• Transactions of the Korean Society of Mechanical Engineers B
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• v.39 no.2
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• pp.153-159
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• 2015

In this study, a 2-W micro-gas turbine engine was designed using micro-electro-mechanical systems (MEMS) technology, and analytical and experimental investigations of its potential under actual combustion conditions were performed. An ultra-micro-gas turbine contains a turbo-charger, combustor, and generator. A compressor, turbine blade, and generator coil were manufactured using MEMS technology. The shaft was supported by a precision computer numerical control machined air bearing, and a permanent magnet was attached to the end of the shaft for generation. An analysis found that the cooling effect of the air bearing and compressor was sufficient to cover the combustor heat, which was verified in an actual experiment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.56-63
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• 2004

In this study, dynamic aeroelastic analyses of the canard with oscillating flap are conducted considering the effect of aerodynamic compressibility. The canard model considered herein is an all-movable type with a pitching axis on a canard-rotor-wing aircraft which was considered as one of the major UAV candidates under developing in Korea. The equivalent structural model is constructed based on the initial design data by the Korea smart UAV development center. Both the frequency and the time-domain aeroelastic analyses have been applied to practically conduct parametric studies on the effects of equivalent torsional stiffness. In the case of all-movable control surface with oscillating flap, the equivalent rotational stiffness of the pitch axes are important design parameters. The parametric results for the aeroelastic instability are practically presented.

• Journal of the Korean Geotechnical Society
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• v.29 no.6
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• pp.77-86
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• 2013

Embankments on soft ground experience significant deformation during time-dependent consolidation settlement, as well as an initial undrained settlement. Since infinitesimal strain theory assumes no configuration change and minute strain during deformation, finite strain analysis is required for better prediction of geotechnical problems involving large strain and geometric change induced by imposed loadings. Updated Lagrangian formulation is developed for time-dependent consolidation combining both force equilibrium and mass conservation of fluid, and mechanical constitutive equation is written in Janumann stress rate. Numerical convergence during Newton's iteration in large deformation analysis is improved by Nagtegaal's approach of considering the effect of rotation in mechanical constitutive relationship. Numerical simulations are conducted to discuss numerical reliability and applicability of developed numerical code: deformation of cantilever beam, two-dimensional consolidation. The numerical results show that developed formulation can efficiently describe large deformation problems. Proposed formulation is expected to facilitate the upgrading of a numerical code based on infinitesimal strain theory to that based on finite strain analysis.

• Proceedings of the Korean Vacuum Society Conference
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• 2011.02a
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• pp.241-241
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• 2011

최근들어 저온플라즈마를 이용한 생물학적 응용분야가 각광을 받고 있다. 특히 전기전도도를 가진 전해질 내에서 형성된 액상 플라즈마는 열손상없이 암, 세균 및 비정상 장기조직의 제거가 가능하다는 점에서 기존 시술들이 가지는 문제를 해결할 수 있다. 허리통증을 유발하는 탈출 수핵을 대용량으로 제거하기위한 플라즈마발생 전극에 관한 연구가 수행되었다. 수핵 분해량을 늘리기 위해서는 플라즈마를 통하여 다량의 수산화기 라디컬을 형성, 수핵표면에 조사해야 한다. 이를 위하여 6개의 텅스텐 전극표면에서 기포를 발생시켜 플라즈마 발생면적을 넓힐 수 있었다. 텅스텐 전극들은 캡톤코딩과 세라믹 스페이서를 통하여 분리되었고, 전극의 후방에는 SUS 재질의 환형 접지전극을 배치하여 6개의 텅스텐 전극표면에서 모두 기포가 발생할 수 있도록 하였다. 시술적용시 플라즈마 및 전극이 가지는 제한 조건은 단백질 변성을 막기위한 섭씨 45도 이하의 온도 상승과 조직에 대한 기계적인 손상 방지를 위한 2.5 mm 이하의 전체 전극 굵기이다. 이를 만족하는 가운데 수산화기 라디컬 형성을 증대할 수 있는 전극의 구조를 결정하기 위하여 1-D 전기 열유체 모델 도입하였다. 모델에서 도출된 기포의 두께를 바탕으로 다중전극간의 거리 조절을 통하여 플라즈마 방전구조를 전극 - 전극 (기포두께${\times}2$ > 전극간 거리)과 전극 - 기포표면 (기포두께${\times}2$ < 전극간 거리)으로 통제하였다. 형성된 플라즈마의 소모전력, 전자 밀도및 수산화기 라디컬의 회전온도를 분석하기 위하여 0.9% 염화나트륨 수용액, 1.6 S/m, 전해질에서 플라즈마 형성를 형성하고 전기신호 및 광학신호를 관측하였다. 전극에 인가된 전압은 340 VRMS이며 운전주파수는 380 kHz이다. 실험 결과, 전극 - 기포표면 방전구조는 전극 -전극 방전구조에 비하여 전해질의 저항역할로 인하여 방전전류가 3.4 Ipp에서 1.6 Ipp로 감소하였으나, 기포표면에서의 물분자의 분해로 인하여 수산화기 라디컬에서의 발광세기는 약 4배 증가하였다. 또한 수산화기의 회전온도 분포상에서도 전극 - 기포표면 방전은 주변 물분자의 열교환으로 인하여 전극 -전극간 방전의 1500K 에 비하여 낮은 400K를 보였다. 이는 전극-기포표면 방전구조의 전극이 낮은 온도의 수산화기를 다량으로 형성할 수 있음을 시사하며, 카데바를 이용한 실험에서 220초에 걸쳐 약 87%의 수핵을 기계적 손상 및 단백질 변형없이 효과적으로 제거함을 확인하였다.

• Journal of Biomedical Engineering Research
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• v.10 no.2
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• pp.139-150
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• 1989

A new motor-driven blood pump for artificial heart was developed. In this blood pump, a small size, high torque brushless DC motor was used as an energy converter and the motor rolls back and forth on a circular track. This movement of the "rolling-cyliner" causes blood ejection by alternately pushing left or right polyurethane blood sacs. This moving-actuator mechanism could be eliminate two potential problems of other motor-driven artificial hearts such as large size and poor anastomosis for the implantation. Theoretical analyses on the pump efficiency, the temperature rise, and the inflow mechanism were also performed. In a series of mock circulation tests, the theoretical analyses were compared to the measured hemodynamic and mechanical values. The pump system was shown to have sufficient cardiac output (upto 9 L/min), sensitivity to preload, and mechanical stability to be tested as an implantable total artificial heart.ial heart.

• Journal of the Society of Naval Architects of Korea
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• v.50 no.5
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• pp.282-290
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• 2013

The effects of the combination of blade number for forward and after propeller on the propeller shaft forces of a contra-rotating propeller (CRP) system are presented in the paper. The research is performed through the numerical simulations based on the Reynolds-Averaged Navier-Stokes equations (RANS). The simulation results of the present method in open water condition are validated comparing with the experimental data as well as the other numerical simulation results based on the potential method for 4-0-4 CRP (3686+3687A) and 4-0-5 CRP (3686+3849) of DTNSRDC. Two sets of CRP are designed and simulated to study the effect of the combination of blade number in behind-hull condition. One set consists of 3-blade and 4-blade, while the other is 4-blade and 4-blade. A full hull body submerged under the free surface is modeled in the computational domain to simulate directly the wake field of the ship at the propeller plane. From the simulation results, the fluctuations of axial force and moment are dominant in the case of same blade numbers for forward and after propellers, whereas the fluctuations of horizontal and vertical forces and moments are very large in the case of different blade numbers.

• Journal of Aerospace System Engineering
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• v.11 no.5
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• pp.20-27
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• 2017

The present paper describes the flow analysis of the flows around the multicopter for the selection of optimal position of air data sensor. For the flow analysis, the commercial fluid dynamics solver, STAR-CCM+ was used with polygon mesh and k-w SST turbulence modeling options. For the simulation of each rotating 4 propellers, unstructured overset mesh method was used. Hovering, forward flight, ascending and descending flight conditions are selected for the analysis and airspeed and flow angle errors were investigated using the CFD results. Through the flow field analysis, sensor location above one propeller diameter distance from the propeller rotating plane showed airspeed error less than 1m/s within the typical flight conditions of multicopter except descending.

• Journal of Energy Engineering
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• v.24 no.1
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• pp.88-96
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• 2015

Gear pump has a simple structure high reliability, easy operation and maintenance, widely used as a source of hydraulic system of hydraulic. In general, the gear pump was designed using variety of variables, the variables through the analysis of the mass flow rate and efficiency. In this paper, three-dimensional flow of the gear pump, in order to produce the optimal design of product, analysis was performed by using commercial software ANSYS v15.0 CFX. And then, combination of design parameters selected by ANSYS was carried out to confirm the simulation result. The efficiency and mass flow rate of the gear pump were studied by varying its rotational speed and the clearance between the gear tip and the housing. In the simulation results, as the rotational speed were increased, the average mass flow rate and efficiency increased. Furthermore, as the clearance between the gear tip and the housing was increased, the average mass flow rate and efficiency decreased.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.38 no.12
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• pp.1027-1034
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• 2014

The shear stress on a surface due to the thin film fluid flow is an important issue. In case of a rotating disk, the fluid is delivered to the edge of the disk by centrifugal force, which acts as a body force on the fluid. Wear of a surface is affected by the shear stress acting on the surface and curvature. In this study, we utilize computational fluid dynamics software to model the ratio of curvature and local shear stress on solid surfaces. The key goal of the study is to determine an optimized curvature for the thin film fluid flow on a solid surface in order to minimize the local shear stress affecting the wear of this surface. Our results on the effects of curvature will be utilized for the design of devices that utilize thin film fluid flow on a solid surface, such as rotating-disk spray systems and thin film coating.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.2
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• pp.42-53
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• 2009

Gas turbine engine simulation program has been developed. In compressor and turbine, 2-D NS implicit code is used with k-$\omega$ SST turbulent model. In combustor, 0-D lumped method chemical equilibrium code is adopted under the limitations, the products are only 10 species of molecular and air-fuel is perfectly mixed state with 100% combustion efficiency at constant pressure. Fluid properties are shared on interfaces between engine components. The outlet conditions of compressor have been used as the inlet condition of combustor. The inlet condition of turbine comes from the compressor The back pressure in compressor outlet is transferred by the inlet pressure of turbine. Unsteady phenomena at rotor-stator in compressor and turbine is covered by mixing-plane method. The state of engine can be determined only by given inlet condition of compressor, outlet condition of turbine, equivalence ratio and rotating speed.