convective instability. The effects of angle of attacks, Reynolds numbers, and Mach numbers have been investigated and it is found that those factors affect the generation of the side force. The side force has the maximum value at ${\alpha}=22^{\circ}$, while over ${\alpha}=22^{\circ}$, asymmetric vortex becomes transient, which results in the unsteady shedding. At the angle of attack of 22 degrees, the side force increases with Reynolds number and decreases with Mach number. The increase of the side force stops over the critical Reynolds number for the present configuration.

• 한국항공운항학회지
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• 제28권2호
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• pp.12-17
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• 2020

Even though the benefit of flight at high angle-of-attack is to be able to reduce the speed of flight and maneuvers in complex flight environment, the flight at high angle-of-attack, however, is easy to be in stall which is characterized by sever unsteady flow separation over an airfoil. Current unsteady numerical analysis using DES was conducted to predict the aerodynamic characteristics of a NACA 0021 airfoil at high angle-of-attack conditions. And this provides the comparison with the steady numerical one with the typical turbulence models. The unsteady calculation by DES is appropriate in terms of predicting the aerodynamic performance of NACA 0021 airfoil at high angle-of-attack conditions.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2007년도 추계 학술대회논문집
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• pp.171-176
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• 2007

Supersonic viscous flow over a 5 degree half angle cone studied computationally with three-dimensional Navier-Stokes equations. Steady asymmetric solutions of 5-deg half angle cone show that the asymmetric flow separation is caused by convective instability. The angle of attack, Reynolds number, and Mach number affected the side force variation that is caused by asymmetric vortical flow.

• 해양환경안전학회:학술대회논문집
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• 해양환경안전학회 2006년도 추계학술발표회
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• pp.65-69
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• 2006

물제트분사장치가 부착된 NACA-0021 익 주변의 흐름을 업자영상유속계를 이용하여 고찰하였다. $R_e=6.0261\times10^4$에서 영각 (a) 을 $0^{\circ}\sim35^{\circ}$로 변화시켜가며, 물제트분사 속도를 0[m/s], 9.2[m/s] 의 2 가지로 조절한 결과 익 후류영역에서는 박리 후 비정상적인 (unsteady) 재순환 재부착 영역이 형성되었으며, 박리영역의 폭이 콴다 효과 (Coanda effect)를 갖는 물제트분사로 인하여 최대 1/3만큼 감소하는 경향을 확인하였다. 물분사가 없는 조건에서의 박리는 영각(a) $17^{\circ}\sim18^{\circ}$부근에서 시작되는 것이 관측되었으나, 물제트분사를 시켰을 경우 $20^{\circ}\sim21^{\circ}$에서 박리가 시작되는 것을 유통관측을 통해 알 수 있었다. 유통계측을 통해 익의 후연부 (trailing edge) 에서 생성되었던 와 (vortex, eddy) 가 물제트분사로 인해 소멸되는 것을 알 수 있었고, 영각이 작고 물분사 유속이 빠를 수록 박리영역의 감소가 더욱 가속화됨을 알 수 있었다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 추계학술대회논문초록집
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• pp.366.1-366
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• 2002

It is addressed that the turbulent broadband sound power from a sirocco fan can be modeled by the trailing edge noise. The trailing edge noise is usually influenced by inflow turbulence, separation, and boundary layer on the blade. The design parameters such as solidity(c/s) and stagger angle are specified to predict performance and noise level because the separation and slip velocity are strong1y affected by them along with the flow coefficient. (omitted)

• Journal of Mechanical Science and Technology
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• 제17권10호
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• pp.1485-1495
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• 2003

We investigate the triboelectrostatic separation of polyvinylchloride (PVC) from mixed plastics in the laboratory scale triboelectrostatic separation system. The flow and electric fields in the precipitator are obtained from the numerical solution of finite volume method. Using these flow and electric fields, we solved the particle motion equation considering the inertia, drag, gravity and electrostatic forces acted on the particles. The particle trajectories are obtained using a Lagrangian method as a function of different important variables such as Reynolds number, Stokes number, electrostatic force, electric charge and electric field distribution, inclined angle of plane electrodes, particle rebounding, particle charge decay rate after impact on the electrode surface, etc., in order to determine the optimal design conditions. The present predicted results for the cumulative yield represent well the experimental ones.

• Wind and Structures
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• 제11권3호
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• pp.221-240
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• 2008

The spanwise flow structure around a rigid smooth circular cylinder model in cross-flow has been investigated based on the experimental data obtained from a series of wind tunnel tests. Surface pressures were collected at five spanwise locations along the cylinder over a Reynolds number range of $1.14{\times}15^5$ to $5.85{\times}10^5$, which covered sub-critical, single-bubble and two-bubble regimes in the critical range. Separation angles were deduced from curve fitted to the surface pressure data. In addition, spanwise correlations and power spectra analyses were employed to study the spatial structure of flow. Results at different spanwise locations show that the transition into single-bubble and two-bubble regimes could occur at marginally different Reynolds numbers which expresses the presence of overlap regions in between the single-bubble regime and its former and later regimes. This indicates the existence of three-dimensional flow around the circular cylinder in cross-flow, which is also supported by the observed cell-like surface pressure patterns. Relatively strong spanwise correlation of the flow characteristics is observed before each transition within the critical regime, or formation of first and second separation-bubbles. It is also noted that these organized flow structures might lead to greater overall aerodynamic forces on a circular cylinder in cross-flow within the critical Reynolds number regime.

• 대한기계학회논문집B
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• 제31권4호
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• pp.357-366
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• 2007

The present study investigated local heat/mass transfer characteristics on the surface of the rotating turbine blade with various incidence angles. The experiments are conducted in a low speed annular cascade with a single stage turbine. The blade has a flat tip with the mean tip clearance of 2.5% of the blade chord. A naphthalene sublimation method is used to measure detailed mass transfer coefficient on the blade. At design condition, the inlet Reynolds number is $Re_c=1.5{\times}10^5$ which results in the blade rotation speed of 255.8 rpm. Also, the effect of off-design condition is examined with various incidence angles between $-15^{\circ}$ and $+7{\circ}$. The results indicated that the incidence angle has significant effects on the blade surface heat transfer. In mid-span region, the laminar separation region on the pressure side is reduced and the laminar flow region on the suction side shrinks with increasing incidence angle. Near the tip, the effect of tip leakage flow increases in span wise and axial directions as the incidence angle decreases because the tip leakage flow is formed near the suction side surface. However, the effect of tip leakage flow is reduced with positive incidence angle.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 1998년도 유체기계 연구개발 발표회 논문집
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• pp.70-77
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• 1998

The rise in pressure across the impeller blade of an axial flow fan depends on the angle of attack. At a low back pressure, the air volume will be large and the angle of attack is small. The gradual increase of the back pressure approached stall zone which is not stationary but travels blade to blade passage. In consequence, a region occurs around these blades with large vibration in the flow. To avoid these stall operation, the stall detector in the axial flow fans has been designed to detect stalling condition with a manometer or differential pressure switch by electric mechanism.