• Proceedings of the KSME Conference
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• 2003.11a
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• pp.604-609
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• 2003

Turbulent temperature field in a channel with wall injection has been investigated using dynamic mixed model(DMM). This flow is pertinent to internal flows inside the hybrid rocket motors. In general, the results obtained with DMM are in better agreement with DNS results compared to those of dynamic Smagorinsky model(DSM). Such favorable features of DMM are attributed to the fact that it explicitly calculates the modified Leonard stress term which takes care of the local interaction between resolved and SGS stresses and only models the remaining cross and SGS Reynolds stress terms.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.3
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• pp.8-14
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• 2003

A cooling performance analysis has been made in the 8-channel calorimeter based on sub-scale KSR-III engine. Three-dimensional heat transfer analysis in cooling channels has been performed using the heat flux distribution through the chamber wall predicted from axi-symmetric compressible flow inside the combustion chamber. The heat flux distribution is verified against the published literature. Presented for the development and operation of the calorimeter are the coolant pressure drop, coolant temperature rise and the maximum chamber wall temperature. Required coolant flow rate is determined for given chamber pressure. Cooling performance is also predicted for temperature dependant coolant properties.

• Solar Energy
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• v.13 no.1
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• pp.31-38
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• 1993

A numerical study of natural convection heat transfer confined by circular parallel walls at different temperatures and flat adiabatic walls is investigated for Rayleigh numbers from $10^3$ to $10^5$and sectorial angles from $30^{\circ}$ to $180^{\circ}$. It is used by a finite difference method to solve the governing equations. The results show velocity and temperature distributions. Mean Nusselt numbers are shown by $\overline{Nu}=C(Ra_L)^m$.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.12
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• pp.90-95
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• 2006

The wall of thermal vacuum chamber which is used for the satellite thermal balance test doesn't absorb satellite's IR emission perfectly and reflects some part of that. It is estimated that small thermal vacuum chamber has relatively larger wall effect than the big one. The small thermal vacuum chamber is required for the small satellite test to reduce the test cost. A quantitative analysis was carried out to investigate the chamber wall effect. As a result, temperature errors caused by chamber wall effect was calculated, and the temperature data acquired in the thermal balance test have been compensated. By defining the optimized area ratio between chamber surface and satellite surface area, the baseline to be able to determine the minimum size of thermal vacuum chamber was established to minimize the wall effect. Also, theoretical analysis about transparent material coating which can reduce the chamber wall effect is conducted.

• Proceedings of the Korea Institute of Fire Science and Engineering Conference
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• 2001.11a
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• pp.301-310
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• 2001

본 연구는 내화성능을 가진 수막보호유리벽을 실제 건축물에 적용하는데 있어서 필수적으로 고려해야 할 가상시나리오 중에서 수막이 유리면을 보호하기 이전에 유리면에 근접되어 있는 화염으로부터 방출되는 복사열이 유리면이 가열된 상태에서 수막이 형성될 경우 유리면의 온도가 급속히 냉각됨으로서 발생할 수 있는 급냉파열특성을 규명하기 위해 실험한 연구로서 가열면온도범위에 따라 유리면에$150^{\circ}C$이상 $250^{\circ}C$이하에서 수막이 형성될 경우 급냉파열은 일어나지 않았으나 일반유리는 $100^{\circ}C$이상 $150^{\circ}C$이하에서 급냉파열이 일어남을 확인하였다. 즉 방화구획벽에 적용가능한 수막형성유리벽의 유리가 강화유리인점을 착안하면 수막의 도포이전에 강화유리면의 온도가 $250^{\circ}C$까지 올라가기 전에는 수막을 유리면에 접촉하여도 유리면의 급냉파열이 일어나짐 않음을 확인할 수 있었다. 이점은 일정한 구획내에서 유리면의 직근에 설치된 감지기에 의해 수막형성시스템의 가동을 할 경우 급내파열형상이 발생하지 않는 온도범위를 설정할 때 중요한 데이터로 활용가능하다. 결과적으로 국부복사열에 의하여 온도범위를 설정할 때 중요한 데이터로 활용가능하다. 결과적으로 국부복사열에 의하여 유리면의 온도가 급냉파열현상을 일으키는 한계온도에 이르기 전에 유리벽체 상부의감지기의 작동이 필수적으로 일어날 수 있음을 증명한다면 수막을 이용한 유리벽체를 일정시간이상의 내화성능이 요구되는 방화구획의 수직부재로 활용하는데 있어서 걸림돌이 되는 급냉파열에 대한 우려를 종식시키는데 이바지할 수 있다.l류 11.56%, acid류 38.87%, hydrocarbon류 2.89%, ester류 0.80%, 총 70.32%가 확인되었다. Alcohol류에서 linalool가 3.78%, acid류에서는 caproic acid류가 14.40%, carbonyl류에서 2-hydroxy-4-methoxyacetophenone이 2.99%, hydrocabon류에서는 aromadendrene가1.59% 그리고 ester류에서는 methyl palmitate가 0.43%으로 가장 많이 함유하고 있었다.0ppm에서 약 25.6%흡수되었고 ferric citrate 100ppm은 24.7%, ferrous sulfate는 19.7%흡수되었다. ILC를 첨가하지 않은 100ppm 철분염 용액은 ferrous sulfate를 제외하고는 흡수도가 감소되었다. 철분 결핍된 쥐에게 gavage 방법에 의하여 철분강화우유를 투여하였을 때 철분 25ppm 시료에서는 ferrous sulfate가 12.5%로 가장 높았고 ferrous lactate는 8.1%, ferric citrate는 6.5% 흡수되었다. 철분 100ppm수준에서는 흡수율이 낮아져 ferrous sulfate는 25ppm 시료보다 절반이하 수준이었다. Ferric citrate는 차이가 거의 없었으며 ferrous lactate는 70%수준이었다. 이상의 결과에서 철분강화우유에 사용하기 적합한 철분염은 ferrous lactate, ferric citrate였는데 특히 ferrous lactate는 제품의 이화학적 품질, 생이용성 측면 모두에서 가장 좋은 것으로 나타났다.다 높았으며, 1회당 평균 8.1$\pm$5.1개의 난포란을 회수하였다.

• Proceedings of the Korean Ceranic Society Conference
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• 2002.10a
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• pp.185.1-185
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• 2002

• Proceedings of the Korean Magnestics Society Conference
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• 2011.12a
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• pp.89-89
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• 2011

• Journal of the Korean Institute of Gas
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• v.24 no.4
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• pp.18-24
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• 2020

The purpose of this study is to validate thermal hinderance effects, i.e., feasibilities, of fire-proof structure for LPG tank exposed to fire from adjacent burning building. The panel materials suggested for the fire-proof structure are (1) 10 mm-thick wood, (2) wood with fireproof coating, (3) 75 mm-thick Expanded Polystyrene, (4) 75 mm-thick glass wool filled sandwich panel, and (5) 75 mm-thick autoclaved lightweight concrete. The square planar fire source of 1 ㎡, a matrix of nozzles releasing 120-140 g/s of LPG, is used to heat up the wall and the tank beyond, mimicking heat transfer from burning exterior wall finishes. The feasibility is tested by inspecting structural integrity after test, and then by examining temperatures at both sides of panels and tank's front surface as well as heat fluxes. As a result, it can be concluded that, among the suggested sample materials, fire-proof wall with ALC panel only showed the feasibility for explosion prevention with the proven evidences of structural integrity and least increase in temperature of tank.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.4
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• pp.67-72
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• 2004

A regenerative cooling system has been designed through empirical 1-D analysis for a liquid rocket engine of 30-ton-level thrust. The hot-gas-side wall temperature from 1-D analysis shows 100K difference compared to 3D CFD analysis. Two variations of design with same cooling performance are suggested for different maximum channel widths i.e., 4mm and 2mm. The coolant pressure drop of the latter design is higher by 20%. The maximum liner temperature is about 700K when TBC and the thermal resistance of carbon deposit are considered. So film cooling is recommended to increase the cooling capacity as the present cooling capacity is insufficient

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.78-82
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• 2003

The cooling mechanism for a regenerative cooling liquid rocket engine of 10tf-thrust using kerosene as a fuel was studied from the viewpoint of curtain cooling. Based on the concept of a highly-stratified gas flow in the combustion chamber, the cross section of the combustion chamber was spilt into 2 independent parts, core and exterior part. Additional fuel is injected into the exterior section and gas temperature can be reduced in the exterior section. Consequently, the heat flux into the coolant and wall temperature are reduced and the thermal stability of a liquid rocket engine could be improved.