• Proceedings of the Korean Radioactive Waste Society Conference
• /
• 2007.05a
• /
• pp.151-152
• /
• 2007

ACP(Advanced Spent Fuel Conditioning Process)의 금속전환로에 $U_{3}O_{8}$을 공급하기 위하여 20 kgHM/batch의 $UO_{2}$ 펠릿(pellets)을 처리할 수 있는 공기산화로가 개발되고 있다. 그림 1은 산소농도 조절이 가능한 공기산화로이다. 공기산화로 이전의 공정인 슬리팅 장치에서 탈피복된 $UO_{2}$ 펠릿은 공기산화로로 운반되고, $500^{\circ}C$온도에서 공기를 공급하여 일정한 입도범위의 균질한 $U_{3}O_{8}$을 만든다. 그리고 다음공정의 금속전환장치로 이동된다. 본 논문에서는 모의연료의 산화에 대한 정확한 산소농도를 측정하고자 한다. 이를 위해서 갈바닉 센서와 지르코니움 센서가 사용되었고, 그 특성이 비교되었다. 14종의 금속 산화물이 혼합된 모의연료를 제조하여 산화실험이 수행되었으며, 시간변화에 따라 산소농도가 측정되었다. 산소농도 컨트롤러와 산소 센서를 사용한 공기산화로는 산소조절기에 의해 산소농도 100%까지 측정될 수 있다. 그림 2는 공기산화로의 산소농도를 조절할 수 있는 산소농도 측정시스템이다. 유량조절기(Mass Flow Controller)를 사용하여 질소와 산소의 혼합비를 변화시킬 수 있다. 또한 산소농도 측정시스템은 측정된 산소농도 값을 이용하여 $UO_{2}$의 산화시간을 계산하기 위하여 제작하였다. 산화시간 계산방법은 다음과 같다. 산소와 질소의 가스는 각각 40 L의 압력 봄베에 의해서 산소농도를 조절할 수 있는 공기산화로의 산소농도 측정시스템 안으로 유입된다. 유입된 산소와 질소의 배합은 컨트롤시스템 안에 있는 산소 유량조절기와 질소 유량 조절기를 사용하여 조절하며, 일정하게 혼합된 산소농도는 장치의 입구와 출구에서 산소 센서에 의해서 측정된다. 투입된 $UO_{2}$ 펠릿이 $500^{\circ}C$에서 반응하면서 공기산화로의 내부에 있는 산소농도가 감소된다. 이때 초기에 같았던 입력과 출력 농도가 시간의 흐름에 따라 감소되며, 펠릿이 완전히 산화됨과 동시에 출력 산소농도가 입력농도와 다시 같아질 때까지 소요된 구간이 산화시간이 된다.

• Journal of Energy Engineering
• /
• v.15 no.3 s.47
• /
• pp.166-173
• /
• 2006

R134a is considered as an alternative refrigerant to R22 for air conditioners. An experimental investigation was made to study the characteristics of the heat transfer and pressure drop for R134a flowing in a fin-and-tube heat exchanger used for commercial air-conditioning units. Experiments were carried out under the conditions of inlet refrigerant temperature of $60^{\circ}C$ and refrigerant mass fluxes of $150,\;200,\;and\;250\;kg/m^{2}s$. The inlet air has dry bulb temperature or $35^{\circ}C$, relative humidity of 40% and air velocity varying from 0.68 to 1.6 m/s. Experiments show that air velocity decreased by 5.9% is needed for R134a than that of R22 while pressure drop for R134a was $18.1{\sim}20.4%$ higher than that of R22 for the degree of subcooling $5^{\circ}C$. The results are useful in designing more compact and effective condensers for various refrigeration and air conditioning systems using refrigerant R134a.

• Journal of Advanced Marine Engineering and Technology
• /
• v.35 no.6
• /
• pp.765-772
• /
• 2011

In this research, the fuel cell system model capable of generating codes in real time was developed to construct of a HIL (Hardware-In-the-Loop) for a SOFC-powered ship. Moreover, the effects of the distribution of the exhaust gas flow rates in a stack, the flow rates of fuels and temperature of air supplied on the temperature characteristics of fuels supplied to the cathode and the anode, the output power of the stack and system efficiency are examined to minimize the temperature difference between fuels supplied to the stack used in a 500kW SOFC system using methane as a fuel. As a result, the temperatures of fuels supplied to the cathode and the anode maintain at 830K when the opening factor of three-way valve located at outlet of turbine is 0.839. Also the process for optimization of methane flow rate considering the fuel cell stack and system efficiency is required to increase the temperatures of fuels supplied to the stack.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2003.10a
• /
• pp.13-19
• /
• 2003

A supersonic ground test facility to develop Ramjet and SCRamjet(Supersonic Combustion Ramjet) engine should be able to simulate high altitude and high Mach number conditions including air total pressure, oxygen level and specific heat ratio at the combustion chamber entrance. The test facility also should simulate the effect of oblique shock wave caused by the flight vehicle. The test facility developed in this study is supersonic free-jet blowdown type, which consists of high pressure air supply source(maximum pressure=32MPa), air heater(vitiation type), supersonic diffuser, ejector, and test chamber(nozzle exit dimension=200mm$\times$200mm).

• Journal of the Korean Society of Propulsion Engineers
• /
• v.7 no.4
• /
• pp.53-62
• /
• 2003

A supersonic ground test facility to develop Ramjet and SCRamjet(Supersonic Combustion Ramjet) engine should be able to simulate high altitude and high Mach number conditions including air total pressure, oxygen level and specific heat ratio at the combustion chamber entrance. The test facility also should simulate the effect of oblique shock wave caused by the flight vehicle. The test facility developed in this study is supersonic free-jet blow down type, which consists of high pressure air supply source(maximum pressure=32MPa), air heater(vitiation type), supersonic diffuser, ejector, and test chamber(nozzle exit dimension=200mm${\times}$200mm).

• Korean Chemical Engineering Research
• /
• v.55 no.4
• /
• pp.548-555
• /
• 2017

This study investigated the influence of air staging on combustion and NOx emission in a tangential-firing boiler at a 560 MWe capacity. For air staging, the stoichiometric ratio (SR) for the burner zone was varied from 0.995 to 0.94 while the overall value was fixed at 1.2. The temperature and heat flux in the burner zone and upper furnace corresponded to the distribution of SR, while the total boiler efficiency remained similar. The NOx emission at the furnace exit was reduced by up to 20% when the SR in the burner zone decreased to 0.94. However, the amount of unburned carbon and slagging propensity was not noticeably influenced by the changes in the SR of the burner zone. Therefore, it was favorable to lower the SR of the burner zone for reduction of NOx emission.

• Journal of the Korean Institute of Gas
• /
• v.23 no.3
• /
• pp.1-6
• /
• 2019

The purpose of the present study is to elucidate flue gas recirculation device for reduction of nitrogen oxides using coanda nozzle without adopting additional power driving fan in a waste incinerator. The characteristics of the exhaust gas recirculation flow rate and the average temperature change at the outlet of the mixed gas were investigated according to the change of air supply nozzle gap and the position of air supply nozzle. When the gap of the air supply nozzle was changed to 3.22, 4.03, and 4.84 mm, the largest recirculation flow ratio, which is the ratio of exhaust gas recirculation flow rate and air supply flow rate, was 2.227 for the case with 3.22 mm and its mean temperature at outlet was $594.8^{\circ}C$. When the position of the air supply nozzle changes to the front position, neck position, and expansion position of the coanda nozzle neck, the recirculation flow ratios at the forward position and the neck position were nearly almost the same value, 1.843, and 1.696 at the expansion position, their mean temperatures were $559.8^{\circ}C$ and $544.3^{\circ}C$, respectively.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.231-235
• /
• 2009

The mainly objectives of this study was a combustion dynamics and instability characteristics in a model dump type combustor which is scale down of GE 7FA+e DLN 2.6 gas turbine combustor with running at Seo-Inchon combined cycle power plant. Model gas turbine injector has 2-stage swirl vane and it's reduced 1/3 size of the original one. The shape of plenum and combustor were designed for similar acoustic characteristics. As the result, this research have been shows the peak frequency of model combustor was changed quarter-wave mode to Helmholtz resonator mode in plenum and longitudinal mode in dump combustor at unstable flame conditions caused by the different of combustor temperature and fuel-air mixture distributions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• v.y2005m4
• /
• pp.237-242
• /
• 2005

The energy consumed by compressor in gas turbine is equivalent to $30\sim50\%$ of energy produced by turbine and, therefore, research on reducing compression work is important in increasing the efficiency of gas turbine. One of the method to reduce the compression work is to inject small water droplets into the compressor. This method decreases the compression work by decreasing the compressor exit temperature through the evaporation of water. Researches on wet compression, up to now, are focused on thermodynamic analysis of wet compression where the decrease of exit flow temperature and compression work is demonstrated. This paper presents an thermodynamic and aerodynamic analysis of wet compression in centrifugal compressor for microturbine.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.40 no.4
• /
• pp.309-315
• /
• 2012

Catalytic combustion is generally accepted as one of the environmentally preferred alternatives for heat and power from fossil fuels, as it has the advantage of stable combustion under very lean conditions with such low emissions as UHC, CO, and NOx. In this work, therefore, comparative numerical studies on the catalytic combustion behaviors over Pd-based catalysts have been conducted with the gaseous $CH_4$, $C_2H_6$, and $C_3H_8$. In the following, after introducing the governing equations with 1D channel and Langmuir-Hinshelwood models, numerical investigations on the catalyst performance are conducted by changing such various parameters as inlet temperature, excess air ratio, and space velocity. The numerical results show that outlet temperature and conversion of $C_3H_8$ are highest among others because of its chemical structure and reactivity.