• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2002.07b
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• pp.773-777
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• 2002

In this study, we analyzed the LPG and LNG sensitivity measurement and voltage variation using catalytic type gas sensor characteristics in catalytic combustion type gas detecter sensors. gas detector shall operate as intended when exposed for 24 hours to air having a relative humidity of 0~85 percent at a temperature of $20[{\mu}m]$ and humidity of 45 percent at a temperature of $-10{\sim}40[^{\circ}C]$ the gas detecter sensors are to be subjected to operation for 210 days in an area that has been detemined to be equivalent to a typical residential atmosphere with an air velocity of 50 [cm/sec]. The source of energy for a gas detector sensors employing a supplementary basic circuit is energized from a separate source of supply direct applied voltage 2.1[V], 2.2[V], 2.3[V]. As a result, it was confirmed that the relative humidity and temperature by regression each analysis, compared to the LPG characteristic graph and methane characteristics graph by a relative humidity of 0 ~ 85 [%] at a temperature range of $-10{\sim}40[^{\circ}C]$ show a similar linear pattern on the whore.

• Plant Journal
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• v.11 no.4
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• pp.38-46
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• 2015

중유를 연소하는 D 발전소 탈황설비는 운전시간의 경과에 따라 흡수탑 중간층에 석고가 쌓이고 가스분사 파이프 내에 경질석고 스케일이 부착됨으로써 발전설비 및 탈황설비의 정상적인 운전이 어렵게 된다. 흡수탑 내부에 발생된 스케일을 제거하지 않을 경우에는 탈황효율의 저하에 따른 SO2 배출농도의 증가로 발전가능 최대출력의 하향조정이 발생되고 나아가 발전정지를 초래한다. 스케일 제거를 위한 탈황설비 세정은 발전가능 최대출력의 하향조정이 발생하는 시점으로 결정할 수 있다. 본 연구에서는 탈황설비의 운전 자료를 분석하여 발전가능 최대출력의 하향조정이 발생되기 6주 전은 탈황설비 출구 SO2 농도값이 130ppm을 초과하고 동시에 흡수탑 차압은 380mmH2O을 초과하며, 직전 흡수탑 세정 이후 44주가 경과된 시점이 됨을 확인하였다. 그리고 흡수탑의 세정시기는 세정준비기간 6주와 발전가능 최대출력 하향이 발생되기 6주 전까지의 운전경과일수 44주를 더하여 직전 세정시점으로부터 50주가 경과된 시점임을 예측하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.43-46
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• 2006

Storage air heater(SAH) is a general purpose facility that is used to simulate the high altitude condition of supersonic ground test facility, thurst compensation test of rocket engine nozzle and gas turbine engine combustor test. SAH in KARI is built to simulate the total temperature of the supersonic ground test facility which has a wide flight envelope from altitude 0km, Mach 2 to altitude 25km, Mach 5 and operates up to 1300K, 3.5MPa. In this paper, we introduces the SAH in JAXA which is model of SAH in KARI and summarizes the design process and manufacture of ours.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.103-106
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• 2008

In this work it was studied that the effect on sub-component of engine considering change of engine inlet pressure caused by variable acceleration during flight of launcher. Also the transitional performance was predicted according to variable acceleration. Engine inlet pressure was defined as summation of propellant head in tank, ullage pressure and pressure difference of line, etc. Therefore consumption of propellant and acceleration of launcher led to change of engine inlet pressure, which affected on discharge pressure of pumps. This effect changed mass flow rate of gas generator and main combustor hence it was observed that engine performance was changed definitely.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.311-314
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• 2009

A two-dimensional thermal response and ablation simulation code for predicting charring material ablation and shape change on solid rocket nozzle is presented. For closing the problem of thermal analysis, Arrhenius' equation and Zvyagin's ablation model are used. The moving boundary problem and endothermic reaction in thermal decomposition are solved by rezoning and effective specific heat method. For simulation of complicated thermal protection systems, this method is integrated with a three-dimensional finite-element thermal and structure analysis code through continuity of temperature and heat flux.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.107-110
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• 2009

A basic design for a Technical Development Model (TDM) of liquid oxygen lines from the turbopump exit to the oxidizer valves of the combustion chamber and the gas generator was conducted to develop a turbopump-fed liquid rocket engine. The TDM is composed of straight lines, elbows, bellows, a branch, an orifice, flanges and a heat insulator. Materials were determined by consideration of operation conditions, weight constraint and manufacturing procedures. The size and the location of each component were determined by flow analysis of the required flowrate and the pressure loss. Basic designs of the components were conducted by consideration of the operating temperature and the maximum expectation operating pressure. The safety factors were evaluated by structural analysis of design of each component.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.2
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• pp.72-82
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• 2017

Nozzleless booster is one of the applicable components for integral rocket ramjet (IRR). In order to predict nozzleless solid booster performance, the simplified theoretical analysis was applied for L/D=5, 6, 7, 9, 11, and 13. Al-HTPB and Zr-HTPB propellant with a high metal content were used to increase the hardness because of the combustion gas flow effect. It was found that the trends between the simplified theoretical analysis and experiments were similar.

• Journal of Environmental Science International
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• v.18 no.3
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• pp.283-288
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• 2009

This is a study on the volatile organic compounds(VOCs) concentrator with zeolite adsorptive honey rotor and catalytic combustion system for abating VOCs emitted from printing industry. VOCs emitted from the printing industry is mainly caused by organic solvent of printing ink. The content of organic solvents in printing ink varies from 40% to 75% and its content in the gravure ink is higher than that in any other ink. The average concentrations of each VOCs are 139 ppm for toluene, 152.1 ppm for MEK, 256.9 ppm for methanol and 42.9 ppm for isopropyl alcohol. We used zeolite honeycomb for absorbent of VOCs concentrator and palladium for catalyst combustion system. This system abated over 96% of emitted total VOCs, 98% of toluene, 100% of MEK, 92% of methanol and, 100% of isopropyl alcohol. It is concluded that the low-leveled high-volume VOCs emitted from printing process were removed almost by concentrator with zeolite adsorptive honey rotor and catalytic combustion system.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.31 no.6 s.261
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• pp.514-521
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• 2007

This study focused on the effects of the $CO_2$ gas concentration in fresh charge and induction air temperature on the combustion characteristics of homogeneous charge compression ignition with dimethyl ether (DME) fuel, which was injected at the intake port. Because of adding $CO_2$ in fresh charge, start of auto-ignition was retarded and bum duration became longer. Indicated combustion efficiency and exhaust gas emission were found to be worse due to the incomplete combustion. Partial burn was observed at the high concentration of $CO_2$ in fresh charge with low temperature of induction air. However, indicated thermal efficiency was improved due to increased expansion work by late ignition and prolonged bum duration. Start of auto-ignition timing was advanced with negligible change of burn duration, as induction air temperature increased. Burn duration was mainly affected by oxygen mole concentration in induction mixture. Bum duration was increased, as oxygen mole concentration was decreased.

• Journal of Preventive Medicine and Public Health
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• v.7 no.2
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• pp.373-375
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• 1974

The concentration of Carton momoxide(CO) and Sulful dioxide($SO_2$) by burning time of coal, and its time of fading out in atmosphere after effluence from stove were measured with Kitagawa gas detector, January, 1974. Gas for measurement was sampled by gas syringe at the point distanced 60cm. from first junction of garvanized pipe of stove. CO concentration was directly proportional to the burning temperature of coal but $SO_2$ was generally constant durning burning time or also in proportion to burning temperature. CO gas of effluent mixed with air(relative humidity, 40%) was maintained for long period relatively, but $SO_2$ gas was early faded out within short time. The period decreasing to allowable limit was about 4 days in former and about 30 minutes in later, respectiively.