• 한국신재생에너지학회:학술대회논문집
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• 2008.05a
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• pp.186-189
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• 2008

Solar simulator를 이용한 메탄의 수증기 개질은 집광된 태양에너지를 이용하기 위한 목적으로 수행되었다. 본 연구에서는 이와 같은 태양열에너지의 화학적 축열을 실시하기 위해 Solar Simulator를 이용한 메탄의 수증기 개질을 연구하였다. 태양열 모사 램프로 1.2kW급 Xenon-arc lamp를 사용하였다. 반응기는 앞면의 Quartz Window와 촉매지지층으로 구성되어 있다. 램프의 빛은 Quartz Window를 통하여 촉매층에 직접적으로 방사되고, 방사된 빛으로 촉매지지층에서 흡열반응이 일어난다.메탄의 수증기개질 반응은 고온에서 일어나기 때문에 촉매지지체를 열에 강한 SiC로 만들어진 Ceramic foam을 사용하였다. 이 촉매지지체에 촉매를 Wash-coat하여 사용하였으며, 담지된 촉매는 Ni을 활성성분으로 하는 ICI 46-6을 사용하였다. 반응기는 318 SUS 재질로 제작되었으며, 반응기 외부는 Insulation을 하여 열손실을 감소시켰다. 실험은 온도와 공간속도에 따른 Solar Steam reforming의 반응특성을 분석하였다.

• 기계와재료
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• v.24 no.2
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• pp.80-93
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• 2012

본 연구는 5,000PS급 선박용 SCR 촉매시스템에 관한 내부 유동특성을 전산유체역학(CFD)을 통해 예측하고 설계에 반영하기 위한 기초를 확보하기 위함이다. 따라서 SCR 촉매반응기 내부 유동특성을 수치해석하기 위한 기법을 소개하였고, 촉매 Cell에 대한 수학적 모델링을 제시한 후 SCR 촉매시스템에서 NOx를 환원시켜 주는 촉매담체에 대한 압력강하를 실험과 수치해석을 통해 비교하였다. 그 결과 수치해석 결과가 실험에 매우 근접함을 확인할 수 있었다. SCR 촉매반응기에 대한 유동특성을 수치해석을 수행하여 각 지점에 대한 압력과 속도분포를 확인하였다. 또한 촉매 담체로 배기가스가 유입되는 입구부의 유동균일도를 예측하기 위해 Inlet pipe의 $90^{\circ}$ 각도에서 유입길이를 변화시켜 수치해석을 수행하였다. 그 결과 각도와 길이에 영향을 받는 것으로 나타났다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.329-334
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• 2005

The rocket grade hydrogen peroxide has been widely used as a monopropellant in propulsion systems. Conventional decomposition of hydrogen peroxide, however, requires preheating before feeding into the reactor. In the present paper, we described an experimental study of a catalytic reactor bed that employs multiple catalysts to enhance the low temperature response in the vicinity of the reactor inlet. $K_2MnO_4$ is experimentally chose as the inlet catalyst from the candidates of silver, platinum, $La_{0.8}Sr_{0.2}CoO_3(LSC),\;and\;K_2MnO_4$. We developed new synthesis and coating method using modified alumina sol-gel method to strengthen the adhesion of $K_2MnO_4$ catalyst. from the vaporizer experiment with hydrogen peroxide at room temperature, satisfactory vaporizing performance was measured.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.185-189
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• 2007

A hydrogen peroxide monopropellant thruster has been developed to research performance characteristics of silver catalyst bed. The experiment data and evaluation result from the fire tests with five catalyst beds are presented A scheme of catalyst arrangement is presented for high concentrated hydrogen peroxide.

• 한국신재생에너지학회:학술대회논문집
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• 2010.11a
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• pp.113.1-113.1
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• 2010

본 연구에서는 중 소형 SOFC에 적용할 수 있는 연료 변환 시스템으로 자체 기동 및 독립운전이 가능한 천연가스 자열개질(ATR) 반응기를 $10Nm^3/hr$급으로 개발하고자한다. 설계된 천연가스 자열개질기는 자열개질 촉매를 코팅한 금속 모노리스형 촉매체를 반응기 내에 장착함으로써 반응열을 신속하게 제거 또는 공급할 수 있는 시스템으로 구성되었다. 이는 금속 모노리스의 뛰어난 열전도 능력에 의해 반응기 내의 촉매층 전체 온도 분포를 균일하게 유지할 수 있는 저에너지형 자열개질 반응기이다. 또한 빠른 기동 특성을 실현하기 위하여 전기 발열식 촉매체(EHC ; Electically Heated Catalyst)를 장착한 start-up 시스템을 적용하여 천연가스 자열개질 반응기의 신속한 기동과 장치 간편화를 실현하였으며, 합성 syngas의 배열 회수를 위한 최적 열교환 시스템을 설계/적용함으로써 에너지 효율 향상을 도모하였다. 이와 같은 촉매 및 구조 시스템을 가지는 천연가스 자열개질 반응용 소형 연료변환 시스템을 원통형의 이중관 구조로 구성하고, 독립운전 모드로 개발함으로써 소형 SOFC의 연료 변환장치의 적용에 용이하게 하고자 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.1
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• pp.19-26
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• 2009

The response characteristics of $H_2O_2$ monopropellant thrusters at a pulse mode were presented in this paper. A catalyst bed was fixed to $MnO_2$/$Al_2O_3$ to investigate the thruster design effect to response time. Three different thrusters (50 N class) having different injectors, ullage volumes, catalyst grain sizes, and reactor volumes were prepared to investigate the response characteristics. As a result, the ignition delay, pressure rising and tail-off time of case 2-2 thruster with 16-20 mesh catalyst size were 14, 108, 94 ms respectively, which were comparable to requirement of response time at commercial hydrazine thrusters.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.371-374
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• 2008

The performance of several catalysts to decompose the high test peroxide (HTP) was described in this paper. Manganese oxide, Platinum and Iridium were coated on the gamma alumina. The response time of various catalysts was measured with a 50 Newton class thruster. Ir/$Al_2O_3$ that showed the fastest response time at the thruster, failed the reaction when continuous mode test was carried out with the thruster. Pt/$Al_2O_3$ and MnO_2/Al_2O_3$ can be substitutes to decompose the HTP. In addition, for larger thruster, MnO_2/Al_2O_3$ can be a good catalyst because its cost is below 5 % of Pt/$Al_2O_3$.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.218-222
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• 2011

During the development of the iridium catalyst for domestic production, the catalyst failure, loss, sintering phenomena are observed by high pressure and temperature. By these abnormal failure of catalyst bed, the performance of thruster is degraded. To figure out the detail phenomena on the damaged catalyst bed, a numerical analysis code is developed by assuming the catalyst bed as an one dimensional porous media. The numerical analysis code is validated with experiment data. Thereby, resulting physical phenomena are examined by considering the variation of catalyst bed characteristics incurred by catalyst granule failure. Through these numerical analyses we figure out the effect of the catalyst loss on the decomposition of hydrazine and ammonia.

• Journal of Korean Society of Environmental Engineers
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• v.30 no.8
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• pp.823-830
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• 2008

The feasibility study for the application of the photoelectrocatalytic decolorization of Rhodamine B(RhB) was performed in the slurry photoelectrochemical reactor with powder TiO$_2$. The photoelectrocatalytic process was consisted of powder TiO$_2$, Pt electrode and three 8 W UV-C lamps. The effects of operating conditions, such as current, electrolyte, air flow rate and electrode material were evaluated. The experimental results showed that optimum TiO$_2$ dosage and current in photoelectrocatalytic process were 0.4 g/L and 0.02 A, respectively. It was found that the RhB could be degraded more efficiently by this photoelectrocatalytic process than the sum of the two individual oxidation processes(photocatalytic and electrolytic process). It demonstrated a synergetic effect between the photo- and electrochemical catalysis. Photoelectrocatalytic process was affected to air flow rate and optimum air flow rate was 2 L/min. The electrode material and NaCl effect of decolorization of RhB were not significant within the experiment conditions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.292-295
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• 2004

Firing performance test of hydrazine decomposition catalyst which is used in mono-propellant thruster of satellite and launcher was peformed. Equipment for catalyst test was developed and with this equipment reaction delay time, catalyst activity, granule stability of the catalyst firing performance was measured and analyzed.