• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.6
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• pp.468-476
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• 2016

In this study, the conic winglet which is made by rotating wing tip airfoil by each 3 axis is applied to the dual type combined fan to reduce the wing tip leakage loss. Computational Fluid Dynamics is used to calculate the loss and optimum technique is used to get minimum loss. Optimization results shows that total pressure loss coefficient was reduced by 3.4 %, and optimization model was a bended shape at the end of wing forward to pressure side.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.1
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• pp.69-75
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• 2009

This paper studies the aerodynamic performance that the vent mixer-new conceptual supersonic mixer-showed with its geometric characteristics. The hole is 2 mm with 2 mm's distance from the wall in case 1 and with no distance in case 2. In case 3 die hole is 1 mm. Case 1 and case 2 showed the same total pressure recovery ratio, of which the case 3 was lower than that. While cases 1-3 had the same reattachment length, the shear layer was thicker in cases 1 and 2 than in case 3. Within the recirculation zone, cases 1 and 2 had lower pressure loss and higher velocity gradient difference than case 3-they enhance mixing between air and fuel. Separation bubble which is developed by the inflow into the recirculation zone has a significant effect on the total pressure recovery ratio in the combustor. Also separation bubble influences pressure distributions and recirculation flows in the recirculation zone. Therefore, inflow rate of air into the recirculation zone mainly affects the performance of vent mixer.

• Journal of Aerospace System Engineering
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• v.12 no.4
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• pp.81-89
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• 2018

In the present study, a numerical investigation was conducted to analyze the effect of the distance between the adjacent injectors on the characteristics of flow structure, fuel penetration, and air/fuel mixing. Numerical results were validated with experimental data using a single injection. Subsequently, the same injector geometry and properties were applied on a non-reacting flow simulation with multiple injectors. Total pressure loss, penetration height, and mixing efficiency were compared with the distance between the injectors. The results showed that each injected gas merged into a single stream, resulting in the 2D-like flow fields under the condition of short distance and lower mixing efficiency along with higher total pressure loss. When the distance between the injectors increased, total pressure loss reduced and mixing efficiency increased due to the weakening of interactions between the injected gases.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.2
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• pp.33-39
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• 2008

To improve the mixing efficiency and to reduce the pressure loss, it is needed to develope a new mixing device for supersonic combustion. The vent mixer is introduced as the new supersonic fuel-air mixer. Computational analyses, that include pressure profile, density contour, and streamline tracing, have been carried out. The expansion wave generates at the end of the extended upper wall of the mixer. And it reduces the shock wave from the hole. Incoming air flow through the hole makes several recirculation regions which increase the mixing efficiency, and the separation region at the downward wall expends the boundary layer which reduces the pressure loss.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.6
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• pp.29-35
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• 2021

Bell mouth inlet is applied in various industries due to the advantage of little pressure loss and accurate flow measurement. In this study, the configuration of the bell mouth intake is designed in a long radius shape, and a suitable grid size was selected to minimize the pressure drop and to prevent the engine damage by foreign objects at outdoor operating conditions. It was able to present a modified pressure drop coefficient equation from two data obtained from the computational simulation and experimental results for the total pressure loss by inlet screen installation.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.282-283
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• 2011

전압이 정격전압을 유지하지 못하면 전기기기의 효율 저하, 수명단축, 손실증대를 야기 시킨다. 하지만 더 큰 문제는 예기치 못한 사고 및 급격한 부하 증가에 따라 전압이 떨어질 때 생길 수 있는 전압붕괴 현상이다. 전압 붕괴 현상은 대규모로 퍼져 대정전 사태를 초래 할 수 있다. 전압안정도를 유지하고 향상시키기 위해 적절한 무효전력의 공급 및 무효전력 예비력 확보는 매우 중요하다. 무효전력 공급을 위한 설비에는 병렬 커패시터, 발전기 등이 있다. 하지만 병렬 커패시터 등 조상설비는 이미 설치되어 있는 양만큼만 출력을 낼 수 있고 사고 등의 급격한 계통변화에 빠르게 대응 할 수 없다. 즉, 사고나 급격한 부하 증가에 효율적으로 대응하기 위한 수단으로 발전기 순동 무효 예비력의 확보가 필수적이다. 하지만 무효전력은 지역적 특성을 띄고 있다. 그렇기 때문에 예비력의 확보와 더불어 지역적 특성을 반영해야만 하다. 본 논문에서는 발전기 무효전력 예비력 관점에서 무효전력의 지역적 특성을 고려 국내지역별 발전기 무효전력 예비력 산정을 위한 발전기 선정을 목표로 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.1
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• pp.48-55
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• 2010

The purpose of this paper was to address the methodology of the air flow measurement using duct mach number that was considered area-weighed average obtained by total, static pressure and temperature measured at engine inlet duct. Without installing boundary rake, the prediction of air flow measurement was discussed. Actual air flow measurement and pressure value using pressure loss through inlet seal were described to improve the reliability and operability of altitude engine test facility.

• Proceedings of the KIEE Conference
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• 2007.07a
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• pp.939-940
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• 2007

다수본의 Bi-2223테이프로 구성되는 초전도전력케이블에서 발생되는 교류손실은 케이블의 효율을 저하시킬 뿐만 아니라 냉동기비용 증가로 인한 기존 케이블과의 가격경쟁에서 경제성을 저하시키는 주된 요인으로 작용하기 때문에 이의 상용화에 앞서 교류손실에 대한 정확한 규명이 되어야 한다. 그러나 다수본으로 구성되는 고온초전도전력케이블의 교류손실을 올바르게 평가하는 것은 테이프의 상이한 임계전류, 전압리드의 배열, 전류분포의 불균일성 및 인접한 테이프에 흐르는 전류위상 상이 등 복잡한 영향인자 때문에 매우 난해하다. 이와 같은 교류손실 평가와 관련된 복잡한 문제들을 규명하기 위해 다수본의 고온초전도도체 샘플을 제작하였으며 그 손실 특성을 실험적으로 조사 및 검토 하였다. 그 결과 다수본 고온초전도도체의 측정된 교류손실은 Monoblock모델 이론값 및 다각형모델에 근거한 수치해석 결과와도 상이함을 알 수 있다.

• Electric Engineers Magazine
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• v.219 no.11
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• pp.42-54
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• 2000

얼마전 언론에 보도된 바에 의하면 반도체 공장들의 순간전압저하로 인한 피해가 몇백억원이 될 정도로 극심하다고 한다. 그러나 이것은 빙산의 일각에 불과하며 순가전압저하에 의한 불량제품의 양산과 그에 따른 국가 경쟁력 저하, 생산기기의 정지와 재기동에 따른 인적, 경제적 손실 등을 고려하면 그 피해액은 엄청나게 불어날 것이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.5
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• pp.297-308
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• 2022

Most air-breathing aircraft operated in the hypersonic region are equipped with a scramjet engine. In a scramjet engine, a shock wave generated at an inlet acts as a compressor for a general gas turbine engine instead, so total pressure loss caused by the shock wave is considered very important. In this study, to minimize total pressure loss, a method of designing an external compression inlet using isentropic compression surface was proposed, and an external compression inlet with 3-deflection angles and Busemann inlet were designed under the same conditions. After that, through computational analysis, the performance characteristics at off-design conditions were compared. Each inlet shape was truncated according to the length of the 3-ramp external compression inlet, and the boundary layer correction was performed. The isentropic external compression inlet showed superior performance at the design point, but under the off-design conditions, its performance was degraded compared to the 3-ramp external compression inlet.