• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.279-286
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• 2010

Hypersonic aircraft technologies have been developed with increase in flight speeds. As hypersonic flight speeds increase, heat loads on an aircraft and it's engine increase. Researches on cooling technologies using endothermic fuels are progressing in the USA, France, and Russia to treat the heat loads. Endothermic fuels are liquid hydrocarbon aircraft fuels which are able to absorb the heat loads by undergoing endothermic reactions, such as thermal and catalytic cracking. In this study, methylcyclohexane, n-octane, and n-dodecane were selected as model endothermic fuels and experiments in endothermic properties were implemented. Experimental conditions were supercritical phase of each model fuels in which actual endothermic fuels were exposed. The object of this study is to identify endothermic properties of the model endothermic fuels and to predict endothermic properties of actual fuels such as kerosene fuels.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.66-73
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• 2004

As a rocket propellent of hydrocarbon fuels, the characteristics of liquefied natural gas was evaluated with the viewpoint of the constituents and content, the cooling performance as a coolant, and characteristic velocity and specific impulse as parameters of the engine performance. Content of methane was a principal factor to determine the characteristics as a rocket propellant and more than 90% of it was needed as a fuel and coolant in the regenerative cooled liquid rocket engine. Some constituents of the liquefied natural gas can be frozen by the pre-cooling of the pipe lines, therefore they can be a factor disturbing the normal working of engine. In case the content of methane is around 90% in the liquefied natural gas, a normalized stoichiometric O/F mixture ratio of 0.75 is suggested for a nominal operation condition to get the maximum specific impulse and characteristic velocity.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.5
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• pp.79-91
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• 2008

The present article is intended to introduce the X-51A Scramjet Engine Demonstrator-Wave Rider (SED-WR) program and its core technologies to the korean propulsion community. The X-51A program is lead by the U.S. Air Force Research Laboratory (AFRL) and is sponsored by the U.S. Defense Advanced Research Projects Agency (DARPA). Most of the contents is taken from the paper by Hank et al.[1] with the supplemental materials from additional references. X-51A is a hypersonic experimental vehicle for the flight test of the hydrocarbon fuel-cooled scramjet engine developed by the AFRL HyTech program. The scramjet engine and the hypersonic flight technologies may enter the era of practical use by the completion of the ground tests in 2008 followed by the flight tests scheduled in 2009.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.643-646
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• 2017

In a liquid rocket engine using hydrocarbon fuels, cooling of the combustion chamber wall is necessary to prevent the combustion chamber wall from melting or structurally deforming due to high heat flux. Among the various methods, regenerative cooling, which uses fuel as a coolant and then injects it into the combustion process, has good performance. This study investigated the heat transfer characteristics of kerosene as a coolant by varying the copper cross-sectional area, the flow rate in the channel, and the current applied to the channel. Convective heat transfer occurred rapidly when the cross-sectional area of the copper channel was small and when the kerosene flow velocity was fast.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.3
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• pp.56-60
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• 2017

In hypersonic aircraft, increase of aerodynamic heat and engine heat leads heat loads in airframe. It could lead structural change of aircraft's component and malfunctioning. Endothermic fuels are liquid hydrocarbon fuels which are able to absorb the heat load by undergoing endothermic reactions. In this study, exo-tetrahydrodicyclopentadiene was selected as a model endothermic fuel and experiments were investigated in endothermic fuel cooling system with zeolite catalyst. Three shapes of catalysts have been manufactured and endothermic characteristics were recovered. Bineded catalyst showed higher heat absorption and conversion than other two zeolite catalysts. In product distribution, binded catalyst showed higher aromatics composition.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.3
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• pp.90-98
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• 2006

The Heated Tube Facility(HIF) was fabricated to identify the forced convective heat transfer and the cooling characteristic for the hydrocarbon fuel(Jet A-1), which is used for the coolant of the regenerative cooling system. The forced convective heat transfer coefficient was calculated from the measured coolant and tube surface temperature. In case of using the Jet A-1, the maximum heat flux which the coolant can absorb was identified by determining the critical wall temperature generating the burnout on the fixed flow condition. The inlet bulk-temperature of the coolant has a direct influence on the forced convective heat transfer characteristic.

• Proceedings of the Membrane Society of Korea Conference
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• 1995.04a
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• pp.38-39
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• 1995

최근 자동차 대체 연료로 가솔린에 10% 무수에탄올이 혼합된 Gasohol 사용에 관한 관심이 고조되고 있으며, 이는 Gasohol이 자동차 배기 가스중의 일산화탄소 및 탄화수소 함유량을 감소시켜 대기 오염을 줄일 수 있기 때문이다. Gasohol에 사용되는 무수에탄올의 농도는 99.5% 이상이어야 하며, 이러한 고순도의 에탄올을 제조하기 위해서는 물과 에탄올의 공비 혼합물(95.6% 에탄올)로부터 공비증류, 분자체 흡착, 투과증발과 같은 분리 조작을 이용하여 물을 제거하는 공정이 필요하다. 현재 에탄올 탈수에는 공비증류가 많이 사용되고 있으나 공비증류는 에너지 사용량이 많을 뿐더러 유독한 Entrainer를 첨가하기 때문에 투과증발과 같은 저 에너지 소비형, 환경친화적인 공정으로의 전환이 이루어지고 있다. 에탄올 탈수용 투과증발 플랜트는 전세계 20여개가 가동되고 있으며, 상업화된 플랜트의 대부분은 독일의 Deutsche Carbone사가 제조한 PVA/PAN 투과증발 복합막을 사용하고 있다. 투과증발 시스템은 물에 대한 친화도가 높은 투과증발막 및 모듈, 기타 분리 구동력을 높여주기 위한 Heater, 진공펌프, 냉각기, 열 교환기 등의 주변 설비로 구성되며, 투과증발 시스템 개발을 위해서는 우수한 막/모듈 제조와 아울러 최적 공정 설계 기술 개발이 필수적이라 하겠다.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.2
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• pp.10-15
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• 2014

For hypersonic aircraft, increase of flight speeds causes heat loads that are from aerodynamic heat and engine heat. The heat loads could lead structural change of aircraft's component and malfunctioning. Endothermic fuels are liquid hydrocarbon fuels which are able to absorb the heat loads by undergoing endothermic reactions, such as thermal and catalytic cracking. In this study, methylcyclohexane was selected as a model endothermic fuel and experiments on endothermic properties were implemented. To improve heat of endothermic reaction, we applied zeolites and confirmed that HZSM-5 was the best catalyst for the catalytic performance. The objective is to investigate catalytic effects for heat sink improvement. The catalyst could be applied to system that use kerosene fuel as endothermic fuel.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.2
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• pp.131-136
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• 2012

This paper investigated the combustion and exhaust gas characteristics of gasoline direct injection engines for various cooling water temperature. The engine-out nanoparticle emission number and size distribution were measured by a DMS-500 equipped upstream of the catalyst. A CLD-400 and an HFR-400 were equipped at the exhaust port to analyze the cyclic NOx and total hydrocarbon emission characteristics. The results showed that the nanoparticle emission number greatly increased at low coolant temperatures and that the exhaust mainly contained particulate matter of 5.10 nm. THC also increased under low temperature conditions because of fuel film on the combustion chamber. NOx emissions decreased under high temperature conditions because of the increase in internal exhaust gas recirculation. In conclusion, an engine management system control strategy for driving coolant temperature up rapidly is needed to reduce not only THC and NOx but also nanoparticle emissions.