• Journal of the KSME
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• v.30 no.6
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• pp.521-534
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• 1990

유동층 연소방식을 이용한 열병합설비는 상당수가 전세계적으로 성공리에 운전되고 있으며, 연료의 폭넓은 수용성, 저온연소에 기인한 저공해 특성으로 인해 기존연소 방식보다 월등한 강 점이 인정되고 있다. 따라서 에너지 활용의 극대화와 환경오염의 최소화라는 두가지 명제를 만족시키는 금세기 최대의 매력적인 석탄 연소 방법으로서 유동층 연소 기술은 지속적인 확산이 예상된다. 그러나 그 동안의 문제가 제작자와 사용자의 노력에 의해 거의 해결되었다고는 하나, 아직도 대형화 및 기본설계상의 문제가 부분적으로 해결되어야할 숙제로 남아 있다. 최근의 추세는 다양한 형태의 설계개념이 차츰 서로 비슷해지는 추세로서, 이는 구체적인 설계과정에서 최적 시스템으로 취합되는 경향을 나타내고 있다. 각공정에 맞는 최적 시스템/최적 설계를 도 입하기 위해서는 각 제작자의 독특한 시스템에 대한 검토 분석이 있어야 하며, 사용코자하는 연료와 석회석의 물리화학적 특성을 사전에 분석하여 선택코자 하는 유동층 시스템과의 적합성 여부에 대한 사전 검토가 요망된다.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.2
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• pp.6-11
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• 2000

In the pressurized propellant feed system of liquid rocket, feed pressure is decided chamber pressure of normal combustion state. However, during ignition period the initial chamber pressure is atmosphere. So, it may have overflow, hard-start and even critical damage of engine. This paper proposes an improved propellant feed system for the stable combustion of liquid rocket. Hot test were already performed to verify the presented propellent feed system. The proposed propellant feed system uses two steps - pre and main combustion - to prevent large pressure increase and uses cavitating venturis for stable flow rate in whole combustion. This system feeds the flow rate lesser than the designed flow rate, so combustion pressure reached pre-combustion pressure. Cavitating venturis offer unique flow control capabilities at normal and abnormal combustion state, because flow rate is solely dependent on upstream absolute pressure and fluid properties, but independent on downstream condition.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.88-94
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• 2002

For the pressurized propellant supply system of liquid rocket, feed pressure is determined with respect to the chamber pressure of normal combustion state. However, during ignition period the initial chamber pressure is atmosopheric. This may cause overflow, hard-start and even critical damage for the engine. This paper proposes an improved propellant feed system for the stable combustion of liquid rocket. The proposed system utilizes the cavitating venturi to provide stable mass flow rate. Cavitating venturi offers unique flow control capabilities at normal and abnormal combustion state, because flow rate is soley dependent on the upstream absolute pressure and fluid properties, but independent on th downstream condition. Experimental variables are propellant feed pressure and chamber pressure. The effectiveness of cavitating venturi increased when the ratio of actual feed pressure to the cavitating venturi design pressure is increased. It is also found that Kerosene if more effective to supply stable mass flow rate than LOx.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.892-897
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• 2011

The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility(CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The fuel supply system modeling using AMESim was performed based on the results of the detailed design, and the fuel supply characteristics was analyzed in this paper.

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.574-577
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• 2012

Thrust measuring is one of the crucial factor to decide the performance of a liquid rocket engine when the engine development test, especially for the combustion chamber, is implemented. Calculating the thrust from a combustion pressure is used when direct measuring the thrust is impossible, but direct measuring the thrust is necessary and various methods for doing it more precisely should be considered. This paper introduces the preliminary design concept about the new thrust measurement system for the vertical firing test stand, which is introduced domestically for the first time, of a liquid rocket engine combustion chamber.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.206-209
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• 2010

The visualization device for hybrid rocket is fabricated to investigate the combustion phenomena. Visualization device were composed with ignition system, oxidizer supply system, control system and data acquisition system, combustion visualization system. GOX as oxidizer and HDPE, Paraffin-LDPE Blending, Paraffin sd were used. As results, combustion phenomena and fuel droplet entrainment were observed.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1996.10b
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• pp.167-170
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• 1996

석탄의 고압 유동층연소는 기존의 PC 보일러보다는 저온 연소로써 NOx의 발생이 억제되며 탈황제를 동시에 주입하여 SOx 발생을 줄일 수 있는 것이 큰 잇점으로서 석탄 신에너지 개발에 유력한 시스템이다. 본 시스템에서 집진은 연소가스 중의 입자가 고온고압에서 고속으로 터빈에서 충돌될 때 일어나는 터빈의 마모, 침식, 및 부식 등을 방지하기 위하여 필수적이다. PFBC 연소기에서 연소된 가스가 정제후에 바로 가스터빈에 주입되기 때문에 PFBC의 집진은 매우 가혹한 조건이다. 뿐만 아니라 차세대에 더욱 높은 열효율 향상과 가스터빈의 수명 연장을 위하여 집진조건이 더욱 가혹해지고 엄격해질 전망이다. 그 동안 PFBC 집진의 연구가 다방면으로 진행되고 있으나 상용화를 위한 준비가 아직 갖추어지지 않았으며 모든 집진 시스템이 잠정적인 문제점을 갖고 있다. 그 중에서도 세라믹 캔들 필터는 성능이 우수하고 가장 많은 운전경험을 갖고 있기 때문에 가장 가까운 시기에 상용화에 성공할 수 있는 집진 시스템이다. 본 고에서는 세라믹 캔들필터 개발의 현황과 핵심 개발과제에 대하여 논의코자 했다.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.1848-1849
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• 2011

Oxy-PC 발전시스템은 화석 연료를 연소하는 과정에서 발생하는 다량의 이산화탄소를 회수처리 하기위해 고려되고 있는 방법 중 하나이며, 신규 발전 시스템은 물론이며 기존 발전시스템에도 개조 과정을 거쳐 적용이 용이한 장점이 있다. 하지만 현재 국내에 해당 시스템의 적용 사례는 없을 뿐만 아니라 설계 기술의 확보도 부족한 실정이다. 따라서 순산소 연소 시 발생하는 복합적인 문제를 사전에 예측하고 시스템 구현 과정에서 발생되는 시행착오를 최소화하기 위해서는 순산소 연소 공정모델을 반영한 Dynamic Engineering Simulator 개발이 요구된다. 본 논문에서는 Oxy-PC 발전 시스템의 특징을 기존 공기 연소 발전 시스템과 비교하여 설명하고 Oxy-PC 발전 플랜트용 Dynamic Engineering Simulator 개발 절차에 대해 기술한다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.4
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• pp.405-412
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• 2012

In the MCFC power generation system, the combustor supplies a high temperature mixture of gases to the cathode and heat to the reformer by using the off-gas from the anode; the off-gas includes high concentrations of $H_2O$ and $CO_2$. Since a combustor needs to be operated in a very lean condition and avoid local heating, a catalytic combustor is usually adopted. Catalytic combustion is also generally accepted as one of the environmentally preferred alternatives for generation of heat and power from fossil fuels because of its complete combustion and low emissions of pollutants such as CO, UHC, and $NO_x$. In this study, experiments were conducted on catalytic combustion behavior in the presence of Pd-based catalysts for the BOP (Balance Of Plant) of 5 kW MCFC (Molten Carbonate Fuel Cell) power generation systems. Extensive investigations were carried out on the catalyst performance with the gaseous $CH_4$ fuel by changing such various parameters as $H_2$ addition, inlet temperature, excess air ratio, space velocity, catalyst type, and start-up schedule of the pilot system adopted in the BOP.