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조성권(Sungkwon Jo),이대훈(Dae Hoon Lee),송영훈(Young-Hoon Song) 대한기계학회 2014 대한기계학회 춘추학술대회 Vol.2014 No.11
Though methane has potential as a new energy source, its utilization is limited due to the bottleneck in methane activation. In this work, we investigate methane activation using additive noble gases to understand the relation between the discharge characteristics and methane conversion. We found that excited and ionized atoms of Ar and Kr considerably affect the methane activation even under similar electron temperature and electron density conditions. In other words, the degree of methane activation is determined by the intrinsic characteristics of the additive gas. We found that methane is predominately activated by electrons when Ar or Kr is used as an additive gas; however, methane is predominately activated by excited atoms with Xe as an additive gas. The difference in the activation species affects not only the methane conversion but also the selectivity of the product species. Among all noble gases, we find that Kr is the most effective for activating methane.
특성길이 변화에 따른 H<SUB>2</SUB>O<SUB>2</SUB>/Kerosene 이원추진제 로켓 엔진의 성능평가
조성권(Sungkwon Jo),장동욱(Dongwuk Jang),김종학(Jonghak Kim),윤호성(Hosung Yoon),권세진(Sejin Kwon) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.11
고농도 과산화수소를 이용하는 1,200 N 급 이원추진제 로켓 엔진 개발을 위한 기존 연구와 더불어, 특성길이의 영향 및 추력 측정을 통한 실질적인 성능을 평가하였다. 특성길이는 0.95, 1.07과 1.20 m, 총 3가지 경우에 대하여 실험을 수행하였으며, 특성길이의 증가에 따라 C<SUP>*</SUP> 효율 및 Isp 효율 모두 증가함을 확인하였다. 설계 당량비에서의 최대 C<SUP>*</SUP> 및 Isp 효율은 각각 98.4%와 93.1%로 측정되었다. 엔진 성능 평가 결과를 바탕으로 분해된 과산화수소를 이용한 엔진에서의 최적 특성길이를 제안하고, 설계 당량비에서의 추력 및 비추력 효율을 이용하여 진공에서의 엔진성능을 예측하여 보았다. 그 결과, 지상 218.4 s, 진공 253.3 s의 비추력과, 진공 추력 1035.3 N의 성능을 예상할 수 있다. In addition to the previous study for development of a 1,200 N-class bipropellant rocket engine with concentrated hydrogen peroxide, the effect of characteristic length and thrust measurement were experimentally evaluated. Tests with characteristic lengths of 0.95, 1.07, and 1.20 m were performed and C<SUP>*</SUP> and Isp efficiencies were increased as increasing characteristic length. The maximum C<SUP>*</SUP> and Isp efficiencies were 98.4% and 93.1% respectively. Based on the evaluation of the designed engine, the optimized characteristic length was proposed in using the engine adapted decomposed hydrogen peroxide and the engine performance at vacuum-level was evaluated using thrust and Isp efficiency at the designed equivalence ratio. As a result, 218.4 s at sea-level, 253.3 s at vacuum-level, and vacuum thrust of 1035.3 N can be estimated.
조성권(Sungkwon Jo),권세진(Sejin Kwon) 한국추진공학회 2008 한국추진공학회 학술대회논문집 Vol.2008 No.11
기존의 자연점화특성을 지니는 추진제는 성능이 높은 대신 독성이 있으며 다루기 어렵고, 환경에 유해한 단점을 지닌다. 이에 따른 대안으로 과산화수소의 촉매분해 후에 발생되는 고온의 산소와 수증기를 이용한 자연점화 방식이 있다. 이 논문에서는 자연점화 방식의 과산화수소/케로신 추력기를 설계하기 위한 기초연구를 수행하기 위해 자연점화특성을 연구하였다. 추력기의 형상변수로 노즐 목의 면적을 달리하여 연소챔버와의 단면적 비인 수축비를 달리하였으며, flame holder의 유·무, 과산화수소와 케로신의 가압압력에 따른 점화특성 및 연소안정성을 관찰하였다. 그 결과, 대부분의 경우에 자연점화를 관찰할 수 있었으나, 가압압력의 조건에 따라 연소 안정성에는 큰 변화가 있음을 확인할 수 있었다. Traditional propellants which have a hypergolic characteristic have a high performance but also have disadvantages of toxicity and complex handling requirement. In order to replace these propellants, one of the alternatives is hydrogen peroxide which generates high temperature oxygen and water vapor after catalytic reaction. In this paper, autoignition characteristics of kerosene by decomposed hydrogen peroxide were investigated to perform fundamental research for designing a thruster using hydrogen peroxide and kerosene propellants. Contraction ratio, whether flame holder exists or not, and feeding pressure of propellants were selected as variables. From the experiments for different mixture ratio, we confirmed the ignition stability is strongly affected by a feeding pressure of propellants.
분해된 과산화수소와 케로신을 이용한 1,200 N 급 이원추진제 로켓 엔진의 연구
조성권(Sungkwon Jo),안성용(Sungyong An),김종학(Jonghak Kim),윤호성(Hosung Yoon),권세진(Sejin Kwon) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.5
고농도 과산화수소를 이용하는 1,200 N 급 이원추진제 로켓 엔진 개발을 위한 선행 연구의 일환으로 이원추진제 엔진 요소를 설계하고 실험적으로 연구하였다. 공급된 과산화수소의 분해 성능을 비교하기 위해, MnO2와 Pb가 첨가된 MnO2 촉매들에 대한 실험을 하였다. 실험결과를 바탕으로, 촉매 반응기를 설계하였으며, 97.2%의 분해 효율을 얻었다. 별도의 점화원이 없이 자연점화를 이용하기 위해, 다양한 당량비에 대해 자연점화 실험을 수행하였다. 모든 실험조건에서 자연 점화를 확인하였으며, C<SUP>*</SUP> 효율은 90% 혹은 그 이상을 보였다. 추력측정 결과, 가장 높은 추력은 830 N을 보였으며, 94.1% 이론 비추력을 적용했을 경우, 진공 추력 1,035 N으로 계산되었다. As part of preliminary study for development of 1,200 N-class bipropellant rocket engine with the concentrated hydrogen peroxide, bipropellant engine elements were designed and experimentally tested. The catalysts of MnO2 and MnO2 added Pb as an addictive were compared to achieve high decomposition performance and the catalytic reactor with MnO2 added Pb was designed and its decomposition efficiency of 97.2% was achieved. The autoignition tests of kerosene by decomposed hydrogen peroxide were carried out under various equivalence ratios to ignite without additional ignition sources. Autoignition were achieved in all experimental conditions and C<SUP>*</SUP> efficiencies at each condition were at or above 90%. From the measured thrust results, the highest value was 830 N which is in corresponds with 1,035 N at vacuum level using 94.1% theoretical Isp.
과산화수소 분해열을 이용한 케로신의 자연점화 안정성 조사
조성권(Sungkwon Jo),권세진(Sejin Kwon) 한국연소학회 2008 KOSCOSYMPOSIUM논문집 Vol.- No.-
Traditional propellants which have a hypergolic characteristic have a high performance but also have disadvantages of toxicity and complex handling requirement. In order to replace these propellants, one of the alternatives is hydrogen peroxide which generates high temperature oxygen and water vapor after catalytic reaction. In this paper, autoignition characteristics of kerosene by decomposed hydrogen peroxide were investigated to perform fundamental research for designing a thruster using hydrogen peroxide and kerosene propellants. Contraction ratio, whether flame holder exists or not, and feeding pressure of propellants were selected as variables. From the experiments for different mixture ratio, we confirmed the ignition stability is strongly affected by a feeding pressure of propellants.
선박엔진의 SCR 성능 향상 및 촉매재생을 위한 플라즈마 버너 실증 평가
조성권(Sungkwon Jo),조동현(Donghyun Cho),이대훈(Dae Hoon Lee),김관태(Kwan-Tae Kim),이재옥(Jae-Ok Lee),송영훈(Young-Hoon Song),장재환(Jae Hwan Jang),노희환(Hui Hwan Roh),박건면(Geon-Myeon Bak),이태우(Tae-Woo Lee),한현식(Hyun-Sik Han) 대한기계학회 2018 大韓機械學會論文集B Vol.42 No.4
선박엔진 배기가스의 국제적인 규제가 강화되고 있으며, 규제를 적극적으로 대응하기 위한 기술이 필요하다. 본 연구에서는 플라즈마 버너를 적용하여 선박엔진 배기가스의 질소산화물 저감 성능을 향상시키고, 촉매 재생에 활용하기 위한 가능성을 확인하기 위한 연구를 수행하였다. 실험을 통해, 플라즈마 버너의 연소 성능을 확인할 수 있었으며, 공연비 대비 40% 이하의 공기 조건에서의 안정적인 연소와 배기가스의 산소를 활용한 연료의 완전 연소를 확인하였다. 또한, 요소수를 환원제로 활용한 탈질실험을 수행하였으며, 플라즈마 버너를 통해 탈질 촉매의 작동 영역으로 온도를 제어하여 탈질 성능을 향상시킬 수 있음을 확인하였다. 또한, 촉매 재생을 통해 촉매의 성능이 회복되는 결과로부터 플라즈마 버너를 활용하여 탈질 설비의 내구성 향상에 기여할 수 있음을 확인하였다. We investigated the possibility of applying a plasma burner to improve NOx-reduced performance of a marine engine and to utilize it for catalyst regeneration. Through experiments, we confirmed that stable combustion can be obtained under an air condition of less than 40% air-fuel ratio and can achieve complete combustion of the fuel using oxygen in the exhaust gas. A deNOx experiment using urea as a reducing agent was performed. We confirmed that deNOx performance can be improved by increasing the temperature of the SCR with a plasma burner. Moreover, we confirmed that the performance of the SCR was restored through the regeneration process, implying that the use of the plasma burner can contribute to a durability improvement of the deNOx system in a marine engine.
분해된 과산화수소와 케로신을 이용한 1,200 N 급 이원추진제 로켓 엔진의 연구
조성권(Sungkwon Jo),안성용(Sungyong An),김종학(Jonghak Kim),윤호성(Hosung Yoon),권세진(Sejin Kwon) 한국추진공학회 2010 한국추진공학회지 Vol.14 No.6
As part of preliminary study for development of 1,200 N-class bipropellant rocket engine with the concentrated hydrogen peroxide, bipropellant engine elements were designed and experimentally tested. The catalysts of MnO₂ and MnO₂ added Pb as an additive were compared to achieve high decomposition performance and the catalytic reactor with MnO₂ added Pb was designed and its decomposition efficiency of 97.2% was achieved. The autoignition tests of kerosene by decomposed hydrogen peroxide were carried out under various equivalence ratios to ignite without additional ignition sources. Autoignition were achieved in all experimental conditions and C<SUP>*</SUP> efficiencies at each condition were at or above 90%. From the measured thrust results, the highest value was 830 N which is in corresponds with 1,035 N at vacuum level assuming C<SUP>*</SUP> efficiency equals I<SUB>sp</SUB> efficiency.
특성길이 변화에 따른 H₂O₂/Kerosene 이원추진제 로켓 엔진의 성능평가
조성권(Sungkwon Jo),장동욱(Dongwuk Jang),김종학(Jonghak Kim),윤호성(Hosung Yoon),권세진(Sejin Kwon) 한국추진공학회 2011 한국추진공학회지 Vol.15 No.3
In addition to the previous study for development of a 1,200 N-class bipropellant rocket engine with concentrated hydrogen peroxide, the effect of characteristic length and thrust measurement were experimentally evaluated. Tests with characteristic lengths of 0.95, 1.07, and 1.20 m were performed and C<SUP>*</SUP> and Isp efficiencies were increased as increasing characteristic length. The maximum C<SUP>*</SUP> and Isp efficiencies were 98.4% and 93.1% respectively. Based on the evaluation of the designed engine, the optimized characteristic length was proposed in using the engine adapted decomposed hydrogen peroxide and the engine performance at vacuum-level was evaluated using thrust and Isp efficiency at the designed equivalence ratio. As a result, 218.4 s at sea-level, 253.3 s at vacuum-level, and vacuum thrust of 1035.3 N can be estimated.