• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.2
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• pp.14-23
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• 1998

The present study investigates numerically particle laden flow through compressor cascade. In general, a lot of turbine engines are affected by various particles which are suspending in the atmosphere. Especially in the case of aircraft aviating in volcanic, industrial and desert region including many particles, each components of engine system are damaged severely. That damage modes are erosion of compressor binding and rotor path components, partial or total blockage of cooling passage and engine control system degradation.. Initial damages can not be serious but cumulation of damages influences on safety of aircraft control and economical maintenance cost of engine system can be increased. When dust, materials and volcanic particles in the atmosphere flow in the compressor, it is necessary to predict damaged and deposited region of compressor blades. To the various flow inlet angle, predictions of particles trajectory in compressor cascade by Lagrangian method are presented and impulses by impaction of particles at blade surface are calculated. By the definition of particle deposition efficiency, characteristics of particles impact are considered quantitatively. With these prediction and experimental data, erosion rates are predicted for two materials - ceramic, soft metal - on compressor blade surface. Improvements like coating of blade surface could be found, by above prediction.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.235-240
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• 2010

Transpiration cooling is the most effective cooling technique for liquid rocket and air-breathing engines operating in aggressive environments with higher pressures and temperatures. Combustor liners and turbine vanes are cooled by the coolant(air or fuel) passing through their porous walls and also the exit coolant acting as an insulating film. However, its practical implementation has been hampered by the limitations of available porous materials. The search for more practical methods of increasing the internal heat transfer within the walls has led to the development of multi-laminate porous structures, such as Lamilloy$^{(R)}$ and Transply$^{(R)}$. This paper reviews recent research activities of transpiration cooling for the propulsions of liquid rocket, gas turbine, and scramjet.

• Journal of the Society of Naval Architects of Korea
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• v.42 no.1 s.139
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• pp.1-9
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• 2005

Waterjet propulsion is widely used to thrust high speed marine vessels in excess of 30-35 knots by virtue of the high propulsive efficiency, good maneuverability, and less cavitation. From the aspect of power loss, approximately $7-9\%$ of the total power is lost in intake duct due to the flow separation, nonuniformity, etc. Thus, detail understanding of flow phenomena occurring within intake duct is essential to reduce the power loss, as well as noise and vibration. The present work solved 30 incompressible RANS equations to provide complicated viscous flow features of intake duct. The numerical results were compared with experiments and good agreements were obtained for three jet velocity ratios.

• Journal of the Society of Naval Architects of Korea
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• v.42 no.3
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• pp.290-298
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• 2005

A study of design and analysis for the POD type waterjet is conducted. The analysis and design of waterjet system are more difficult than that of conventional propulsor because waterjet is complicatedly composed of many parts which are impeller, stator, inlet, nozzle, etc. The streamline method is traditionally used in the design of pump whose characteristics are similar to those of waterjet. This streamline method, however, has some limitation in analysis of a viscous flow as well as the interaction of inlet part of hull. In the present study, the developed CFD program is applied to the analysis of POD type waterjet. The developed program is first validated by comparing the existed experimental results. The designed waterjet system is also analyzed by the developed CFD program and analyzed results show that the performance of the present POD type waterjet is above the requirement.

• Proceedings of the Korea Water Resources Association Conference
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• 2021.06a
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• pp.38-38
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• 2021

전 세계적으로 기후변화의 영향으로 인해 수문·기상 등 다양한 분야에서 심각성이 야기되고 있으며, 가뭄, 집중호우, 태풍 등과 같은 자연재해의 발생빈도와 피해가 증가하고 있다. 우리나라의 경우 봄철 가뭄의 발생빈도가 증가하고 있으며, 발생지역이 확산되는 추세이다. 증발산량(evapotranspiration)은 기상학과 수문학에 주요한 농업기상 매개 변수로 다루어지며, 작물의 생육·성장에 필요한 물 수요 및 관개용수 산정에 필요한 인자로 가뭄 분석에 활용하는 중요 인자들 중 하나다. 증발산량 자료 구축에는 증발산계 (Lysimeter)를 이용하여 현장 데이터를 실측하는 방법과 구조화된 알고리즘을 통해 증발산량을 산출하는 방법으로 나누어진다. 우리나라의 경우 증발산계가 설치된 지역이 많지 않고 분포도 조밀하지 않으며, 기상, 식생, 토지 피복 등 다양한 요인들의 영향을 받는 증발산량의 특성상 실측 데이터를 구축하는 것은 현실적으로 어렵다. 이에 물수지 기법, 기상 변수 기반 추정 등 간접적인 방법을 통해 증발산량을 추정하는 연구가 일반적으로 진행되고 있다. 이에 본 연구에서는 미국항공우주국 (National Aeronautics and Space Administration, NASA) 제트 추진 연구소 (Jet Propulsion Laboratory, JPL)의 The ECOsystem Spaceborne Thermal Radiometer Experiment on Space Station (ECOSTRESS)에서 제공하는 위성영상 중 증발산량 데이터를 구축하였다. 구축한 ECOSTRESS 증발산량 적합성 확인을 위해, 청미천·설마천에서 제공하는 증발산량과 비교 및 검증을 실시하였으며, 시공간적 변동성 분석을 위해 통계적 방법을 이용하였다. 본 연구에서 도출된 증발산량의 시공간 변동성 결과를 통해 지역별 가뭄 분석의 기초자료로 활용될 수 있을 것으로 사료된다.