• Proceedings of the KIEE Conference
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• summer
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• pp.1510-1512
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• 2004

본 연구는 농형 유도 발전기와 양방향 PWM 인버터를 가진 WECS (Wind Energy Conversion System)시스템을 모델링하고 이 모델에 기초하여 제어 법칙을 제안하였다. 제어 법칙은 풍속 따라 작용하는 최적 팁 속도비에 의해 효율이 최대가 되도록 제어하는 것이다. WECS은 바람의 변동이 있어도 최적치에 팁 속도비를 유지하기 위해 터빈의 회전 속도 제어하여 행한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.305-310
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• 2007

For the understanding of the complex flow characteristics in the counter-rotating axial flow fan, it is necessary to investigate the three-dimensional unsteady flow fields in the counter-rotating axial flow fan. This information is also essential for the prediction of the aerodynamic and acoustical characteristics of the counter-rotating axial flow fan. Experimental study on the three-dimensional unsteady flow in the counter-rotating axial flow fan is carried out at the design point(operating condition). Three-dimensional unsteady flow fields in the counter rotating axial flow fan are measured at the cross-sectional planes of the upstream and downstream of each rotor using the $45^{\circ}$ inclined hot-wire. Three-dimensional unsteady flow fields in the counter-rotating axial flow such as the wake, the tip vortex and the tip leakage flow are shown the form of the velocity vectors and the velocity contours.

• 한국전산유체공학회:학술대회논문집
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• 2008.03b
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• pp.240-243
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• 2008

In this paper, the design of Centrifugal Compressor which is used in sizes 50 horse power has 8 pressure ratio and numerical analysis of the flow within compressor varying tip clearance length are performed. To get high pressure ratio with low power the exit height of impellers is low but compressor has very high speed of revolution. So compressor has high specific speed although mass flow rate is very small. The shape of impellers at the first stage is carried out. Flow and performance characteristics of impellers has been analyzed by using a commercial CFD program, $Fine^{TM}$/turbo. The result shows that loss coefficient is affected by tip clearance length and compressor has proper tip clearance length. It is possible to decrease loss by selecting apt tip clearance length.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.387-391
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• 2009

The experimental study on the ducted fan for the propulsion system of a small UAV has been performed. In this paper, to investigate the three-dimensional unsteady flow field characteristics of the ducted fan, it was measured by using a $45^{\circ}$ inclined hot-wire from hub to tip at inlet, behind the rotor and outlet of the ducted fan. The hot-wire signal data was acquired at fixed yaw angle. The data was averaged by using the PLEAT (Phase Locked Ensemble Averaging Technique), and then three of non-linear equations were solved simultaneously by using the Newton-Rhapson numerical method. Flow characteristics such as tip vortex, secondary flow and tip leakage flow were confirmed through axial, radial and tangential contour plot.

• Proceedings of the Computational Structural Engineering Institute Conference
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• 2011.04a
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• pp.561-564
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• 2011

다양한 공학/산업적 측면에서 동적 취성 파괴 현상은 매우 중요하다. 취성 균열은 다른 균열 전파에 비해 그 전파 속도가 매우 빠르고 전파 범위가 넓기 때문에 대규모의 파괴 현상을 일으킨다. 동적 전파 중인 취성 균열 거동을 모델화하기 위해 오랜 기간 동안 많은 연구가 진행되었지만, 여전히 많은 부분들이 해석되지 못한 채 남아있다. 특히 균열 생성 및 전파를 위해 인위적인 조건들을 도입해야 하는 것은 기존 방법론들이 가지는 공통적인 문제점이다. 본 연구는 peridynamics를 동적 분기 균열 문제 해석에 도입한다. Peridynamics는 전통적인 연속체 이론에 기반한 수치해석 모델화 기법으로 균열과 같은 비연속성이 있는 문제의 모델화에 강점이 있으며, 인위적인 조건 없이 매우 간단한 방법으로 파괴 현상을 해석할 수 있다. 본 연구에서는 peridynamics 모델이 실험적으로 관측된 분기균열 형상과 균열 전파 속도를 매우 잘 예측해 낼 수 있음을 보인다. 또한 균열팁 주변에 높은 응력이 발생할 때 나타나는 연쇄 분기 현상도 해석할 수 있다. 이와 같은 연구를 통해 응력파가 균열 전파 속도를 변화시키고 전파 방향에도 영향을 주는 것을 알 수 있었다. 수치해석 결과도 또한 실험 결과들과 잘 부합함을 확인하였다.

• Journal of the Korean Solar Energy Society
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• v.29 no.5
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• pp.73-80
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• 2009

A tidal current turbine is designed and analyzed numerically by using blade element momentum theory. The rated power has a limitation because the diameter of the tidal current turbine cannot exceed the depth of sea water. This study investigates a horizontal axis tidal-current turbine with a rated power of 500 kW. NACA-6 series laminar foil shape is used for basic airfoil along the blade span. The distributions of chord length and twist angle along the blade span are obtained from the hydrodynamic optimization procedure. Prandtl's tip loss correction and angle of attack correction considering the three-dimensional effect are applied for this study. The power coefficient curve shows maximum peak at the rated tip speed ratio of 6.0, and the maximum torque coefficient is developed at the tip speed ratio of 4. The drag coefficient reaches about 0.85 at the design tip speed ratio.

• Proceedings of the Korean Vacuum Society Conference
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• 1999.07a
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• pp.126-126
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• 1999

본 실험의 목적은 FED의 상부, 하부 전극으로 사용되는 Mo를 건식, 습식 식각함으로써 DED 소자의 공정을 개발하는 것이다. Mo는 $261^{\circ}C$의 높은 융점을 지니고 있으며, 우수한 열적 안정성과 비교적 낮은 비저항을 가지는 재료로써 FED와 같은 전계 방출 소자의 cathod 팁 및 전극물질로 사용되어지는 가장 보편적인 물질이다. FED와 같은 전계방출소자가 갖추어야 할 요건은 전자 방출 영역이 소자 동작시 변형되지 않아야 하고, 기계적 ,화학적, 열적 내구성이 좋아야 함인데 이러한 요건을 충족시킬 수 있고 가장 범용적으로 사용되는 물질이 Mo이다. 실험에서 사용된 Mo는 DC magnetron sputter를 사용하여 Ar 가스를 첨가하여 5mTorr하에서 Si 기판위에 증착속도를 300$\AA$/min로 하여 1.6$\mu\textrm{m}$ 증착하였다. 본 실험의 Mo 식각은 고밀도 플라즈마원인 ICP를 이용하였다. 식각특성은 식각 가스조합, inductive power, bias voltage, 공정 압력의 다양한 공정 변수에 따른 식각특성 변화를 관찰하였다. 식각시 chlorine 가스를 주요 식각 가스로 사용하고 BCl3, O2, Ar을 첨가가스로 사용하였으며, inductive power는 300-600, bias voltage는 120-200V 사용하였고 압력은 15-30mTorr, 기판온도는 7$0^{\circ}C$로 유지하였으며 식각마스크로는 electron-beam evaporator로 1$\mu\textrm{m}$ 증착한 SiO2를 patterning하여 사용하였다. 식각속도는 stylus profiler를 이용하여 측정하였으며 식각후 profile은 scanning electron microscopy (SEM)을 통하여 관찰하였다. 실험 결과 순수한 Cl2 BCl3 가스만을 사용한 경우 보다는 Cl2 가스에 O2를 첨가하였을 때 좋은 선택비를 얻었다. 또한, inductive power와 bias voltage, Mo의 식각속도의 적절한 조절을 통해 SiO2에 대한 선택도를 변화시킬 수 있었다. Cl2:O2비를 1:1로 하고 400W/-150V, 20mTorr의 압력, 7$0^{\circ}C$ 기판온도에서 식각시 200$\AA$/min의 Mo 식각속도, SiO2와의 선택비 8:1을 얻을 수 있었다. 또한 실제 FED 소자 구조형성에 적용한 결과 비등방적인 식각형상을 형성할 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.6
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• pp.92-99
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• 2005

Numerical analyses of critical speed and mass unbalance response are performed for a 30 ton thrust turbopump. The stiffness and damping of ball bearings and non-contact seals are quantified under aerodynamic and hydrodynamic loads induced by a fuel pump and turbine. Critical speed margin and tip displacements of the rotating parts are evaluated using a three-dimensional finite element method. The results are used to ensure the soundness of the rotordynamic design using an one-dimensional transfer matrix method. A further study shows that sufficient resonance margin may be assured via controlling the stiffness of the rotor support by employing an additional elastic ring to the bearing support.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.6
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• pp.56-63
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• 2018

In low swirl combustors the flame is lifted above the nozzle to achieve balance between the flame speed and velocity field at the exit of the nozzle. Characterization of the flame liftoff height is important because it affects the stability of the combustor and degradation of the nozzle material. In experiments, a counter-intuitive trend of flame liftoff heights with respect to inlet velocities was observed. To elucidate the complicated flow field in a low swirl combustor having swirl vanes and a turbulence generator, a series of numerical simulations of non-reacting flows was conducted by varying the inlet velocity. The flow structures at the exit of the nozzle with respect to the inlet velocities are investigated to support the observation in the experiments.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.10
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• pp.891-898
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• 2007

Optimal aerodynamic design for the pitch-controlled horizontal axis wind turbine and its aerodynamic performance for various pitch angles are performed numerically by using the blade element momentum theory. The numerical calculation includes effects such as Prandtl‘s tip loss, airfoil distribution, and wake rotation. Six different airfoils are distributed along the blade span, and the special airfoil i.e. airfoil of 40% thickness ratio is adopted at the hub side to have structural integrity. The nonlinear chord obtained from the optimal design procedure is linearized to decrease the weight and to increase the productivity with very little change of the aerodynamic performance. From the comparisons of the power, thrust, and torque coefficients with corresponding values of different pitch angles, the aerodynamic performance shows delicate changes for just $3^{\circ}$ increase or decrease of the pitch angle. For precisive pitch control, it requires the pitch control algorithm and its drive mechanism below $3^{\circ}$ increment of pitch angle. The maximum torque is generated when the speed ratio is smaller than the designed one.