• Proceedings of the Korean Society of Marine Engineers Conference
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• 2006.06a
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• pp.21-22
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• 2006

디젤엔진에서 배출되는 배기가스 중의 주요 오염물질 중의 하나인 NOx(질소산화물)는 대부분 고온의 연소 과정에서 발생하고, 발생량은 연소온도에 따라 결정되는 것으로 알려져 있다. 또한 연료의 연소 중에 물이 첨가되면 연소공기의 비열 증가에 의하여 연소온도가 감소하여 NOx 발생량이 급격하게 감소하게 되는데, 연소실에 물을 첨가하는 방법으로는 유화연료, 직접물분사, 흡기가습 등이 있다. 이중 흡기가습은 구조가 간단하면서 NOx 저감효율이 가장 높은 것으로 알려져 있다. 본 연구는 당사 고유모델 중형엔진인 힘센엔진에 흡기가습 기술을 적용하여 연소성능 및 NOx 저감효과 등을 시험하고, 흡기가습 시스템의 상용화 모델 개발을 위한 기초 데이터를 확보하기 위해 수행되었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.04a
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• pp.2-2
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• 1998

현대우주항공(주)가 미국의 AlliedSignal사와 함께 국제 공동 개발중인 10MW급의 ASE120 엔진은 항공용 엔진을 산업용으로 개조한 개조형 엔진으로서 희박 예혼합 예기화(Lean Premix prevaporization) 방식의 연소기를 쓰고 있다. 이 연소기는 연소에 관여하는 공기량을 부하에 따라 가감하여 일정 공연비를 유지하는 air staging법을 사용하고 있으며 이로써 연소화염온도를 일정치로 조절하여 연소중 생성되는 유해가스의 양을 목표치 이하로 제어한다. 연소화염온도 설계치는 2912$^{\circ}$F이며 배기가스 발생량은 NOx, CO모두 궁극적으로 10ppmv 이하를 목표로 하고 있다. 이러한 건식 저 배기가스(Dry Low Emission) 연소기가 그 역할을 다하기 위하여는 양호한 혼합기를 확보하는 것이 선결 문제이다. 본 연구소에서는 두 개의 혼합기(mixing can)가 180$^{\circ}$ 간격으로 환형 연소기(annular type)에 접선 방향으로 설치되어 대칭을 이루고 있고 혼합기의 혼합성능을 측정하기 위하여 제작된 시험장치에는 하나의 혼합기만을 쓰고 있다.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.2
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• pp.17-25
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• 2009

A typical unsteady internal ballistic analysis model was proposed to take account of the erosive burning with the variance of local velocity and pressure along the grain surface of a solid rocket combustor. To validate the model of concern in the study, both cases of non-erosive and erosive burning were compared with the previous researches with marginal accuracy. It was quantitatively investigated that the combustion pressure, grain length, initial temperature, and vaporization temperature of propellant affect the erosive burning characteristics.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.29-33
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• 2005

In the fuel of the solid fuel ramjet there are metal particles in order to improve the Isp like as solid rocket propellants. Because of the short combustion residence time these metallized fuels have low combustion efficiencies. Therefore it is necessary to increase the combustion efficiency and the inlet air temperature does an important role to this. The effect of the inlet air temperature to the performance is investigated through the semi-empirical method by adopting the experimental combustion efficiency. There are two factors to affect the inlet temperature, free stream temperature and the flight Mach number.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.271-274
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• 2007

In the fuel of the solid fuel ramjet there are metal particles in order to improve the Isp like as solid rocket propellants. Because of the short combustion residence time these metallized fuels have low combustion efficiencies. Therefore it is necessary to increase the combustion efficiency and the inlet air temperature does an important role to this. The main factors to affect the inlet air temperature is the free stream temperature and the flight Mach number. Also the flow velocity in the combustor does an important role, therefore entire range of the air flow; from the stagnation to the sonic velocity in the ramjet combustor is considered.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.285-289
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• 2017

Laser-induced breakdown spesctroscopy (LIBS) is a technique that complements the disadvantages of conventional laser-based combustion diagnosis techniques such as weak signal strength, complex equipment configuration, and low accuracy. In this study, basic research was carried out to measure the combustion gas temperature of scramjet engines using LIBS. Spray flames were generated from Jet A-1 fuel used in scramjet engines and gas temperatures were measured at the top of the flames with a calibrated thermocouple. The LIBS signals were acquired at the same points as the temperature measurement positions of the thermocouple. The LIBS spectra were analyzed to obtained a calibration curve between the LIBS signal and the reference temperature measured at the thermocouple. Therefore, it was confirmed that the combustion gas temperature can be measured in-situ using LIBS.

• 한국연소학회:학술대회논문집
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• 2002.06a
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• pp.237-246
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• 2002

가압유동층연소로(bed dia. 0.17m, freeboard dia. 0.25, total height 5m)에서 국내무연탄을 연소시켜 이에 대한 탈황특성을 고찰하였다. 실험은 압력($2{\sim}6atm$), 요동층온도(($850{\sim}950^{\circ}C$), 과잉공기(10, 20, 30,%)등의 조건과, 탈황을 위한 Ca/S몰비(($0.8{\sim}4.8$)가 탈황특성에 미치는 영향을 고찰하였다. 결과적으로, 본 연구의 실험범위에서 연소효율은 $80{\sim}99%$를 보였고, 연소온도, 압력 그리고 과잉공기가 증가 할수록 증가하였다. 배가스중의 $SO_2$배출농도는 압력, Ca/S몰비가 증가함에 따라 감소하였다. 탈황율은 상압에서 층(bed)온도의 증가에 따라 감소하였다. 운전압력이 증가함에 따라 탈황율의 감소폭이 둔화되었다. 과잉공기가 증가함에 따라 탈황율은 증가하는 경향을 나타냈다. 각각의 운전압력에서 과잉공기의 증가에 따라 약 10%의 증가폭을 보였다. 국내무연탄을 연소하는 경우 운전압력 4atm일 때 Ca/S몰비는 4이상 주입하여야 하고, 6atm일 때 Ca/S 몰비가 2.5이상주입하여야 150ppm이하를 보여 배출규제치를 만족하는 것을 보였다.

• Fire Science and Engineering
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• v.13 no.2
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• pp.12-17
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• 1999

We intended to investigate combustion properties of rice bran dust. Combustion properties of h rice bran dust according to size distribution and amount were measured as temperature v variation with time using spontaneous ignition apparatus. Moreover, combustion properties w with blowing or without blowing condition were checked in order to investigate combustion p properties in spontaneous ignition apparatus according to flow condition of air. A As the mass and size of rice bran dust was increased, i띠ti외 smoldering temperature was l lowered. All of combustion forms were smoldering combustion. Initial smold얹ing temperature w was slightly lower with blowing condition than without blowing condition in spontaneous i ignition apparatus, which condition made heating value high.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.272-275
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• 2007

The combustion efficiency of the solid fuel ramjet is affected by the inlet air temperature. And this inlet air temperature is dependent on the flight Mach number and the environment air temperature. If the flight altitude is changeable, the inlet air temperature and also the air density vary. The performance efficiency is investigated with this variables related to the combustion efficiency.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.254-257
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• 2017

As a part of the development of aircraft gas turbines, combustion performance tests have been conducted in the single combustor sector. The effects of change in the amount of air supplied to the main combustion zone to the performance of the combustor, such as a pollutant emission, a liner temperature distribution and an exit temperature patterns, were studied. Emissions of CO and NOx increased with the main air-ratio and exit temperature pattern was improved. When changing the pattern of the dilution holes, it was shown that the temperature patterns on the exit plane of the combustor and the surface of liner changed depending on the main flame structure and mixing with diluent air. These observations will be applied to combustor liner designs to improve combustor durability and emissions reduction performance.