• Proceedings of the KAIS Fall Conference
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• 2010.11a
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• pp.284-287
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• 2010

본 연구논문에서는 주요 온실가스인 이산화탄소의 제거를 목적으로 이온성 액체를 실험실규모로 제조한 후 기-액 흡수평형장치를 이용하여 이산화탄소의 용해도 및 재생특성 그리고 희석제첨가에 따른 영향을 조사하였다. 이산화탄소 용해도는 흡수평형압력 25bar조건에서 두 이온성 액체 모두 0.6 mole $CO_2$/mole ILs의 비슷한 흡수력을 보였다. 재생성능의 경우 탈착 전 후의 흡수력 차가 약 7%로 양호한 재생력을 나타냈다. 점도 감소를 위하여 sulfone 희석제를 첨가하여 조사한 결과 흡수력에서 약 15%가량 감소함을 알 수 있었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.253-256
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• 2006

A numerical study for spray flow of fuel and oxidizer droplets in the combustion chamber has been conducted prior to the analysis of spray combustion of the liquid rocket engine. As the spray combustion model, DSF model and Euler-Lagrange scheme have been used. While the coupling effects of the droplets between gas phase and evaporated vapor have been calculated using PSIC model, SIMPLER algorithm and QUICK scheme have been used as numerical schemes. As the results, the calculations have shown velocity and temperature distribution in combustion chamber as well as mole fraction of fuel and oxidizer.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.16-17
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• 2002

재생냉각은 엔진 경량화 및 높은 추력을 발생시킬 수 있으며 엔진이 장시간 작동할 경우에도 추력의 변화가 일어나지 않는 우수성으로 인해, 액체로켓엔진에서 보편적으로 사용되고 있는 냉각방식이며, 고성능 액체로켓엔진 개발에 있어서 핵심기술이다. 일반적으로 재생냉각 방식은 연소기 내벽에 형성된 냉각유로에 연료 또는 산화제를 흘려보내 고온고압의 연소실내에 온도 경계층을 생성시키면서 벽면온도를 적정온도 이내로 유지하는 것이 목적이며, 또한 냉각유로에서의 압력강하가 추진제 공급 시스템의 공급 압력의 한계값을 넘어서지 않도록 하며, 냉각후의 연료 또는 산화제의 열역학적 상태가 엔진 작동 조건에 적합하도록 제어하여야 한다.

• 한국전산유체공학회:학술대회논문집
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• 2008.03b
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• pp.316-319
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• 2008

A computational analysis has been conducted on the compressible flow in the turbine exhaust nozzle of the gas generator cycle liquid rocket engine. The commercial CFD code Fluent has been used. Four nozzle designs have been compared to select the turbine exhaust nozzle concept. Three candidates with single nozzle have comparable performance. The model with bifurcated nozzles shows significant performance loss. However it will be better in the view of balanced thrust distribution because of its symmetric geometry.

• 한국전산유체공학회:학술대회논문집
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• 2008.03b
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• pp.328-331
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• 2008

A literature survey has been reported of the systems analysis on the liquid rocket engines. The analysis tools are mainly about the calculation of the rocket engine performance at the early days. However recent trend shows that researchers try to develop an integrated environment of distributed analysis tools for faster and cheaper analysis. This article presents the systems analysis results of the liquid rocket engine of gas generator cycle using the published mass estimating model. The specific impulse change for various thrust to weight ratio agrees qualitatively well with the published data.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.6
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• pp.126-133
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• 2018

A liquid rocket engine experiences various static loads in flight, such as high pressures due to propellents, thrust and thermal loads due to cryogenic liquid oxygen and combustion gas with extreme vibration. During the engine development stage, structural analyses and investigation on the strain measured from ground firing tests are necessary for determining the structural reliability of the engine. In this study, the strain characteristics, obtained from the ground firing tests of a 75 tonf-class engine, were analyzed.

• Journal of the Korean Society of Marine Environment & Safety
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• v.19 no.2
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• pp.225-231
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• 2013

Liquefied gas carriers generally transport cargoes of flammable or toxic nature. Since these cargoes may cause an explosion, fire or human casualty, the accommodation spaces, service spaces and control stations of liquefied gas carriers should be so located as to avoid ingress of gas. For this reason, the paragraph 8.2.9 of IGC Code in IMO requires that the height of vent exits should be not less than B/3 or 6 m whichever is greater, above the weather deck and 6 m above the working area and the fore and aft gangway to prevent any concentration of cargo vapor or gas at such spaces. Besides as known, the LNG market has been growing continually, which has led to LNG carriers becoming larger in size. Under this trend, the height of a vent will have to be raised considerably since the height of a vent pipe is generally decided by a breadth of a corresponding vessel. Accordingly, we have initiated an examination to find an alternative method which can be used to determine the safe height of vent masts, instead of the current rule requirement. This paper describes the dispersion characteristics of boil-off gas spouted from a vent mast under cargo tank cool-down conditions in the membrane type LNG carriers.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.168-175
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• 2005

The pressurization system in a liquid rocket propulsion system provides a controlled gas pressure in the ullage space of the vehicle propellant tanks. It is advantage to employ a hot gas heat exchanger in the pressurization system to increase the specific volume of the pressurant and thereby reduce over-all system weight. A significant improvement in pressurization-system performance can be achieved, particularly in a cryogenic system, where the gas supply is stored inside the cryogenic propellant tank. The temperature characteristic of cryogenic pressurant is very important to develop some components in pressurization system. Numerical modeling and Test data were studied using SINDA/FLUINT Program and PTF(Propellant-feeding Test Facility).

• 한국신재생에너지학회:학술대회논문집
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• 2011.05a
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• pp.78.1-78.1
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• 2011

분포지역과 매장량이 한정되어 있는 석유에 비하여 석탄은 가채년수가 길고 세계 전역에 널리 분포되어 있으므로 향후 안정적인 에너지 공급으로 각광받고 있다. 석탄을 이용하여 CWM을 제조하는 기술은 석유에 비하여 저장, 수송, 분진 비산등의 문제점을 개선하여 위하여 1980년대부터 석탄 물 혼 합연료(Coal-Water Mixture)의 기술개발을 위한 연구가 진행되었다. 이는 미분탄(유연탄)에 30%정도의 물과 약간의 첨가제를 혼합하여 유체화하여 수송성은 액체연료와 같고 연소성은 석탄의 성상을 갖는 특징을 가지게 된다. 본 연구에서는 당센터에서 보유하고 있는 습식 분류층 가스화장치에 적용하기 위한 CWM(Coal Water Mixture)제조 특성을 연구하였다. 습식 석탄 가스화기에 사용되는 CWM은 미분되어진 석탄과 물, 첨가제를 일정비율로 혼합하여 사용하게 된다. 이때 공급되어지는 미분의 입도와 분쇄 형태에 따른 입자 형태, 입자의 분포에 따라서 CWM의 특성이 각각 다르게 나타나게 된다. 이때 만들어진 CWM의 농도와 점도 특성에 따라서 버너의 성능 및 가스화기 운전 조건등에 많은 영향을 미치게 된다. 습식 석탄 가스화에 적용된 예정인 대상탄을 대상으로 하여 석탄분쇄 형태에 따른 CWM의 제조 특성을 실험하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.197-201
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• 2006

In the development process of a fuel-rich gas generator using kerosene and LOx for a 30 tonf class liquid rocket engine, a heat damage occurred at the LOx post of swirl coaxial injectors used in the gas generator and the problem has been examined. To prevent the heat damage, injectors are redesigned to have an increased recess while maintaining internal mixing, which minimizes recirculation region to prevent anchoring of the flame in the recirculation region. The combustion test results of the sub-scale gas generator showed that this scheme can prevent heat damage of the LOx post in the swirl coaxial injectors of the fuel-rich gas generator.