• Journal of the Korea Academia-Industrial cooperation Society
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• v.18 no.1
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• pp.345-350
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• 2017

Downsizing is widely applied to diesel engines in order to improve fuel efficiency and reduce exhaust emissions. Engine sizes are becoming smaller but pressure and temperature inside combustion chambers are increasing. Therefore, research for fuel spray under high pressure and temperature conditions is important. A constant volume chamber which simulates high temperature and pressure likely to be found in diesel engines was developed in this study. Pressure and temperature were increased abruptly because of ignition of the pre-mixture in the constant volume chamber. Then pressure and temperature were gradually decreased due to the heat loss through the chamber wall. Fuel spray occurred when temperature and pressure were reached at the target condition. In this experiment, the temperature condition should be exactly defined to understand the relation between fuel evaporation and ambient temperature. A fast response thermocouple was developed and used to measure the temporal and spatial temperature distribution during the combustion process inside the combustion chamber. In the results, the core temperature was slightly higher than the bulk temperature calculated by the gas equation. Ed-note: do you want to say 'ideal gas equation'? This was attributed to the heat transfer loss through the chamber wall. The vertical temperature deviation was higher than the horizontal temperature deviation by 5% which resulted from the buoyancy effect.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.207-210
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• 2006

Injector is one of the most important elements in Liquid rocket Engine design, and how to arrange these injectors on the head determines the engine performance. In this study, when the swirl injectors are used for the 1st designing of injector head of 170 tonf UDMH-LOX as the propellant of LRE, a distribution relation of the mass flow rate per unit area was calculated from the function of ${\Phi}$, which is related with the mass flow rate characteristics of swirl injector. And the combustion characteristics by circumferential axis were estimated using this relation under the consideration of combustion core and film cooling area.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.4
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• pp.63-72
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• 2003

The combustion characteristics of the KSR-III engine were investigated numerically from the viewpoint of performance and combustion field. For numerical analysis of KSR-III engine with hub-and-spoke baffle, 3-D calculation was performed about $30^{\cire}$ section and the prediction of performance was in a good agreement with hot-firing test result. As a result of baffle installed, the performance of KSR-III engine was reduced in comparison with no baffle case and local high temperature region appeared on injector plate, combustion wall and baffle wall, This calculation was used practically as basic data for designing injector plate with film cooling holes and predicting the performance of KSR-III final flight test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.54-58
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• 2017

A combustion instability has been one of the most serious problems in the development of combustion devices including rocket engine and gas turbine. In particular, a high-frequency combustion instability generated by resonant coupling between combustion phenomena and acoustic oscillations within thrust chamber causes severe damage to the hardware. Because it is accompanied by high amplitude pressure oscillations and excessive heat flux to the chamber wall. Therefore, combustion instability is one of the difficult problems that must be resolved in developing liquid rocket engine. This paper describes the cases of combustion instability encounted during the development of thrust chamber for KSR-III and KSLV-II.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1996.10a
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• pp.50-54
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• 1996

최근들어 전력수요와 상시 전력공급이 요구되는 시설이 증가함에 따라 독립적으로 전력을 공급할 수 있는 상용 또는 비상용발전기가 많이 이용되고 있는 추세이다. 이러한 소형 발전시스템에는 디젤엔진이나 터빈 엔진에 발전기를 연결하여 전력을 공급하는 코젠 시스템(co-generation system)이 주로 이용된다[1]. 일반적으로 코젠시스템은 운전중에 매우 높은 수준의 소음이 발생되므로 건물 주변이나 사람의 왕래가 잦은 곳에 설치되는 경우에 필히 소음저감을 위한 대책이 필요하게 된다[2,3]. 본 사례는 대형놀이시설의 전력공급용으로 설치된 옥내(발전실내)의 상용/비상용 발전기(3600 KW 디젤엔진 2대)에서 발생한 상당량의 소음이 놀이시설주변까지 전달되어, 소음원 및 그 전달경로를 규명하고 대책을 수립한 내용이다. 놀이시설의 개장을 앞두고 소음문제가 발생되었기 때문에 신속하고 현실적인 해결책의 적용이 요구되었으므로 발전기 및 발전실 주변의 소음레벨 및 주파수특성의 분석을 통하여 주소음원을 규명하는 방법을 택했다. 분석결과로부터 주 소음원은 엔진 배기구에서 발생되는 저주파수 특성을 갖는 소음으로 규명되었고, 그 주파수특성에 적합한 흡음 및 반사특성을 동시에 갖는 조합형 2차 소음기를 추가로 설치하여 발전실 주변소음레벨을 크게 저감할 수 있었다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.10
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• pp.1001-1009
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• 2012

In this study, the cooling characteristics of combustion gas were investigated by injecting liquid nitrogen ($LN_2$) into a liquid rocket combustion chamber, which uses liquid oxygen (Lox) and kerosene as propellants. $LN_2$ injectors and an extended chamber for mixing were installed at the end of the ordinary LRE combustion chamber, and a nozzle was installed after the chamber for mixing. First, an ignition test of the liquid rocket engine was conducted to verify the stable combustion process. Next, a hot firing test was performed step-by-step for safety. Finally, the test was performed for 20 s. The results showed that the combustion gas of the LRE could be successfully cooled by using $LN_2$.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.4
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• pp.91-101
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• 2004

With the mathematic linear model of a combustor which consists of a combustion chamber and injectors, the analysis of low frequency dynamic characteristics of a liquld-propellant rocket engine combustor was performed. Propellant mass flowrate was varied by combustion chamber pressure feedback, therefore low frequency oscillation was appeared. Increasing the time constant of a combustion chamber and injector pressure differences and decreasing combustion time delay increased the combustor system stability. The variation of injector time constant little affected stability. The system was always stable, when there was no combustion time delay. Increasing combustion time delay decreased oscillation frequency and damping ratio, and the system eventually became unstable.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.6
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• pp.79-87
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• 2003

Application of combustion stabilization devices such as baffle and acoustic cavity to liquid propellant rocket engine is investigated to suppress high-frequency combustion instability, i.e., acoustic instability. First, these damping devices are designed based on linear damping theory. As a principal design parameter， damping factor is considered and calculated numerically in the chambers with/without these devices. Next, the unbaffled chambers with/without acoustic cavities are tested experimentally for several operating conditions. The unbaffled chamber shows the peculiar stability characteristics depending on the operating condition and it is found to have small dynamic stability margin. As a result, the acoustic cavity with the present design has little stabilization effect in this specific chamber. Finally， stability rating tests are conducted with the baffled chamber, where evident combustion stabilization is observed, which indicates sufficient damping effect.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.1-1
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• 2000

액체로켓엔진에 있어서 연소실로 공급된 추진제의 안정적인 점화를 위해 추진제 공급의 선점 시간을 결정하기 위한 실험이 수행되었다. 사용된 추진제는 Jet A-1과 액체 산소이고 추진제의 공급은 가압 방식이다. 135$^{\circ}$의 각을 갖고 배열된 인젝터는 FOOF 타입의 비동류형 충돌형 인젝터이고 연소실 압력이 200psi가 되도록 설계되었다. 현재의 실험은 점화원으로서 TEAL(triethylaluminum)을 사용하여 쿼드렛 타입의 점화기의 안정적 점화 여부를 검증하는 것도 포함된다. 점화 특성 파악을 위해 인젝터 상류의 매니폴드 압력, 연소실 압력이 측정되었고 점화 과정 및 정상 상태로의 천이 과정에 대한 간접적 증거로서 화염 길이가 측정되었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.203-207
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• 2005

An experimental study was carried out to investigate the effect of film cooling in the thrust chamber of liquid rocket using LOx and Kerosene as propellant. The heat fluxes were obtained from the measured wall temperature to the axial direction of thrust chamber for different type of coolant, the various O/F ratio, mass flow rate and the location of the film cooling injector. A thin wall combustion chamber and nozzle were used to obtain the heat flux.