• Nuclear Engineering and Technology
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• v.27 no.6
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• pp.932-937
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• 1995

1990년 12월 카나다의 Darlington 2호기에서 발생한 핵연료 다발의 양쪽 지지판에 있는 지지 금속판의 파손은 펌프 날개 통과 압력 충격파가 Acoustic 성격으로 중폭되어 연료봉지지판의 파손을 일으킨 것으로 추정되었고 이에 따른 주열수송계통에 대한 ABAQUS를 이용한 Acoustic 해석과 수많은 실험을 거쳐 Acoustic 압력 충격파가 핵연료 다발의 연료봉 지지판 파손 원인임이 입증되었다. 이러한 Acoustic 해석과 실험의 결과로써 Darlington 발전소의 열수송 펌프를 5 날개 펌프에서 7 날개 펌프로 교체시키게 되었으며 그 결과 핵연료 스트링의 축방향 진동을 감소시켜 연료봉 지지판의 파손을 방지하게 되었다. 이러한 사례로 인하여 최근 CANDU형 원자로 열수송 계통의 Acoustic 해석에 대한 연구가 AECL의 Chalk River Laboratory와 COG(CANDU Owners Group)에서 활발하게 진행되고 있다. 이 기고문에서는 매우 새로운 분야로써 현재 이루어지고 있는 CANDU형 원자로 열수송 계통의 Acoustic 해석을 위한 해석 이론과 해석 방법을 간단히 요약 정리하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.5
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• pp.483-489
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• 2009

A CFD code was developed to investigate the inception of cavitation around impeller blades of centrifugal fuel pump using two dimensional cascade modeling. With the verification test for numerical validity of the developed code, the prediction of the onset of cavitation was made for the configuration of a newly designed KHP fuel pump. The calculation results show impeller design was free of cavitation if the pump operates within the operational temperature and rotational speed range. However, the cavitation would be relatively easy to occur at off design region of fuel pump where the rotational speed is higher than design limit. Specially, the onset of cavitation is sensitively dependent on the increase in fuel temperature while the decrease in temperature will reduce the possibility of cavitation inception in the pump.

• Proceedings of the Korean Society of Marine Engineers Conference
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• 2006.06a
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• pp.331-332
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• 2006

연료 분사펌프는 600bar 이상의 고압 연료를 분사밸브를 통하여 디젤기관의 연소실에 연속적으로 공급하는 장치이며, PLUNGER&BARREL 은 분사펌프의 핵심 부품으로 작동하고 고온 고압의 환경에서 $4{\mu}m$ 미만의 초정밀 간극을 유지해야 한다. 이러한 정밀한 가공 상태를 유지하기 위해선 내마모성 및 내열성에 적합한 재료와 열처리가 필수 요소이다. 현재 주로 사용되고 있는 방식은 DIAMOND STONE 에 의한 HORNIG 가공을 주로 사용하기 있다. 하지만, 연삭 가공과는 달리 별도의 치수 보정 장치가 없는 관계로, STONE 마모와 그에 따르는 마모량 공차에 의한 정밀 치수 확보의 어려움으로 인해, 고비용 저효율의 약점을 가지고 있다. 그러므로 기존의 HORNING STONE 방식을 대체한 PIN 방식의 HORNING MACHINE 개발을 목표로 한다.

• Journal of the Korean Society of Manufacturing Technology Engineers
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• v.20 no.5
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• pp.612-617
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• 2011

The comfort and quietness of vehicle has been improved greatly due to the development of technology in automobile industry. Some of noise reductions, for example, are driven by the improvement in the power-train system. Due to better in all performance, it is required to reduce more noise in automobile components. One of them is related to the fuel pump system including a pump and a tank. Therefore, this study is focused on investigating the characteristics of fuel pump and fuel tank first, and then comparing the data before and after installation of fuel pump system in a testing vehicle. Additionally, the measured data will be analyzed to identify the problems and provide knowledge to reduce the level of noise and vibration in fuel pump system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.605-609
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• 2010

The present paper describes a conceptual design of a turbopump which employs a planetary gear system. In a launcher system, weight is one of the most important design factor. In turbopump systems using propellants such as kerosene, or methane, single shaft systems are employed because of simplicity. One of the main disadvantages of this system, however, is the same rotational speed of both pumps and a turbine which forces to operate under non-optimum condition. To operate each component in optimum or favorable rotational speeds, a planetary gear system may be the best choice when the compactness and efficiency of a turbopump system is considered. A conceptual design and feasibility of the turbopump system adopting a planetary gear system is suggested.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.3
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• pp.89-95
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• 2015

Performance test was conducted for an oxidizer pump and a fuel pump for a 7 ton class rocket engine, by using water. The pumps were driven by an electric motor. The hydrodynamic performance and the suction performance were measured at flow ratio of the design and off-design conditions. Head-flow curve, efficiency-flow curve, and head-cavitation number curve were obtained. It is confirmed that the pumps can satisfy the design requirements of hydrodynamic performance in terms of the head and the efficiency. The pumps also satisfied the design requirements of suction performance.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.3
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• pp.58-63
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• 2011

The present paper describes a conceptual design of a turbopump which employs a planetary gear system. In a launcher system, weight is one of the most important design factor. In turbopump systems using propellants such as kerosene, or methane, single shaft systems are employed because of simplicity. One of the main disadvantages of this system, however, is the same rotational speed of both pumps and a turbine which forces to operate under non-optimum condition. To operate each component in optimum or favorable rotational speeds, a planetary gear system seems to be the best choice when the compactness and efficiency of a turbopump system is considered. A conceptual design and feasibility of the turbopump system adopting a planetary gear system is suggested.

• Journal of Aerospace System Engineering
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• v.12 no.3
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• pp.1-8
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• 2018

The fuel pump, which is used for an aircraft, was first developed in Korea through the Civil-Military Dual Components Development Program. The BLDC motor type, which is superior to the DC brush motor when considering efficiency, endurance, and explosive environmental characteristics, was applied to the fuel pump given its capacity and operating condition. The magnetic flux of the permanent magnet was analyzed based on the magnet flux density equation, using the Maxwell equation and the environmental condition. The motor performance, according to the load, was analyzed using the finite element method in order to design validation. The motor assembly was developed by designing the motor drive and the EMI filters. The performance test results of the motor assembly for the fuel boost pump were consistent with the analysis.

• Journal of Energy Engineering
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• v.20 no.3
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• pp.224-230
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• 2011

For developing high performance fuel cell, peripheral devices and key components have to be studied in priority. In this study, centrifugal pump was studied for heat recovery. For PEM fuel cell system, a four-impeller centrifugal pump was designed, tested and compared with result of commercial product (IWAKI). In addition, effects of number of impeller were analyzed by CFD. The experiment and analysis were progressed in the same conditions. The results showed the quantitative difference under 30% between the numerical and the experimental pressure difference and mass flow rate.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.11
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• pp.1013-1021
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• 2007

Design and performance analysis of the jet pump to transfer fuel between tanks in the smart UAV fuel supply system were carried out through one dimensional flow analysis and the flow analysis using a commercial CFD code. From the analysis results, it was proved that the jet pump was designed with the flow ratio of 2.23 that is the fundamental requirement of the jet pump design. The comparison results showed that the primary nozzle pressure is higher in the CFD analysis than in one dimensional flow analysis, mainly due to the underestimated loss coefficient of the primary nozzles. Consequently, the loss coefficients of the jet pump components should be determined more precisely for the design of the jet pumps with high performance.