• JOURNAL OF ELECTRICAL WORLD
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• s.301
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• pp.68-73
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• 2002

미쓰비시(삼릉)전기는 1999년 5월치바현 이치가와시 동빈에$''$특정가정용기기재상품화법(통칭 : 가전리사이클법)$''$에 대응하기 위하여 일본국내 최초의 전기제품 리사이클 플랜트를 가동시켰다. 이 플랜트에서는 종합전기메이커로서의 특징을 살려 연소를 수반하지 않는 철저한 머티어리얼 리사이클, 물을 쓰지 않는 완전건식에 의한 소재(素材)의 분리$\cdot$분별(分別)을 실현하였다. 최대의 특징은 수(手)작업에 의한 부분분해와 기계분해(파쇄에 의한 소재분리)를, 리사이클률, 경제성, 환경부하성의 3가지 관점에서 조화를 시키고 있는 점이다. 본고에서는 리사이클 플랜트의 개요를 소개하고 리사이클률 향상과 리사이클 처리비용 저감을 위해 대처해 온 다음의 3개 항목에 대하여 기술한다. (1) 플라스틱찌꺼기(殘材) 리사이클설비의 개발 주파쇄분리(主破碎分離) 프로세스에서 배출되는 금속과 염화비닐을 포함한 플라스틱찌꺼기를 처리하여, 플라스틱을 고로환원재(高爐還元材)로서 유효 활용할 수 있도록 하였다. (2)효율적인 물류(物流)레이아웃 및 수해체방식(手解體方式)의 설계 공장내의 폐제품(廢製品)$\cdot$분별물(分別物)에 대한 보관장소, 반송수단$\cdot$경로를 최적 설계하여 처리비용을 요하는 수해체 작업을 효율적으로 할 수 있도록 업무흐름을 설계하였다. (3)리사이클공장 관리시스템의 구축 공장관리의 효율화와 배출자(排出者)에 대한 리사이클정보가 분명하게 나타날 수 있게 하기 위하여 리사이클공장관리시스템을 개발하여 도입하였다.

• Journal of Energy Engineering
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• v.2 no.2
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• pp.154-170
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• 1993

복합발전사이클은 서로 다른 온도조건에서 운전되는 두 개의 사이클을 열역학적으로 결합한 발전사이클로서 Fig. 1-(d) 처럼 고온부 사이클에서 배출되는 열량을 저온부 사이클에서 회수하여 전체 시스템효율을 개선하도록 설계되었다$^{1)}$ . 고온부에서 작동하는 사이클을 상부사이클(topping cycle or topper)이라고하며 저온부에서 작동하는 사이클을 하부사이클(bottoming cycle or bottomer)이라고 한다.

• Proceedings of the KAIS Fall Conference
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• 2010.11b
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• pp.684-687
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• 2010

본 논문은 복합사이클 발전플랜트의 폐열회수 보일러 최적운전 및 최적설계에 대한 새로운 접근 방법을 도출하기 위해 폐열회수 보일러에서 발생되는 증기로 증기터빈을 구동하는 하부사이클 효율을 검토하였다. 열역학 제1법칙 해석을 통해 하부사이클 에너지 평형을 검토하였고, 열역학 제2법칙을 통해 엑서지 평형을 검토하였다. 하부사이클 효율이 최대가 되는 폐열회수 보일러를 설계하기 위해서는 열역학 제1법칙을 해석할 경우 하부사이클 전체를 해석하여야 함을 알 수 있다. 하지만, 열역학 제2법칙을 통한 엑서지 해석을 행할 경우 하부사이클 효율이 최대가 되는 증발온도와 폐여회수 보일러에서 소모되는 엑서지가 최소가 되는 점이 일치함을 알 수 있었다. 따라서 본 논문을 통해 폐열회수 보일러에서 소모되는 엑서지 해석을 통해 하부사이클 효율이 최대가 되는 폐열회수 보일러 최적화가 가능함을 알 수 있다.

• Proceedings of the KSME Conference
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• 2005.11a
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• pp.216.1-216.1
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• 2005

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.2
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• pp.181-188
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• 2016

It is known that reliability of liquid rocket engines depends on the design thrust, propellant, engine cycle, and hot firing test time. Previously, a method was developed for estimating reliability of a new engine by adjusting the design thrust and hot firing test time of reference engines where reference engines have the same propellant and engine cycle with the new engine. In this paper, we provide a procedure to predict the engine reliability when the new engine and the reference engine have different propellant and engine cycles. The proposed method is illustrated to estimate the engine reliability of the first stage of Korea Space Launch Vehicle II.

• Journal of Energy Engineering
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• v.19 no.4
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• pp.228-233
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• 2010

About 55% of total energy is consumed in the industrial division. The industrial heat pump application will show magnificent energy saving effect as well as higher cost efficiency because of larger energy consuming volume of each facility and longer operation hour and higher stability against seasonal temperature change. Over 90% of dryer for industrial usage has hot wind heat source and hot wind dryer is the representative type covering 68.7% while its 30 ~ 50% lower heat efficiency causes lots of energy loss by exhaust air. Re-usage of exhaust air can improve energy efficiency of dryer because 68% heat energy or 78% of hot air lose in exhaust air. Therefore, high temperature heat pump dryer can be the best alternative. Comparing to the existing dryer with 30% ~ 50% energy efficiency, newly developing high temperature heat pump dryer will enhance energy efficiency up to 60% ~ 80% efficiency. In this paper, heat pump system for high temperature was designed, constructed and tested. The results have shown that system COPh is estimated as 3.3.

• Transactions of the Korean Society of Mechanical Engineers
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• v.14 no.1
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• pp.225-229
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• 1990

As a basic study of optimal design conditions of refrigeration systems, the reversed carnot cycle, including heat transfer processes through the finite temperature differences between heat sources and the working fluids, is analyzed with the capacity of heat exchanger as a design parameter. When the temperatures of heat sources and the input work are fixed as constants, the optimal design condition is obtained as an optimum ratio of capacities of heat exchangers, which is exactly unity when the exergy output and effectiveness are maximum. In addition, the optimum ratio is slightly increased from unity as the irreversibility of the cycle increases.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.40 no.10
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• pp.673-679
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• 2016

Because of the growing interest in supercritical carbon dioxide power cycle technology owing to its potential enhancement in compactness and efficiency, supercritical carbon dioxide cycles have been studied in the fields of nuclear power, concentrated solar power (CSP), and fossil fuel power generation. This study introduces the current status of the research project on the supercritical carbon dioxide power cycle by Korea Institute of Energy Research (KIER). During the first phase of the project, the un-recuperated supercritical Brayton cycle test loop was built and tested. In phase two, researchers are designing and building a supercritical carbon dioxide dual Brayton cycle, which utilizes two turbines and two recuperators. Under the simulation condition considered in this study, it was confirmed that the design parameter has an optimal value for maximizing the net power in the supercritical carbon dioxide dual cycle.

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.111-119
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• 2013

Conceptual design of RBCC (Rocket Based Combined Cycle) engine is performed through the thermodynamic cycle analysis. The engine is designed to take off at sea level and accelerate to Mach 8 at 30 km altitude. According to the flight speed, the engine operating modes are categorized into 3 modes : Ejectorjet (~ Mach 3), Ramjet (Mach 3~6), Scramjet (Mach 6~8). As a design result, the engine has a diameter of 1 m and a length of 6.7 m. In the prediction results, its maximum thrust is 16.5 ton. In Ramjet and Scramjet modes, design condition of the engine intake influence the engine thrust according to the flight speed.

• Journal of Advanced Marine Engineering and Technology
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• v.39 no.7
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• pp.735-743
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• 2015

The major component with a significant impact on the thermodynamic efficiency of the organic Rankine cycle is the turbine. Many difficulties occur in the turbine design of an organic Rankine cycle because the expansion process in an organic Rankine cycle is generally accompanied by a dramatic change in the working fluid properties. A precise preliminary design for a radial inflow turbine is hard to obtain using the classic method for selecting the loading and flow coefficients from the existing performance chart. Therefore, this study proposed a method to calculate the loading and flow coefficient based on the number of rotor vanes and thermodynamic design requirements. Preliminary design results using the proposed models were in fairly good agreement with the credible results using the commercial preliminary design software. Furthermore, a numerical analysis of the preliminary design results was carried out to verify the accuracy of the proposed preliminary design models, and most of the dependent variables, with the exception of the efficiency, were analyzed to meet the preliminary design conditions.