• Journal of Mechanical Science and Technology
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• 제15권3호
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• pp.374-383
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• 2001

The spray/wall interaction is considered as an important phenomenon influencing air-fuel mixing in the internal combustion engines. In order to adequately represent the spray/wall interaction process, impingement regimes and post-impingement behavior have been modeled using experimental data and conservation constraints. The modeled regimes were stick, rebound, spread and splash. The tangential velocities of splashing droplets were obtained using a theoretical relationship. The continuous phase was modeled using the Eulerian conservation equations, and the dispersed phase was calculated using a discrete droplet model. The numerical simulations were compared to experimental results for spray impingement normal to the wall. The predictions for the secondary droplet velocities and droplet sizes were in good agreement with the experimental data.

• 한국결정성장학회지
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• 제9권6호
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• pp.558-562
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• 1999

승화 성장법을 적용하여 성장된 6H-SiC 결정에 대하여, KSV 이론과 성장 계면에서의 미사면(vicinal plane)상의 step 성장 양상을 근거로 하여, 성장 계면에서의 물질 흡착의 거동과 결함의 생성간의 상호 관계를 고찰하고, micropipes와 내부 결함의 생성 원인을 논하였다. micropipe와 면결함등의 결함들은 ledge 혹은 kink에 침입된 불순물에 의하여 step 성장의 진행이 방해받는 부분에 형성되었다. 따라서, SiC 결정에서 이들 결함의 생성은 SiC 결정 성장 계면에 형성되는 결정학적 step 성장면과 분자 또는 원자들의 격자 이동에 관련이 있음을 알 수 있었다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2002년도 춘계 학술대회논문집
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• pp.71-78
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• 2002

All modem, aerospace gas turbines must operate with hot stage gas temperature several hundreds of degrees hotter than the melting temperatures of the materials used in their construction. Complicated cooling schemes need to be employed in the combustor walls and In the high pressure turbine stages. Internal passages are cast or machined into the hot sections of aero-gas turbine engines and air from the compressor is used for cooling. In many cases, the cooling system is engineered to utilize jets of high velocity air, which impinge on the internal surfaces of the components. They are divided by Impinging cooling method and Vortex cooling method. Specially, Research of new cooling system(Vortex cooling method) that overcome inefficiency of film cooling and limitation of space. The focus of new cooling system that improve greatly cooling efficiency using quantity's cooling air which is less is set in surface heat transfer elevation. Therefore, In this study, the numerical analysis have been performed for characteristic of flow and thermal in the swirl chamber and compared with the flow field measurement by LDV. especially, for understanding of high heat transfer efficiency in vicinity of wall. we considered flow structure and mechanism of vortex and heat transfer characteristic in variation of Reynolds number.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 추계 학술대회논문집
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• pp.281-285
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• 2005

Viscous solutions of supersonic jet impinging on a flat wall in a confined plenum are simulated using three-dimensional Navier-Stokes solver. A confined plenum was designed for simulating the missile launch and analyzing the behavior of the exhaust plume, which were accompanied by complex flow interactions with shock and boundary layer. Concerns of this paper are to show accurate simulation of internal flow in confined plenum and to demonstrate the jet flow structure when the jet interacts with a small opening on the side. Objectives of this numerical simulation are to understand the effect of changing the plume exit area of the plenum. Pressure and temperature rise at certain position in the plenum are traced and compared with test data.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2009년도 제33회 추계학술대회논문집
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• pp.217-220
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• 2009

본 연구는 케로신-LOX를 연료와 산화제로 하는 액체로켓엔진의 가스발생기용 스월 동축형 인젝터의 리세스 길이에 따른 분무특성 파악을 목표로 하였다. 리세스 길이에 따른 두 추진제의 혼합 형태가 내부 혼합, 팁 혼합, 외부 혼합 등으로 분류되고, 인젝터 외부의 분무안정성에 영향을 미치므로 분무특성과 큰 연관성을 가진다.

• 한국전산유체공학회지
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• 제16권4호
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• pp.92-99
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• 2011

In order to protect the turbine blade from working fluid of high temperature, many cooling techniques such as internal convection cooling, film cooling, impinging jet cooling and thermal barrier coating have been developed. With all other things, film-cooling has been widely used as the important alternative. In the present work, numerical analysis has been performed to investigate and to compare the film-cooling performance of various film-cooling hole schemes such as cylindrical, crescent, louver, and dumbbell holes. To analyze the turbulent flow and the film-cooling mechanism, three-dimensional Reynolds-averaged Navier-Stokes analysis has been performed with shear stress transport turbulence model. The validation of numerical results has been assessed in comparison with experimental data. The characteristics of fluid flow and the film-cooling performance for each shaped hole have been investigated and evaluated in terms of centerline, laterally averaged and spatially averaged film-cooling effectivenesses. Among the film cooling holes, the dumbbell shaped hole shows better film-cooling effectiveness than the other shaped holes. And the louver and cylindrical shaped hole show the worst film cooling performance, and concentrated flows on near the centerline only.

• 생태와환경
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• 제49권2호
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• pp.124-129
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• 2016

본 연구는 하수처리장에서 최종 방류되는 하수처리수의 거품발생 원인분석과 저감방안을 제시하고자 수행되었다. 감조하천의 방류구에서 거품이 발생하는 것은 구조적인 문제점으로 파악되었다. 거품은 낙차에 의한 공기 연행과 확산방지막에 의한 내부축적이 주요한 원인이었다. 이러한 여건을 고려하여, 방류수로와 방류구 종단에서 미세스크린과 수중방류를 통해 거품발생을 완화시킬 수 있는 효과적인 방안을 제시하였다.

• 한국추진공학회지
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• 제10권3호
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• pp.9-17
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• 2006

본 연구는 케로신-LOX를 추진제로 하는 액체로켓엔진용 스월 동축형 인젝터의 리세스 길이에 따른 분무특성 파악을 목표로 하였다. 리세스 길이에 따른 두 추진제의 내부충돌현상에 의한 ripple의 형성과 감쇠가 인젝터 외부의 분무안정성에 영향을 미치므로 분무특성과 큰 연관성을 가진다. 또한, 리세스 길이가 증가함에 따라 평균액적크기는 증가하였으며, 혼합효율은 증가하다가 최대값에 도달한 후 다시 감소하는 경향성을 보였다.

• 한국유체기계학회 논문집
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• 제18권2호
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• pp.60-66
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• 2015

Conjugate heat transfer analysis was performed to investigate the flow and cooling performance of the high pressure turbine nozzle of gas turbine engine. The CHT code was verified by comparison between CFD results and experimental results of C3X vane. The combination of k-${\omega}$ based SST turbulence model and transition model was used to solve the flow and thermal field of the fluid zone and the material property of CMSX-4 was applied to the solid zone. The turbine nozzle has two internal cooling channels and each channel has a complex cooling configurations, such as the film cooling, jet impingement, pedestal and rib turbulator. The parabolic temperature profile was given to the inlet condition of the nozzle to simulate the combustor exit condition. The flow characteristics were analyzed by comparing with uncooled nozzle vane. The Mach number around the vane increased due to the increase of coolant mass flow flowed in the main flow passage. The maximum cooling effectiveness (91 %) at the vane surface is located in the middle of pressure side which is effected by the film cooling and the rib turbulrator. The region of the minimum cooling effectiveness (44.8 %) was positioned at the leading edge. And the results show that the TBC layer increases the average cooling effectiveness up to 18 %.

• 생태와환경
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• 제49권3호
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• pp.187-196
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• 2016

본 연구는 감조하천과 연결된 하수처리장 방류구에서 발생하는 거품의 형성기작 해석과 저감기술의 실험적용을 위하여 2015년 3월부터 2016년 7월까지 수행하였다. 거품은 방류구와 하천 수면 사이의 낙차에 의한 공기연행과 거품확산방지막에 의한 내부축적이 원인이었다. 특히 썰물 때와 방류량이 많을 때에 거품성장이 가장 활발하였다. 이를 해결하기 위하여 방류수로와 방류구에 각각 미세스크린 망과 수중방류 인공수로장치를 각각 설치한 후 실험하였다. 거품 저감효과는 각각 약 85.0~92.0%, 70.7~85.6% 범위였다. 또한, 거품뿐만 아니라 소음 등 부가적인 문제점도 해결할 수 있었고, 무엇보다도 민원예방에 기여할 것으로 본다. 본 연구는 단일 하수처리장을 대상으로 하였으나, 국내 다른 하수처리장의 유사한 사례에도 응용될 수 있을 것으로 사료된다.