• Fire Science and Engineering
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• v.15 no.2
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• pp.91-95
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• 2001

Decays of the ceiling jet front velocity under a circular ceiling are investigated. To simulate the ceiling jet in fires He and $N_2$gas were injected from a nozzle to the center of the ceiling. The jet fronts in the form of turbulent eddies were traced by a high-speed camera system. The instantaneous locations of the front were obtained from visual readings of visualized front, and the radial velocity was calculated from the information of the time and the location with respect to the front. The similarity and dimensional analysis were also carried out to reveal the relationship between the velocity decay and the radial distance. It was shown that the radial velocity of the front was inversely proportional to the radial distance in the fully developed region from the experimental results and the theoretical analysis.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.1
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• pp.80-88
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• 2013

In currently developed engine condition monitoring systems, most field engine maintenance engineers have difficulties to use them in fields due to complexity, unpractical use, lack of understanding, etc. Therefore a practical usable engine condition monitoring system must be needed. This work proposes a practical performance condition monitoring of a small turbojet engine through comparing between the on-line performance monitoring data and the initial clean performance data calculated by the base engine performance model. Moreover the proposed monitoring system checks the gas path components' on-line health condition through comparing the component performance characteristics between the running engine represented as a deteriorated engine or a degraded engine and the base engine performance model represented as a clean engine. The proposed condition monitoring system is coded in a friendly GUI type program for easy practical application by a commercial tool, MATLAB/SIMULINK and LabVIEW.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.1
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• pp.18-25
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• 2001

The results of systematic numerical experiments of secondary gas injection thrust vector control are presented. The effects of secondary injection system such as injection location and nozzle divergent cone angle onto the overall performance parameters such as thrust ratio, specific impulse ratio and axial thrust augmentation, are investigated. Complex nozzle exhaust flows induced by the secondary jet penetration is numerically analyzed by solving unsteady three-dimensional Reynolds-averaged Navier-Stokes equations with Baldwin-Lomax turbulence model for closure. Numerical simulations compared with the experiments of secondary air injection into the rocket nozzle of $9.6^{\cire}$ divergent half angle showed good agreement. The results obtained in terms of overall performance parameters showed that locating the secondary injection orifice further downstream of primary nozzle ensures the prevention of occurrence of reflected shock wave, therefore is suitable for efficient and stable thrust vectoring over a wide range of use.

• Fire Science and Engineering
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• v.20 no.4 s.64
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• pp.58-64
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• 2006

Smoke extraction in tunnel fire is investigated experimently with thermal model. The object is a immersed tunnel, of which the partial extraction system exists between the tubes. The model tunnel is measured 12 m long, 0.5 m wide and 0.35 m high. The fire is simulated to pool fire and the size corresponds to full scale fire of 5 MW based on Froude modeling. The performance of partial extraction system is determined under two ventilations, natural and longitudinal ones. The results show that compared with longitudinal ventilation, the smoke extraction efficiency of natural ventilation is increased about 30% because of smoke stratification in tunnel. Also the efficiency is identical to the iso-thermal model. The results will be help for activation of the ventilation system in emergency such as in the event of tunnel fires.

• Proceedings of the Korean Institute of Surface Engineering Conference
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• 2018.06a
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• pp.39-39
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• 2018

최근 플라즈마 의학이 발달하면서 제트, 펜, 니들, 토치 등의 다양한 형태의 플라즈마 발생기가 개발되었으며 내부의 가스라인으로 가스의 종류, 유속, 조성 등을 조절하여 생물학적 효과를 극대화 할 수 있고 안정적으로 플라즈마 방전상태를 유지할 수 있으나 처리 면적이 좁아 실제 생물학적 시스템 (세포, 조직, 그리고 박테리아) 적용에 있어 한계점이 존재한다. 이러한 한계점을 극복하기 위해서 유전체격벽방전 (Dielectric barrier discharge, DBD) 방식을 이용한 플렉서블 활성종 발생기를 제작하고 생물학적 시스템에 적용하기 위한 방전 특성 평가를 진행하였으며, 간단한 in vitro 모델인 한천 젤을 이용하여 플라즈마 처리에 따른 전달물질의 침투거리를 확인하였다. 플라즈마 방전 시 생성되는 수산화기 [OH], 과산화수소 [$H_2O_2$], 초산소음이온 [$O_2{^-}$], 오존 [$O_3$], 그리고 산화질소 [$NO_x$]와 같은 산소 및 질소 활성종 (Reactive oxygen and nitrogen species, RONS)은 세포벽 또는 세포막의 주요 구성성분인 다당류와 인지질의 과산화 반응을 통해 구조를 변화시키고 생물학적 시스템의 표면의 pH를 낮춘다. 이러한 RONS의 작용은 살균, 소독 뿐만 아니라 약물의 침투를 돕는다. 일반적으로 한천 겔은 농도에 따라 생체 내 뇌 조직과 물리적 특성이 유사하고, 미생물학 기질, 방사선학 연구를 위한 조직모델로 사용되기 때문에 본 연구에서는 3%와 5% 농도의 한천 젤을 사용하여 침투거리를 확인하였다. 한천 젤은 $2.5{\times}2.5{\times}2.5cm^3$의 크기로 준비되었고 대조군으로 염료가 포함된 에멀젼을 0.01 g 도포하고, 실온에서 30분간 보존 후 단면을 잘라 현미경으로 침투거리를 확인하였으며, 실험군으로 플라즈마 전처리 후 에멀젼을 도포한 시표와 에멀젼 도포 후 플라즈마 처리한 시료에 대해 에멀젼 침투거리의 변화를 확인하였다. 본 연구의 플렉서블 활성종 발생기는 인체에 부착하여 사용되기 때문에 화상, 홍반을 유발을 방지하기위해 $40^{\circ}C$의 온도에서 실험을 진행하였고 이때에 플라즈마 방전조건은 $0.065W/cm^2$ 수준의 전력을 소모하는 1.7 kV의 전압, 16 kHz의 주파수로 10분간 처리하였다. 그 결과 3%의 한천 젤의 경우 침투거리 0.779 mm에서 0.826 mm, 0.942 mm까지 침투거리가 증가하였고 5%의 한천 젤의 경우 0.859 mm, 0.949 mm로 증가하였다. 이러한 침투거리 증가는 젤 표면의 다당류를 구성하고 있는 단량체가 플라즈마 처리시 화확적 구조가 끊어져 결론적으로 약물 침투가 증가된 것으로 판단된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.2
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• pp.150-158
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• 2018

Numerical simulation and experimental study on the thermal flow field of the micro turbojet engine have been carried out for the purpose of developing infrared reduction technology for aircraft. A circular basic nozzle and five rectangular nozzles with different aspect ratio were considered. The conditions for CFD analysis were derived from the analysis of the engine performance. The temperature distribution of the nozzle plume was measured using a temperature sensing system. The thrust of the rectangular nozzle with the aspect ratio 5 was reduced about 1.8% compared to the circular nozzle, and the thrust decreased with increasing the aspect ratio of the nozzle. In the case of thermal flow field, it was observed that, as the aspect ratio increases, the exhaust plume in the experiment was formed wider than in the CFD analysis.

• The Journal of the Convergence on Culture Technology
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• v.10 no.1
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• pp.551-557
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• 2024

Hydrogen is a renewable energy source with various characteristics such as clean, carbon-free and high-energy, and is internationally recognized as a "future energy". With the rapid development of the hydrogen energy industry, more hydrogen infrastructure is needed to meet the demand for hydrogen. However, hydrogen infrastructure accidents have been occurring frequently, hindering the development of the hydrogen industry. HyRAM+, developed by Sandia National Laboratories, is a software toolkit that integrates data and methods related to hydrogen safety assessments for various storage applications, including hydrogen refueling stations. HyRAM+'s physics mode simulates hydrogen leak results depending on the hydrogen refueling station components, graphing gas plume dispersion, jet frame temperature and trajectory, and radiative heat flux. In this paper, hydrogen leakage data was extracted from a hydrogen refueling station in Samcheok, Gangwon-do, using HyRAM+ software. A hydrogen leakage simulator was developed using data extracted from HyRAM+. It was implemented as a dashboard that shows the data generated by the simulator using a database and Grafana.