• Proceedings of the Korean Institute of Industrial Safety Conference
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• 2004.04a
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• pp.162-165
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• 2004

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.10-13
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• 2010

Low pressure combustion tests for TDM(Technology Demonstration Model) of 75 tonf thrust chamber were performed. It has design chamber pressure of 60 bar, propellant mass flow rate of 243.6 kg/s. Due to the limitation of the current firing test facility in Korea, the combustion tests were conducted to verify the operation and the combustion performance at low pressure condition (30 bar, 121.8 kg/s). All the tests had been successfully executed without the damage of the hardware. These test results can be used as fundamental data to predict the combustion performance at design point condition for 75 tonf thrust chamber.

• Proceedings of the Korean Institute of Industrial Safety Conference
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• 2001.11a
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• pp.61-66
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• 2001

가스 공정에서 취급하는 가연성물질의 연소 특성 파악은 공정의 안전 확보에 가장 중요한 문제이다. 따라서 연소특성들은 가연성물질이 공정의 취급상 부주의로 인해 누출되어 주위에 공기와 혼합되면 화재 및 폭발이 발생할 수 있는 잠재적 위험성을 평가할 수 있다. 연소특성들로는 폭발한계, 인화점, 최소자연발화점, 최소산소농도, 최소발화에너지, 연소열 등을 들 수 있다/sup 1)/.(중략)

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.1
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• pp.69-77
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• 2005

To optimize and limit the axial length of the baffle of the KSR-III engine, stability rating tests using pulse gun as one of artificial disturbance devices have been done. Generally a rocket engine can be considered to be dynamically stable if a certain imposed external perturbation or pressure oscillation in rocket combustion chamber could be suppressed within a short time period. Decay time and other parameters for the evaluation of stabilization ability of an engine to external perturbation have been analyzed to quantify stabilization capacity of engine, in other words, dynamic stability margin. Baffle not covering flame zone enough which can be considered as collision region of injector wasn't be able to suppress external perturbation sufficiently. The limit of combustion stability margin of engine is assumed to be 50 mm length baffle of the KSR-III engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.346-350
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• 2005

Effects of the changes of a film cooling mass flow rate and operating conditions on the heat flux characteristics of the subscale calorimeter were studied. A film cooling ring with twelve orifices is inserted between the injector head and the calorimeter. The calorimeter is composed of nineteen cooling channels. When a mass flow rate of film cooling is 10.5 % of a main fuel mass flow rate, maximum heat flux at the nozzle throat is decreased by 30% compared to that without film cooling. In the OD3(of-design point) test result, maximum heat flux at the nozzle throat is increased by 31% compared to that of the DP(design point) test when a film cooling flow rate is zero.

• The Journal of the Acoustical Society of Korea
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• v.15 no.4
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• pp.105-112
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• 1996

A linear acoustic analysis for baffled rocket combustion chambers has been developed. This study provides the comprehensive theoretical background for the baffle as one of the stabilizing devices in a liquid rocket propulsion system. Several specific effects of baffles are presented as mechanisms by which baffles eliminate instability. Included are longitudinalization of transverse waves inside baffle compartments, severe restriction of velocity fluctuations near the injector face, and decreased normal mode frequency of the chamber.

• Journal of the korean Society of Automotive Engineers
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• v.6 no.2
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• pp.1-6
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• 1984

복잡한 연소과정의 예측을 위한 이론적인 연구는 Gosman, Spalding, Patankar등의 수치해석방 법을 이용하여 진행된 것들이 많다. 현재 이분야에 응용되는 일반적인 Program으로는 Boundary Layer Type의 방정식을 이용한 One-Dimensional Program (GENMIX 4, Revised GENMIX) 등이 있으나 Parabolic Type이므로 주방향에 수직된 방향으로 동일한 값이 2개 이상 존재할 수 있는 Elliptic현상을 설명하기에는 어려움이 있다. 그러므로 비록 기억용량(Computation Storage) 및 계산시간(Running Time)에 불리한 점이 있기는 하나 Elliptic상황을 해석해야만 할 경우가 있다. 본 해설은 Patankar의 Elliptic "SIMPLE" Program을 연소 해석과정에 이용되는 방법을 간단한 연소과정의 예로서 설명하는 것으로 연소과정의 연구보다도 Program의 응용성에 중점을 두었다. 따라서 실제의 물리적인 연소 mechanism에서 많은 가정을 도입하여 문제를 단순화 시켰으며 실제의 연소문제에 충분한 접근을 위해서는 turbulence-modeling과 radiation heat flux가 본 해설에 덧붙여져서 논의되어야 한다. 논의되어야 한다.

• Journal of Advanced Marine Engineering and Technology
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• v.21 no.1
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• pp.43-48
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• 1997

The present study is aimed to investigate experimentally on the hydrodynamic behaviours of air ~ pulverized coal flow in rectangular combustor with cavity. Mean velocity, density and tur¬bulent properties of pulverized coal in rectangular entrained flow combustor were measured by PDA. Experimental results show that the flow reattachment point at the lower plane in the com¬buster chamber has been developed near X/D= 15. The similarities at each section are found after the flow reattachment point. The maximum values of turbulent intensity and Reynolds shear stress have been shown near Y/D=6, which is higher than centerline. The maximum density of the pulverized coal sited in the range ofY/D=6~8.

• Proceedings of the Korean Nuclear Society Conference
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• 1995.05b
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• pp.715-720
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• 1995

DUPIC 핵연료의 제작 조건, 특히 소결 조건에서 필요한 O/M값에 따른 산소포텐샬을 점결함모형을 이용하여 구하였다. 산소포텐샬 값은 순수 우라니아에서보다 크게 나타났고 주요 점결함 형태의 변화로 온도에 따라 엔트로피 값의 변화가 보였다. 연소중 DUPIC핵연료의 산소포텐샬 변화는 핵연료를 닫힌 계로 보고 물질 보존 및 평형법칙을 기초로 하여 구하였다. 산소포텐샬은 초기에 급격히 증가하지만 곧 일정한 값에서 매우 완만히 증가하게 된다. O/M값도 거의 변화가 없는데, 이는 Mo의 완충작용 때문이다. 따라서 초기 Mo의 화학적 형태- 금속 또는 산화물-가 DUPIC핵연료 O/M값 변화에 큰 영향을 미칠 것으로 예측되며 DUPIC핵연료 제작시 소결 조건에 유의할 필요가 있다.

• Fire Science and Engineering
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• v.31 no.3
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• pp.25-30
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• 2017

Because of the vertical combustion characteristics of combustible substances, accurate substance safety information for their safe use, handling and transportation is essential. The flash point, fire point, explosion limits and autoignition temperature (AIT) are important safety parameters which need special attention in chemical plants and laboratories that handle dangerous materials. In this study, tert-butylbenzene which is widely used as an intermediate material in the chemical industry was selected. For the reliability of the flammable properties of tert-butylbenzene, this study was investigated the explosion limits of tert-butylbenzene in the reference data. The flash points, fire points and AITs by the ignition delay time for tert-butylbenzene were experimented. The lower flash points of tert-butylbenzene by using the Setaflash and Pensky-Martens closed-cup testers measured $39^{\circ}C$ and $44^{\circ}C$, respectively. The flash points of tert-butylbenzene by using the Tag and Cleveland open cup testers are measured $51^{\circ}C$ and $54^{\circ}C$. And the fire points of tert-butylbenzene by the Tag and Cleveland open cup testers were $54^{\circ}C$ and $58^{\circ}C$ respectively. The AIT of tert-butylbenzene measured by the ASTM 659E tester was measured as $450^{\circ}C$. The lower explosion limit of $39^{\circ}C$ which measured by the Setaflash flash point tester was calculated to be 0.68 vol%.