• 한국정밀공학회지
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• 제28권5호
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• pp.614-622
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• 2011

An internal lobe pump is suitable for oil hydraulics of machine tools, automotive engines, compressors, constructions and other various applications. In particular, the pump is an essential machine element of an automotive engine to feed lubricant oil. The subject of this paper is the theoretical analysis of internal lobe pump whose the main components are the rotors: usually the outer one is characterized by lobe with multiple profile(ellipse1, involute and ellipse2) shapes, while the inner rotor profile is determined as conjugate to the other. Also, the design of outer rotor depends on new applications with removing carryover phenomenon. The system generates new lobe profile and calculates automatically the flow rate and flow rate irregularity according to the lobe profile generated. In order to obtain rotor shapes in performance and to find optimize the design parameters, a Taguchi method is proposed in this paper. Results obtained from the analysis enable the designer and manufacturer of oil pump to be more efficient in this field.

• 설비공학논문집
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• 제12권8호
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• pp.717-724
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• 2000

It is important to investigate characteristics of flow of refrigerant/oil mixture circulating in a refrigeration system. Therefore the oil concentration in refrigerant/oil mixture should be measured exactly by the adequate measuring instrument. In this paper, the oil concentration was measured by density monitoring system(DMS) in the liquid-line of a inverter-driven heat pump. Experimental result follows ; the main factor that have an effect on oil concentration refrigerant/oil mixture circulating in a refrigeration system is the momentum and kinematic viscosity of refrigerant/oil mixture compressed by scroll compressor.

• 한국해양환경ㆍ에너지학회지
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• 제19권2호
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• pp.99-110
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• 2016

해양에서 시추작업 중 라이저가 손상되어 기름유출이 발생하면 경제적인 피해 뿐 아니라 해양환경에 막대한 피해를 가져오게 되므로 사고 발생 시 신속하게 사고에 대처해야 될 뿐만 아니라 초기의 기름 유출량 및 확산 정도를 파악하는 것이 중요하다. 본 연구에서는 소스코드가 공개된 전산유체역학 라이브러리인 OpenFOAM을 이용하여 손상된 라이저로 부터 기름이 유출되는 현상을 해석하였다. 수치방법을 검증하기 위해 제트 유동과 밀도 차에 의한 확산 문제인 Rayleigh-Taylor instability를 해석하였다. 라이저의 손상된 크기, 기름 유출량, 손상된 위치, 해류의 속도를 변화시키며 해석하였다. 해석 결과 기름이 유출 될 경우 수면에 도달 할 때까지 이동한 거리 및 시간을 예측하여 기름 확산에 대비할 수 있는 가이드라인을 제시하였다.

• Elastomers and Composites
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• 제44권3호
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• pp.315-322
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• 2009

이피디엠/폴리프로필렌 열가소성 경화물을 오일의 배합 순서를 달리한 두 가지 방식(오일 블렌드 후 가교방식과 가교 후 오일 블렌드 방식)으로 제조하여 가교도(겔분율), 경도, 인장강도, 신율, 용융흐름지수 등을 조사, 오일의 블렌드 방식이 열가소성 경화물의 물성에 미치는 영향을 알아보았다. 오일의 블렌드 방식에 따른 두 경화물의 가교도와 기계적 물성의 차는 크지 않았으나, 가공성에 있어서는 가교 후 오일 블렌드 방식으로 제조한 경화물의 용융흐름지수가 현저히 증가한 결과를 보였다.

• 한국기계가공학회지
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• 제16권2호
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• pp.50-55
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• 2017

This study is about the distributions of flow in an air conditioning duct used for marine and oil drilling ships. Three-dimensional steady state turbulence was assumed as a governing equation for describing the flow in the air conditioning duct in this study. We compared the flow field with the pressure distribution according to the inlet velocity for two types of air conditioning duct, and stress and safe factors were simulated using ANSYS W/B. The result of fluid analysis showed an increased pressure drop in the duct according to the inlet velocity. Furthermore, secondary flow and complicated flow characteristics occurred at the bellows zone.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2004년도 제28회 KOSCO SYMPOSIUM 논문집
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• pp.199-206
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• 2004

In the multi-burner power plant, uneven supplies of combustion air to multi-burner are induced by unbalanced flow distribution in the windbox. These flow patterns tend to make flame unstable, increase the formation of pollutants and lower the overall combustion efficiency. To prevent these disadvantages, flow patterns in the windbox should be investigated and made to be distributed uniformly, In this study, scaled windbox model was used for tests and measured the velocities at the exit of the each burner and compared those with the CFD results.

• 한국전기전자재료학회:학술대회논문집
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• 한국전기전자재료학회 1988년도 춘계학술대회 논문집
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• pp.70-73
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• 1988

Influence of Velocity and Temperature on Streaming Electrification of Insulating Oil is investigated by injection method. Leakage current is increased slightly with increasing temperature in the temperature range 20 to $80^{\circ}C$ at low flow rate, however, it show a peak in the temperature 40 to $60^{\circ}C$ at high flow rate. Leakage current is also increased linearly with increasing flow rate in the flow rate range 1 - 31/min but thereafter, it is increased abruptly with increasing flow rate.

• 한국해양공학회:학술대회논문집
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• 한국해양공학회 2001년도 추계학술대회 논문집
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• pp.122-127
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• 2001

As pipelines are often used to transport gas, oil, water and oil products, there are more than one pipeline installed in the offshore field. The size and space of pipelines are various depending on the design specifications. The pipelines are to be designed and installed to secure the stability to external loads during the installation and operation period. The flow patterns are very complex around the pipelines being dependent on incoming flow velocity, pipelines size and space. To investigate the flow patterns, number of experiment are conducted with visualization equipment in a circulating water channel. The flow motion and trajectory were recorded from the laser reflected particles by camera. From the experiment the flow patterns around spaced pipelines were obtained. Also pressure gradient was measured by mano-meter to estimate the hydrodynamic forces on the behind pipeline. The results show that the various sizes and spaces can be affected in the estimation of external load. The complex flow patterns and pressure gradients can be effectively used in the understanding of flow motion and pressure gradient.

• 한국군사과학기술학회지
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• 제6권4호
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• pp.124-131
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• 2003

When a secondary gaseous flow is injected vertically into a supersonic flow through circular nozzle, a complicated structure of flow field is produced around the injection area. The interaction between the two streams produces a strong bow shock wane on the upstream side of the side-jet. The results show that bow shock wave and turbulent boundary layer interaction induces the boundary layer separation in front of the side-jet. This study is to analyze the structure of flow fields and distribution of surface pressure on the flat plate according to total pressure ratio using a supersonic cold-flow system and also to study the control force of affected side-jet. The nozzle of main flow was designed to have Mach 2.88 at the exit. The injector has a sonic nozzle with 4mm diameter at the exit of the side-jet. In experiments, The oil flow visualization using a silicone oil and ink was conducted in order to analyze the structure of flow fields around the side-jet. The flow fields are visualized using the schlieren method. In this study, a computational fluid dynamic solution is also compared with experimental results.

• 대한기계학회논문집B
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• 제26권8호
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• pp.1153-1163
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• 2002

A transient analysis on temperatures of fuel and oil in hydraulic and lubrication systems in an aircraft was studied using the finite difference method. Numerical calculation was performed by an explicit method with modified Dufort-Frankel scheme. Among various missions, air superiority mission was considered as a mission model with 20% hot day ambient condition in subsonic region. The ambience of the aircraft was assumed as turbulent flow. Convective heat transfer coefficient were used in calculating heat transfer between the aircraft surface and the ambience. For an aircraft on the ground, an empirical equation represented as a function of free-stream air velocity was used. And the heat transfer coefficient for flat plate turbulent flow suggested by Eckert was employed for in-flight phases. The governing equations used in this analysis are the mass and energy conservation equations on fuel and oils. Here, analysis of fuel and oil temperature in the engine was not carried out. As a result of this analysis, the ground operation phase has shown the highest temperature and the largest rate of temperature increase among overall mission phases. Also, it is shown that fuel flow rate through fuel/oil heat exchanger plays an important role in temperature change of fuel and oil. This analysis could be an important part of studies to ensure thermal stability of the aircraft and can be applicable to thermal design of the aircraft fuel system.