• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.79-82
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• 2011

An afterburning device was developed to safely treat unburnt gases of fuel-rich condition discharged by a gas generator. Hot-firing tests for a subscale gas generator were carried out to investigate operation and safety of the afterburning device. When supplying additional liquid oxygen, the length of the afterburning flame was significantly reduced.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.69-72
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• 2011

Hot-firing tests were performed on the third sub-scale gas generator for development of a 75 ton-class liquid rocket engine. This paper deals with the analysis results of low-frequency combustion instabilities that were encountered during combustion tests of the gas generator. The low-frequency pressure fluctuations seem to be related to chamber pressure and pressure drops through oxidizer/fuel injectors.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.10-13
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• 2010

Low pressure combustion tests for TDM(Technology Demonstration Model) of 75 tonf thrust chamber were performed. It has design chamber pressure of 60 bar, propellant mass flow rate of 243.6 kg/s. Due to the limitation of the current firing test facility in Korea, the combustion tests were conducted to verify the operation and the combustion performance at low pressure condition (30 bar, 121.8 kg/s). All the tests had been successfully executed without the damage of the hardware. These test results can be used as fundamental data to predict the combustion performance at design point condition for 75 tonf thrust chamber.

• 방재와보험
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• s.5
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• pp.76-80
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• 1976

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.6
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• pp.32-40
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• 2012

For predicting eigenfrequency and initial growth rate of combustion instabilities in lean premixed gas turbine combustor, linear thermoacoustic analysis model was developed in the current paper. A model combustor was selected for the model validation, which has well-defined inlet and outlet conditions and a relatively simple geometry, compared to the combustor in the previous works. Analytical linear equations for thermoacoustic waves were derived for a given combustion system. It was found that the prediction results showed a good agreement with the measurements, even though there was underestimation for instability frequencies. This underestimation was more obvious for a longer flame (i.e. wider temperature distribution) than for a shorter flame.

• 한국방재학회:학술대회논문집
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• 2011.02a
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• pp.63-63
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• 2011

화재란 사람의 의도에 반하거나 고의에 의해 발생하는 연소현상으로서 소화시설 등을 사용하여 소화할 필요가 있는 것을 말한다. 사람의 의도에 반한다고 하는 것은 과실에 의한 화재를 의미하며 화기취급 중 발생하는 실화뿐만 아니라 부작위에 의한 자연발화도 포함하며, 고의에 의한다고 하는 것은 일정한 대상에 대하여 피해발생을 목적으로 화재발생을 유도하였거나 직접 방화한 경우를 말한다. 연소현상이라 함은 가연성 물질이 산소와 결합하여 열과 빛을 내며 급속히 산화되어 형질이 변경되는 화학반응을 말한다. 소화시설 등을 사용하여 소화할 필요가 있다는 것은 화재란 연소현상으로서 소화의 필요성이 있어야 하며 소화의 필요성의 정도는 소화시설이나 그와 유사한 정도의 시설을 사용할 수준 이상이어야 한다. 화재원인조사란 발화부를 판단하고 화재에 이르게 된 발화원을 규명하며, 발화부로부터 연소확대된 경과를 조사하는 일련의 행위로서 화재원인조사시 가장 중요한 사항은 발화부 판단인 바, 이는 화재원인이 발화부에만 존재하기 때문이다. 최근에는 다양한 소재의 사용으로 인해 일단 화재로 진행될 경우 인명 및 재산상 피해가 증가하게 되어 있으며, 이로 인해 화재조사시 화학, 물리, 전기, 건축, 기계, 소방 등 다양한 지식과 화재현장에 대한 이해가 요구된다. 화재현장 조사시 발화부 판단의 과학적 접근은 매우 중요한 것으로서, 화재원인의 명쾌한 규명으로 책임한계 구분은 물론, 유사사고의 재발방지를 위한 연구가 필요하다. 본 연구에서는 기 발생한 화재사례에서 얻은 화재패턴을 분석하여 얻은 자료를 통해 발화부를 판단할 수 있는 조사방법을 다음과 같이 제시하였다. 1) 화재시 열전달과 화염확산 과정에서 건축구조물, 내장재, 집적물 및 각종 설치물의 구조, 재질 등에 따라 다양한 화재패턴을 형성하게 됨을 알 수 있다. 2) 화재패턴의 종류로는 화재플럼에 의한 삼각형, 주상, V, U 패턴 등이 있으며, 연소 생성물인 화염, 연기, 열 등에 의해 다양한 형태를 보임을 알 수 있다. 3) 위와 같은 결과를 종합하여 연소의 상승성, 불꽃 및 연기 흔적, 열에 의한 흔적 등에 의해 연소의 방향성을 알 수 있다. 4) 결국 화재현장에서 명확한 화재원인을 규명하기 위해서는 화재패턴에 의해 연소확대과정을 역으로 추적하여 발화부를 결정한 다음, 발화부내에서 화재원인을 찾아내야 할 것이다.

• Applied Chemistry for Engineering
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• v.21 no.5
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• pp.553-558
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• 2010

To solve the problems of the low combustion activity of Korean anthracite and the abundant loss of unburned carbon in fly ash, pellet coal was fabricated from coal fines and fly ash, and the mixed combustion of coarse coal with the pellet coal was examined in the circulating fluidized bed combustor of a 0.1 MW scale test unit. In the combustion of the raw coal only, the significant amount of coal fines was entrained, resulting in overheat at the top of the combustor. With the coarse coal that most fines were eliminated, however, the combustion temperature was maintained stable. The mixed combustion of coarse and raw coals was also feasible even though it often went unstable. The mixed combustion of the coarse coal with the pellet coal was as stable as the coarse coal combustion, showing a promise that the combustion of the Korean anthracite in commercial circulating fluidized bed boilers could be further enhanced.

• Proceedings of the KIEE Conference
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• 2001.07d
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• pp.2160-2162
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• 2001

화력 발전소의 주 연료로 사용되는 석탄은 1차 공기에 의해 노내로 이송되어 연소되게 된다. 연소에 필요한 1차 공기량은 연소되는 탄의 종류와 급탄기로 보내는 급탄량에 의해 결정되고, 1차 공기량 제어는 연소에 영향을 주며, 역화와 과열 방지를 위해 적절한 제어가 요구된다. 특히 단일 탄종이 아닌 여러 탄종을 연소하는 화력 발전소에서는 탄종에 따라서 그리고 연소되는 탄량에 따라서 미분기로 들어가는 1차 공기량을 변화시켜야만 한다. 본 논문에서는 2종류의 탄을 연소하는 발전소에 대해 연소탄종에 따른 1차 공기량 제어 로직을 구현하고, 구현한 로직에 의한 1차 공기량 제어 결과를 통해 구현한 제어 로직의 효용성을 보인다.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.1
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• pp.89-96
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• 2013

Combustion pressures were measured to study combustion stability for an oxygen rich preburner by both of static and dynamic pressure sensors. The resolutions of each static and dynamic pressure sensor are the 1,000 Hz and 25,600 Hz, respectively. The nominal combustion pressure of the preburner was 200 bar but 80 bar was used at the several initial tests for the safety reason. Two stage ignition was applied to reduce the ignition impact for every tests including the tests with 200 bar combustion pressure. The tests lasted for 10 sec. max. and a little fluctuations of pressure was observed during the main mode. The measured pressures were studied by FFT analysis and no noticeable frequency coupling was found. Thus the preburner can be regarded as stable and it can be utilized for further study on staged combustion cycle liquid rocket engine.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.5
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• pp.31-36
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• 2007

Combustion performance characteristics of subscale high-pressure combustor were investigated at 70 bar combustion pressure. All tests were successfully performed without any damage on the combustor. The mixing characteristics and distribution pattern of the injectors were found to have considerable influence on the combustion performance. The characteristic velocity of the combustor was higher in the injector with internal mixing than that of external mixing and in the injector with smaller mass flowrate. The pressure fluctuations at the propellant manifolds and the combustion chamber were measured to be less than 3% of the mean combustion pressure to meet the combustion stability criterion and to prove stable combustion characteristics of the combustor.