• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.3
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• pp.53-64
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• 2018

In this study, computational simulation was performed to investigate the characteristics of air/fuel mixing according to the shape of the injector exit when the transverse jet was injected into a supersonic flow. Non-reacting flow simulation was conducted with fixed mass flow rate and the same cross-sectional area. To validate the results, free stream Mach number and jet-to-crossflow memetum ratio are set to 3.38 and 1.4, respectively, which is same as the experimental condition. Further, separation region, structure of the under-expended jet, jet penetration height, and flammable region of hydrogen for five different injectors compared.

• Transactions of the Korean hydrogen and new energy society
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• v.28 no.3
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• pp.308-314
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• 2017

Jet pump in automotive fuel tank module is used to deliver fuel to fuel pump so that the pump is operated without aeration in suction side. In this study, three dimensional simulation model of jet pump is developed to understand performance variation over design parameters. Performance of jet pump is also investigated experimentally in terms of operating pressures. The experimental data is used to verify the three dimensional simulation model of jet pump. Verification results show that the three dimensional simulation model of jet pump is about 1% error with experiment. The simulations are conducted in terms of throat ratio and primary flow induction angle. As the throat ratio is increased, the flux ratio is trade-off at 3 times of throat diameter. On the other hand, as primary flow induction angle is increased, vapor pressure inside the nozzle is decreased. In summary, the results show that liquid jet pump has to be optimized over design parameters. Additionally, high velocity of induced flow is able to evolve cavitation phenomena inside the jet pump.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.453-456
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• 2011

An experimental investigation of the heat transfer characteristics of stretched premixed flames using Synthetic gas has been performed. Hydrogen and carbon mon-oxide which could be extracted from coal gasification process are the main fuel of synthetic-gas. Heat flux at the stagnation point was increased as global strainrate was increased, then the heat flux was decreased when a global strainrate reached a sudden point. Heat flux at the stagnation point is also affected by nozzle to impingement distance. Heat flux was increased as nozzle to impingement place distance was increased. This study is a foundation study of practical use of secondary gases from coals.

• 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.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.5
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• pp.71-78
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• 2002

Experiments have been performed using two-color PIV in hydrogen non-premixed flames with various conditions of coaxial air, which was classified into three cases with/without reaction. Mean velocity, turbulence intensity and Reynolds stress were analyzed using flow fields from PIV measurement First, the similarity of pure jet had a good agreement with previous results of other researchers. It was found that the decay of centerline velocity was proportional to $x^{-1}$ in coaxial air conditions. By normalizing axial distance with effective jet diameter defined by effective density, the data of centerline velocity collapsed a single line. And the radial profiles of mean velocity showed that they didn't become self-similar because the curves differed from each other as coaxial air velocity increased at fixed fuel velocity. Also, turbulence intensity became self-similar further downstream than mean velocity.

• Proceedings of the Korean Vacuum Society Conference
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• 2013.08a
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• pp.175-175
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• 2013

현재 치과에서 상용되는 치아미백법은 과산화수소와 레이저를 사용하여 의사가 직접 치료를 하고 있다 [1]. 단기간에 높은 미백효과를 얻기 위해, 고농도의 과산화수소를 이용하게 되는데, 이는 암 또는 심장병 등을 유발시키는 원인이 될수 있음으로 인체에 매우 유해하다 [3,4]. 우리는 식품의약품안정청에서 규제하고 있는, 카바마이드 퍼옥사이드(15%)를 사용하였다. 카마바이드 퍼옥사이드(15%), 수증기, 저온 대기압 플라즈마 제트를 사용하여 미백효과를 관찰하였다. 기체 유량은 1,000 sccm 이며, 공기와 질소를 사용하였다. 미백효과를 보기 위한 대상으로는 우치(牛齒)를 사용하였으며, 플라즈마를 처리하여 미백효과를 관찰하였다. 실험 대조시료군으로는 카바마이드 퍼옥사이드(15%)와 수증기(0.4%)를 첨가한 다음, 공기 플라즈마와 질소 플라즈마를 조사하여 비교해보았다. 수증기를 첨가한 이유는 활성산소의 농도를 높이기 위함이며, 탁월한 미백효과를 얻을 수 있다. 실험을 통하여 우치에 카바마이드 퍼옥사이드(15%)와 수증기(0.4%)를 처리한 경우 플라즈마의 미백효과가 탁월함을 보였다. 이때 CIE색좌표 ($L^*a^*b^*$)에서 명도도가 높아짐을 보았다. 미백효과에 대한 측정은 측색분광기(cm-3500d)를 이용하였다. 라만은 빛이 어떤 매질을 통과할 때 빛의 파장을 변화시켜 빛의 일부는 진행방향에서 이탈해 다른방향으로지행하는 현상을 산란이라고 한다. 이를 이용하여 빛의 파장을 변화시키는 현상을 라만산란이라고 한다. 이것을 이용하여 같은 우치의 표면을 플라즈마 처리 전 후를 라만을 통해 측정하였다. 대기압 저온 플라즈마에서 발생되는 ROS는 미백효과에 큰 영향을 미친다. 모든 실험의 플라즈마 처리시간은 최대 20분까지로 하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.15-15
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• 1998

마하 수 6 이상인 극초음속 비행에는 스크램제트(SCRamjet : Supersonic Combustion Ramjet) 엔진이 가장 적합한 엔진으로 알려져 있고 현재 미국을 중심으로 이 엔진의 개발에 많은 노력을 기울이고 있다. 스크램제트 엔진의 성공적인 개발을 위해서는 초음속 공기 내에서 연료의 분사를 통한 가장 효율적인 연소를 유도할 수 있어야 한다. 초음속 상태의 공기와 연료의 혼합을 증대시키고 연소안정성을 향상시키는 방법으로 연소기 내에 인위적으로 경사충격파를 발생시키는 방안이 Marble 등에 의해 최초로 도입되었다. 본 연구에서는 스크램제트엔진 내의 연소기를 모델링하여 마하수 2.5의 초음속공기 유동 중앙에 수소 제트를 분사하여 초음속 수소-공기 화염을 만들고 연소기의 측면에 동일한 모양과 크기의 쐐기를 각각 부착시켜 평면 경사충격파를 발생시켰다 본 실험은 충격파가 초음속 화염에 미치는 영향을 연구한 최초의 실험연구이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.5
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• pp.333-338
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• 2022

The single jet of decane/methylcyclohexane mixed fuel that is surrogate for kerosene was injected into supercritical environment and visualized using shadowgraph technique. The injection pressure drop of the fuel jet of T_r = 0.484 was kept constant at 0.5 MPa and the experiment was conducted above the critical point of the mixed fuel, and the reduced temperatures of the chamber was changed from 1.00 to 1.23, and the reduced pressures was 1.00 and 1.38. As an index for reducing the density of jets sprayed into the supercritical environment, the brightness intensity of the post-processed jet image was observed with the internal temperature and pressure of the chamber. It was confirmed that the decrease in the brightness intensity of the jet when the temperature inside the chamber increased, and when the pressure inside the chamber was higher at the same temperature, the decrease in the brightness intensity of the jet was delayed. When the pressure inside the chamber is high, it is thought that the change in brightness intensity is delayed due to the increase in the pseudo-critical temperature of the fuel and the increase in the temperature required to reduce the density of the fuel jet.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.4
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• pp.53-58
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• 2021

Based on surrogate model, a hydrocarbon mixture was analyzed by visualizing the impinging break up mechanism in subcritical and supercritical conditions. Decane and methylcyclohexane with different critical pressures and temperatures were selected as experimental fluids. The impinging injector was installed inside the chamber, and the spray was visualized through a speed camera in subcritical and supercritical conditions. The injection condition of the mixture and chamber was kept constant at Pr(P/P_c) = 1, and Tr(T/T_c) was increased from 0.48 to 1.02. As Tr increased, the spray angle increased, and the sheet length decreased as the properties of the mixture reached each critical point. In addition, when the mixture approached the near critical point, it was shown that the change in density gradient was largely observed out of the impinging break up mechanism.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.325-329
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• 2017

In this study, the combustion experiment of hydrocarbon-kerosene fueled dual mode ramjet combustor was performed at mach number 3.5~6.0 conditions. Through the experiment, the temperature and the pressure distribution inside the combustion chamber were measured and the combustion characteristics inside the combustion chamber were investigated. In the mach number 3.5~5.0 range, it was able to identify subsonic combustion in the downstream combustion chamber. In the mach number 6.0 condition, the injected fuel from the injectors was naturally fired, and it was possible to confirm that supersonic combustion was successful in the upper chamber.