• 한국유체기계학회 논문집
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• 제10권3호
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• pp.17-24
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• 2007

This paper presents the design procedure of a vertical wind turbine named jet-wheel-turbo turbine and the numerical and experimental verifications. The design parameters such as the rotor inlet angle, the diameter-to-hub ratio, the inlet guide outlet angle and the solidity were optimized to maximize the energy transfer, and to further increase the turbine efficiency by applying the side guide vane and the side opening to the rotor. The maximum power coefficient of 0.59, which is much higher than the ever-designed three-bladed horizontal turbines, was experimentally obtained when the optimal inlet- and side-guide vanes were installed and both sides of the rotor were 80% opened. The maximum power coefficients occur at the tip speed ratio ranging between 0.6 and 0.7. This vertical-axis turbine model can be applied to the large-scale power generation system with the speed and torque control algorithm for the specified wind characteristics.

• Journal of Mechanical Science and Technology
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• 제19권7호
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• pp.1478-1487
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• 2005

A small mixed-type turbine with a diameter of 19.9 mm has been substituted for a rotational part of pencil-type air tool. Usually, a vane-type rotor is applied to the rotational part of the air tool. However, the vane-type rotor has some problems, such as friction, abrasion, and necessity of accurate assembly etc.,. These problems make the life time of the vane-type air tool short, but air tools operated by mixed-type turbines are free of friction and abrasion because the turbine rotor dose not contact with the casing. Moreover, it is assembled easily because of no axis offset. These characteristics are merits for using air tools, but loss of power is inevitable on a non-contacting type rotor due to flow loss, tip clearance loss, and profile loss etc.,. In this study, four different rotors are tested, and their characteristics are investigated by measuring the specific output power. Additionally, optimum nozzle location against the rotor is studied. Output powers are obtained through measured pressure, temperature, torque, rotational speed, and flow rate. The experimental results obtained with four different rotors show that the rotor blade shape greatly influences to the performance, and the optimum nozzle location exists near the mid span of the rotor.

• 한국정밀공학회지
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• 제27권12호
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• pp.107-112
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• 2010

A gas turbine consists of an upstream compressor and a downstream turbine with a combustion chamber, and also the compressor and the turbine are generally coupled using a single shaft. Large scale gas turbine compressor is designed as multi-stage axial flow and the blade is fan-type which is thick and wide. Recently radial cracking happens occasionally at the compressor blade tip of large scale gas turbine. So, FEM was performed on the compressor blade and vibration modes and dynamic stresses were analyzed. According to the analysis, 9th natural frequency mode of the blade, which is 2 strip mode, is near the vane passing frequency by the vane located at the upstream of the blade.

• 한국윤활학회:학술대회논문집
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• 한국윤활학회 1994년도 제20회 학술대회
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• pp.49-53
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• 1994

베인형 펌프, 모터 등의 마찰, 마모특성에 관해서 많은 연구가 있었으나, 베인펌프는 구조로부터의 제약이 많기 때문에, 대용량, 고압, 고속화라는 일련의 요구를 만족시키는 것이 쉽지 않아, 그 요구에 부응하기 위해 지금까지의 연구가 내마모성 작동유, 표면처리 기술, 특수 베인기구등의 개발을 제약에 부딪칠 때마다 필요에 따라 한결같이 경험적으로 이루어졌으며, 측정에 대한 면에서도 동적 조건 하에서의 측정은 거의 없으며, 해석에 관해서도 일반성이 상당히 결여된 상태라 할 수 있다. 따라서 본 연구에서는 유압 베인펌프의 베인과 캠링간의 접동 모델로써 동적 마찰 실험장치를 제작하여, 베인 선단의 마찰력을 측정하고 이를 기초로 하여 실기 유압 베인펌프의 베인과 켐링내면간의 접동부에 관한 마찰특성을 추정하는 것을 목적으로 하였다.

• 대한기계학회논문집B
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• 제41권1호
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• pp.53-62
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• 2017

이중냉각 환형핵연료 집합체를 위한 비틀림 혼합날개 지지격자의 강제대류열전달 성능을 실험적으로 평가하였다. 비틀림 혼합날개 지지격자는 부수로 간 혼합뿐 아니라 부수로 내 혼합을 동시에 증대시킬 수 있도록 설계되었다. 실험을 위한 이중냉각 환형핵연료 모의 집합체로, 봉 중심 간 거리와 봉 외경의 비가 1.08인 봉 간격이 좁은 $4{\times}4$ 정사각 배열의 봉다발을 준비하였다. 실험은 봉다발 유동의 축방향 평균속도가 1.5 m/s, 열유속은 $26kW/m^2$인 조건에서 수행하였다. 원주방향 온도 분포의 경우, 지지격자 상류에서는 부수로 중심 벽면에서, 하류에서는 비틀림 혼합날개 끝이 향하는 벽면에서 온도가 가장 낮게 나타났다. 축방향 온도 분포의 경우, 지지격자 하류 근처에서 온도가 급격하게 감소하는 것으로 측정되었고, 비틀림 혼합날개에 의해 누셀트 수는 최대 56 % 증대되는 것으로 나타났다. 본 실험결과를 토대로 봉 간격이 좁은 이중냉각 환형핵연료 집합체에서 비틀림 혼합날개 지지격자에 의해 강제대류열 전달 성능이 효과적으로 증대될 수 있음을 확인하였다.

• International Journal of Aeronautical and Space Sciences
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• 제4권1호
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• pp.88-98
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• 2003

Compared to the noise limits (CAN7) specified in ICAO Annex 16 for civil helicopters, the Lynx helicopter equipped with BERP blades has only 0.2 EPNdB margin in the approach case although it has more than 4 EPNdB margin in fly-over and take-off conditions. The objectives of the study described in this paper were to devise a low noise main rotor blade for the Lynx using UEAF combined with the high resolution airload model ACROT. A design requirement is that the new blade, KBERP (Korean BERP) blade should achieve a significant reduction in noise during approach(at least 6EPNdB margin) without any noise penalty in fly-over and take-off conditions and minimal performance penalty. It was decided to investigate a tip modification to the BERP blade, employing the twin vortex concept to reduce the BVI noise and to retain the excellent high speed performance characteristics of BERP. Through the parametric study, the KBERP blade with optimized twin vortices has at least a 9 EPNdB noise margin in approach flight condition with only a small penalty in fly-over and take-off conditions. The KBERP tip is thus a very cost effective wav to reduce BVI noise during approach.

• 한국유체기계학회 논문집
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• 제8권4호
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• pp.27-38
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• 2005

The present study investigated the effect of relative position of the blade on blade surface heat transfer. The experiments were conducted in a low speed wind tunnel with a stationary annular turbine cascade. The test section has a single turbine stage composed of sixteen guide vanes and blades. The chord length of the blade is 150 mm and the mean tip clearance of the blade is $2.5\%$ of the blade chord. The Reynolds number based on blade inlet velocity and chord length is $1.5{\times}105$ and mean turbulence intensity is about $3\%$. To investigate the effect of relative position of blade, the blade at six different positions in a pitch was examined. For the detailed mass transfer measurements, a naphthalene sublimation technique was used. In general, complex heat transfer characteristics are observed on the blade surface due to various flow characteristics, such as a laminar flow separation, relaminarization, flow acceleration, transition to turbulence and tip leakage vortices. The results show that the blade relative position affects those heat transfer characteristics because the distributions of incoming flow velocity and turbulence intensity are changed. Especially, the heat transfer pattern on the near-tip region is significantly affected by the relative position of the blade because the effect of tip leakage vortex is strongly dependent on the blade position. On the pressure side, the effect of blade position is not so significant as on the suction side surface although the position and the size of the separation bubble are changed.

• 동력기계공학회지
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• 제21권2호
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• pp.48-56
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• 2017

The steady-state, incompressible and three-dimensional numerical analysis was carried out to evaluate the velocity fields around the seabed tiller used for the improvement of the seabed soil and the pulling force and buoyancy generated by driving the seabed tiller. The turbulence model used in this study is a realizable $k-{\varepsilon}$ well known to be excellent for predicting the performance of the flow separation and recirculation flow as well as the boundary layer with rotation and strong back pressure gradient. As a results, a typical vortex pair appears near the adjacent rotor vane tip. When the current is stopped, there is no force when pulling the seabed tiller, but when the current flows at 1.2 knots, the force acts on the downstream side and the pulling force is much greater. In stationary currents, the buoyancy of the seabed tiller acts more strongly towards the seabed as the number of rotations of the rotor increases, but acts more strongly toward the sea surface at 1.2 knots of current.

• 한국유체기계학회 논문집
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• 제15권6호
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• pp.58-63
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• 2012

This paper presents a numerical study on the performance improvement of axial-flow pump with guide vanes. Design optimization for guide vanes in an axial-flow pump has been studied through the implementation of a commercial CFD code and DOE (design of experiments). We also discussed how to improve the performance of the axial-flow pump by designing the guide vanes. Geometric design variables were defined by the meridional plane and vane plane development of guide vanes. The effect of hub tip ratio analyzed the meridional plane of guide vanes. The importance of the geometric design variables was analyzed using $2^k$ factorial designs. The objective functions for guide vane geometric variables were defined as the total efficiency and the total head at the design flow rate. From the $2^k$ factorial design results, the important design variables were found and the performance was increased in comparison with the base design model.

• 대한기계학회논문집B
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• 제41권3호
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• pp.161-169
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• 2017

터빈 블레이드의 내부냉각 설계 강화를 위해 설치된 경사요철과 가이드 베인에 대한 연구를 진행하였다. 채널의 입구로 들어오는 공기와 요철이 만나는 각도를 기준으로, 서로 상반된 두 가지 요철배열을 전연면과 후연면에 평행하게 배치하였다. 채널의 종횡비(AR)는 5:1이고, 요철의 각도는 $60^{\circ}$, 요철의 높이와 요철간 간격 비($e/D_h$)는 0.075이다. 레이놀즈 수는 10,000으로 고정하였다. 요철배열에 따른 2차 유동과 딘 와류의 상호작용이 곡관부와 전체 채널의 열전달 결과와 유동특성에 어떠한 영향을 미치는지 확인할 수 있었다. 결론적으로 첫 번째 유로의 요철배열이 팁 면의 열전달 분포에 지배적인 요인이며, 곡관부에서 유동의 분포에도 영향을 미쳤다. 또한 U자 형상 가이드 베인을 사용하였을 때 모든 요철에서 팁 면의 열전달 값이 상승하였으며, 특히 공기와 요철의 충돌각도가 양의각도일 때 가장 높은 냉각성능계수를 보였다.