• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.3
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• pp.97-103
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• 2012

The combustion chamber and nozzle of a liquid rocket engine should be protected from the high temperature combustion gas generated by the chamber. An upper-stage nozzle extension has a large expansion ratio, therefore, The light-weight refractory materials have been used since the weight impact on the launcher performance is crucial. Gas film cooling method was used before, but was not applicable nowadays. Ablative cooling method and radiative cooling method with niobium alloy, Ni-based superalloy and ceramic based composite have been used to this day.

• Journal of the Korean Institute of Gas
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• v.10 no.4 s.33
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• pp.41-46
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• 2006

A study was conducted to investigate the problem caused by the mechanical particles in LOX system during operating and testing propulsion system, especially concentrated on effects of contaminants accumulation and transfer in LOX system. Several methods for system operation decreasing accidents caused by oxidizer Beakage and contaminants accumulation was investigated. These methods can be applied to LOX system and other propellants system in liquid propellants propulsion system.

• Journal of the Korean Institute of Gas
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• v.19 no.3
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• pp.18-24
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• 2015

The flash point is one of the most important indicators of the flammabiliy of liquid solutions. The flash point is the lowest temperature at which there is enough concentration of flammable vapor to form an ignitable mixture with air. In this study the flash points of binary flammable solutions, 2-propanol+propionic acid and n-hexanol+formic acid systems, were measured using Seta flash closed cup tester. Particularly n-hexanol+formic acid system exhibited minimum flash point behavior. The measured values were compared with the calculated values using Raoult's law and optimization method. The calculated data by optimization method described the measured values more effectively than those calculated by Raoult's law.

• Journal of the Korean Institute of Gas
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• v.15 no.3
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• pp.1-5
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• 2011

For the hydrogen liquefaction, the large amount of energy is consumed, because precooling, liquefaction and ortho/para conversion heats should be eliminated. In this paper the basic design and thermal analysis are carried out to reduce the energy consumption by using LNG cold energy for precooling process in hydrogen liquefaction processes. The LNG cold energy utilization for hydrogen precooling enables not only to get energy saving for liquefaction, but to recover the wasted cold energy to sea water at the LNG terminal. The results show that the energy saving rate for liquefaction using LNG cold energy is almost 75% of current industrial hydrogen liquefaction plant. The demand flow-rate of LNG is only 15T/D for 1T/D hydrogen liquefaction.

• The Journal of the Acoustical Society of Korea
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• v.8 no.1
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• pp.23-30
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• 1989

Propagation phenomena of nonlinear pressure waves in a bubbly mixture are studied. The governing equations for a bubbly mixture are derived heuristically and energy equation is incorporated with other governing equations to take thermal effects into consideration inside the bubble. This non-isothermal condition of the bubble inside is especially important when high amplitude pressure waves are treated. Keller's equation is adapted for the bubble dynamics as practical problem. Some numerical simulations are carried out for the shock tube problem using a computer program based on the above model. A comparison with experimental results of Noordzij and van Wijngaarden shows that the structure of the wave in the shock tube experiment seems to be much more significantly affected 요 the complex heat transfer phenomena inside the bubbles than by the relative translational motion between bubbles and surrounding liquid.

• Korean Journal of Air-Conditioning and Refrigeration Engineering
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• v.25 no.3
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• pp.137-142
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• 2013

A small air-conditioner or chiller for a constant temperature bath normally uses a constant speed compressor. The constant speed compressor is relatively inexpensive, but it uses on/off control for capacity modulation. The on/off control has several disadvantages, specifically energy loss and large temperature fluctuation. Continuous operation with a bypass system can be an alternative to on/off control, for capacity modulation. In this study, a heat pump system having a hot-gas bypass and a liquid bypass was adopted. The performance of the bypass-type heat pump was measured, by varying the bypass valve opening. The differences of the COP between the hot-gas bypass and the liquid bypass, in the cooling and heating operations, were within 2% and 1%, respectively. The liquid bypass showed a wider range of capacity control in the cooling operation but the hot-gas bypass showed a wider range of capacity control in the heating operation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.04a
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• pp.26-26
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• 1998

우주항공 산업에 대한 관심 증가에 따라 지상에서 많은 연소시험을 시행하고 있으나, 소음 발생문제에 부딪혀 어려움을 겪고 있는 실정이다. 따라서 초보적 단계이기는 하나, 액체로켓 엔진의 추력 손실을 최소화시키고 최대한 제트 소음을 크게 줄일 수 있는 소음기를 연구, 개발하고 있다. 본 연구에서는 제트소음에 대한 기초연구를 수행하여 물분사형 소음기를 설계 및 제작하였고, 물분사량과 소음기의 기하학적형상이 소음 특성에 미치는 영향을 연구하였다. 본 실험범위에서 연구의 결과는 다음과 같다. 1. 동일한 물 분사량 조건에서, 소음기 길이가 노즐출구 직경의 10배 모델 보다 30배 모델이 9dbl 정도 감음효과를 보였다. 2. 불 분사량이 증가함에 따라 소음레벨은 감소하였고, 30배 모델의 경우 불분사량이 배기가스의 10-12배 조건에서는 소음레벨을 91dbl까지 줄일 수 있었다. 3. 상기조건(소음레벨 91dbl)에 확장관을 부착함으로써, 소음레벨을 약 86dbl까지 줄일 수 있었다. 4. 본 형태의 물분사방식을 채택할 경우 고온배기가스로 인한 소음기의 파손을 방지하기 위해서 반드시 막냉각장치의 설치가 요구된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1084-1087
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• 2017

When a liquid rocket engine is started the oxidizer and fuel must be flowed into combustion chamber and gas generator with time differences. The wrong time difference between propellants or malfunction of ignition device can occur the explosion of combustion chamber due to detonation by energized premixed-propellants. Therefore it is important to observe the transient characteristic of propellants or to measure the inflow time of propellants into combustion chamber and gas generator. The measurement of static pressure is not enough to observe the propellants inflow time into combustion chamber and gas generator. By measuring dynamic pressure of main flow passage of propellants the accurate propellants inflow time could be investigated.

• Journal of the Korean Institute of Gas
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• v.20 no.6
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• pp.31-36
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• 2016

The flash point is one of the most important indicators of the flammability of liquid solutions. The flash point is the lowest temperature at which there is enough concentration of flammable vapor to form an ignitable mixture with air. In this study the flash points of ternary liquid solutions, n-nonane+n-decane+n-dodecane system, were measured using Seta flash closed cup tester. The measured values were compared with the calculated values using Raoult's law and empirical equation. The calculated data by empirical equation described the measured values more effectively than those calculated by Raoult's law.

• Journal of Energy Engineering
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• v.16 no.2
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• pp.58-63
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• 2007

In recent years, the technologies for the production of synthetic fuel from natural gas have been attracting considerable interest because of high oil prices. While oil prices remaining high, GTL (Gas-to-Liquids) technology would provide an attractive option for utilizing gas resources. Furthermore, GTL fuels contain almost zero sulfur and low aromatics and have a very high cetane so that they are estimated to be environmentally friendly diesel fuels able of meeting the advanced fuel specifications of the 21st century. GTL process generally consists of three primary steps: synthesis gas production from natural gas reforming, hydrocarbon production from synthesis gas by Fischer-Tropsch (F-T) synthesis, product upgrading by hydrocracking/hydroisomerization. This paper presents a brief summary of GTL technology and worldwide development trend about it focusing on the reforming of natural gas and the F-T synthesis.