• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.10a
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• pp.9-9
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• 1999

액체로켓 엔진의 분사기와 연소실 설계에 사용될 재생냉각형 칼로리미터의 냉각유로를 설계하였다. 사용할 펌프의 수두는 5기압이며 이로써 끓는점 아래에서 작동할 수 있고 동시에 넓은 냉각 면적을 가지는 유로의 형상을 결정하였다. 유로에서의 압력강하와 온도분포는 전산유동해석에 의하여 구하였고 열부하는 기존의 연소 해석과 1차원해석에 의한 결과를 적용하였다. 해석결과로서 유로의 폭이 4mm에서 2.5mm까지 2단계로 줄었다가 다시 2단계로 늘어나는 냉각유로를 설계하였으며 이 때 높이는 2mm로 일정하게 유지하였다. 유량 변화에 의한 레이놀즈 수는 1.9$\times$$10^4$, 2.4$\times$$10^4$, 2.9$\times$$10^4$이며 세 경우 모두 주어진 펌프수두 이내의 압력강하를 보였으나 온도상승과 성능상의 여유를 고려하여 레이놀즈 수 2.4$\times$$10^4$인 경우를 최종 설계안으로 결정하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.3
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• pp.97-103
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• 2012

The combustion chamber and nozzle of a liquid rocket engine should be protected from the high temperature combustion gas generated by the chamber. An upper-stage nozzle extension has a large expansion ratio, therefore, The light-weight refractory materials have been used since the weight impact on the launcher performance is crucial. Gas film cooling method was used before, but was not applicable nowadays. Ablative cooling method and radiative cooling method with niobium alloy, Ni-based superalloy and ceramic based composite have been used to this day.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.505-509
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• 2011

The combustion chamber and nozzle of a liquid rocket engine should be protected from the high temperature combustion gas generated by the chamber. An upper-stage nozzle extension has a large expansion ratio, therefore, The light-weight refractory materials have been used since the weight impact on the launcher performance is crucial. Gas film cooling and ablative cooling methods were used before, but were not applicable nowadays. Radiative cooling method with niobium alloy, Ni-based superalloy and ceramic based composite has been used to this day.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.2
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• pp.50-55
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• 2011

A preburner for the high performance, staged combustion cycle liquid rocket engine is being developed. For the structural design processes, strength experiments and finite element analyses on specimens simulating the brazing joints of the preburner, were performed and compared. Total two kinds of the specimen were manufactured for the tests. One simulated the joints between the oxygen injectors and the head junctioned by the conventional vacuum brazing. The another was made to test the brazing surfaces by vacuum compression between the combustion chamber cooling channel and the outer wall. During the burst experiments, it was observed that the fractures were occurred not at the brazed joining but in the middle of the face plate and the cooling wall. In addition, the analysis showed that the predicted fracture locations and the strains were well matched with the experiment results.

• Journal of the Korean Society of Fisheries and Ocean Technology
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• v.36 no.4
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• pp.322-328
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• 2000

Welding means that metal parts are joined by melting (with or without a filler material) or that new material is added to a metal part by melting. Welding of metal parts is an important technology method in manufacturing processes of capstan drum for costal vessels. Thermal stresses due to the non-uniform temperature fields during welding influence both the fabrication and the use of the weldment. In the problem of this thermal effect, particularly it is a well known that analysis for temperature gradient, temperature distribution, and the like become consequence factors to a safety and a strength design. This paper analyzes the temperature distribution of welding part in capstan drum for the inshore and costal vessels using finite element method. At early stage of the cooling after welding processes, the abrupt temperature gradient has been shown in vicinity of the bottom face of welding part. Therefore it calculates the numerical value that can be applied to the optimal design of welding parts in the shapes for capstan drum.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.38 no.12
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• pp.1051-1056
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• 2014

After hot rolling, a high-temperature steel plate with a temperature higher than $800^{\circ}C$ is rapidly cooled by multiple circular water jets. In this cooling process, because the temperature of the steel plate is much higher than the boiling point of the cooling water, film-boiling heat transfer occurs and a very thin steam layer forms between the plate surface and the cooling water. The steam layer acts as a thermal resistance that prevents heat transfer between the cooling water and the steel plate. In addition to the film-boiling heat transfer, complex physical phenomena such as the free-surface flow of residual water that accumulated on the material and the material's high-speed motion also occur in the cooling process. In this study, the simultaneous cooling process of the upper and lower sides of a running hot steel strip is investigated using a three-dimensional numerical model and the cooling performances and characteristics of the upper-side cooling and lower-side cooling are compared.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.59-63
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• 2005

The experimental study has been conducted to investigate the effect of the recirculation zone on the multi-slot film cooling in the ramjet combustor. The recirculation zone which is generated by the protrusion tip on the entrance of the coolant flow path affects on the first slot. Velocity fields, dimensionless temperature fields and adiabatic film cooling effectiveness on the downstream wall of the slot exit are measured. The results show that the film cooling performance is rapidly decreased after the slot exit by the share layer and high turbulence intensity between separated flows and coolant flows.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.170-173
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• 2007

Cooling characteristics of a liner were investigated by a film cooling method using a gas nitrogen in a rocket engine. High temperature gas of this test was made by mixing liquid nitrogen with combustion gas of a liquid rocket. A supply system of gas nitrogen was additionally constructed to the existing test facility of liquid rocket engine, and a new test section consisted of a liner and a gas injection ring was manufactured. A 10 second firing test for finding cooling characteristics of the liner was successfully conducted and liner surface temperatures and hot gas temperature was obtained.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.197-204
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• 2004

A design of regenerative cooling system of 30 ton level thrust combustion chamber for ground test has been performed. The 1-D design code has been validated by comparing with the heat flux of the NAL calorimeter for high chamber pressure and water-cooling performance of the ECC engine of MOBIS. The present design code has been confirmed to predict accurately the heat flux and water-cooling performance for high chamber pressure condition. The maximum hot-gas-side wall temperature is predicted to be about 720 K without thermal barrier coating and the coolant-side wall temperature is less than the coking temperature of RP-1. The coolant temperature rises nearly 100 K with thermal barrier coating when Jet-A1 is used as coolant.

• The Magazine of the Society of Air-Conditioning and Refrigerating Engineers of Korea
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• v.18 no.2
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• pp.108-115
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• 1989

과학산업의 육성책으로서 정부에서는 1988년도부터 특정출연연구 개발과제로 극한기술 개발을 시작하였다. 본 연구개발 과제는 극한기술의 5개 분과중 하나인 극저온 기술 분야에서의 연구개발목표인 SQUID(Superconductive Quantum Interference Devices)의 냉각장치로 사용되는 극저온용 냉동기 개발이다. 1988년부터 3년간, 연구개발비 약 3억원을 투자하여 작동온도 4.2K에서 약 100mW의 냉각능력을 갖는 냉동기에 대한 시제품을 개발함이 목적이다. 본 기술논문에서는 지난 6개월간의 연구수행 내용을 개략적으로 기술하여 연구진행상황을 파악할 수 있도록 하였다.