• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2010년 춘계학술대회논문집
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• pp.129-130
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• 2010

Design of turbo-compressors has been considered to be a high-tech which only a few early industrialized countries could do efficiently since it requires not only deep understanding of high level gas dynamics and complex fluid dynamics but also accumulation of experiences in the feedback of expensive manufacturing and difficult testing to the design theory and empirical design coefficients. CFturbo is the turbomachinery design software which incorporates traditional well formulated German design technology and latest software technology of 3-dimensional graphics. Fine/Turbo is a powerful tubomachinery-oriented CFD package with quality structured grid topology templates for almost all the tubomachinery configurations for easy, fast and accurate CFD analysis. Rapid and effcient process off turbo-compressor R&D is setup with the combination of CFturbo and Fine/Turbo.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 춘계학술대회
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• pp.1738-1743
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• 2004

Turbo-pump system, an essential component of liquid rockets and induced weapons, adopts a partial admission axial turbine which drives pump. And the turbine of a turbo-pump system is usually operated at supersonic condition due to its high loading chracteristics. Therefore, reseaches about flow and performance characteristics of a partial admission supersonic turbine must be preceeded to progress the aerospace and defense industries as well as the development of turbo-pump systems. In this study, flow characterisitics within blades of the partial admission supersonic turbine are numerically investigated by using Fine Turbo, a commercial CFD Code. Before performing the numercial analyses, to verify accuracy of the numerical result computed by Fine Turbo, I performed the comparison between the numerical results with J.J.Cho' experimental results. It is found that the numerical results show good agreement with the experimental results. Computations about the partial admission supersonic turbine have been performed to investigate flow characteristics including shock patterns. It is also found that the flow and performance of partial admission supersonic turbine are largely depend on shocks ocurred in the nozzle and at the leading edge of blades, expansion or compression at exit of nozzle and separations occurred in passage.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2005년도 제24회 춘계학술대회논문집
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• pp.413-422
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• 2005

본 연구에서는, 먼저 $Fine^{TM}/Turbo$의 신뢰성을 확보하기 위해 초음속 터빈의 실험 결과와 비교 해석하였다. 그 결과 $Fine^{TM}/Turbo$는 초음속 유동 현상을 비교적 정확하게 해석함을 알 수 있었다. 다음으로 Grid Independency Test를 통하여 3차원 터빈의 적합한 격자계를 선정하여. 3차원 초음속 터빈의 노즐-로터 상호작용에 관해 유동해석을 실시하였다. 터빈의 노즐-로터간의 축방향 간격은 점점 커질수록 높은 추력을 나타냈으며, 로터 블레이드의 Chamfering Angle 또한 Blade-Edge가 날카로워 질수록 추력이 증가하였다.

• 대한약침학회지
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• 제9권3호통권21호
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• pp.117-129
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• 2006

Objectives : The aim of this study was to find optimal conditions for producing red ginseng from cultivated wild ginseng using the Turbo Mill. Methods : Characteristics of powdered cultivated wild ginseng based on various temperature settings of the Turbo Mill were observed, and changes in the content was measured by HPLC for various ginsenosides. Results : 1. The diameter of cultivated wild ginseng powder ground by the Turbo Mill was around 10${\mu}m$. 2. As the temperature rose, pressure, Specific Mechanical Energy(SME), and density decreased, whileas Water Solubility Index(WSI) increased. 3. As the temperature rose, super fine powder showed tendency to turn into dark brown. 4. Measuring content changes by HPLC, there was no detection of ginsenoside Rg3 and ginsenosideRg1, Rb1, and Rh2 concentrations decreased with increase in temperature. Conclusions : Super fine powder of cultivated wild ginseng produced by the Turbo Mill promotes easy absorption of effective ingredients by breaking the cell walls. Using this mechanism to produce red ginseng from cultivated wild ginseng, it yielded less than satisfactory results under the current experiment setup. Further researches are needed to verify more suitable condition for the production of red ginseng.

• 항공우주시스템공학회지
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• 제1권1호
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• pp.67-72
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• 2007

In this paper, numerical results for 3-D supersonic turbine flow have been firstly compared with the experimental results to verify results computed by $Fine^{TM}/Turbo$. It was found that $Fine^{TM}/Turbo$ can accurately predict flow characteristics within supersonic turbine. Next, an grid system for 3D turbine flow was optimized selected through grid independency test. Finally, the effect of axial gap between rotor and nozzle and chamfer angle of blade edge on the flow characteristics within 3-D supersonic turbine was analyzed with Frozen Rotor method.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2000년도 유체기계 연구개발 발표회 논문집
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• pp.293-304
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• 2000

• 한국유체기계학회 논문집
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• 제7권5호
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• pp.78-81
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• 2004

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제21회 추계학술대회 논문집
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• pp.99-103
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• 2003

캐스케이드 내 유동 해석은 터보 펌프의 설계 제작에 필수적인 요소이다. 그러나 기존의 무한 입구 경계 조건에서는 입구 유동의 초기 설정 경계치와 계산 후 입구 유동 경계치의 차이가 발생하여 원하는 입구 경계 조건에서의 유동 해석을 하지 못한다. 이에 본 연구에서는 Fine Turbo를 이용하여 입구 경계 조건으로 무한 경계 조건을 적용하였을 때 발생하는 문제점을 분석하였다. 그리고 무한 입구 경계 조건 대신 캐스케이드 앞에 수축·확산 노즐이나 직선 노즐을 위치시켜 전산 해석을 실시하여 그 특성을 비교, 검토하였다.

• 한국추진공학회지
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• 제24권3호
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• pp.71-80
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• 2020

발사체 분석을 위한 CFD 소프트웨어인 LVAFoam을 개발하기 앞서 발사체의 연소기, 터보 펌프 및 외부유동의 시뮬레이션에 사용된 해외의 인하우스 CFD 소프트웨어 및 상용 CFD 소프트웨어에 대한 조사를 수행하였다. 인하우스 소프트웨어로는 NASA, 미시시피 주립대학, DLR, Bertin Technologies & CNES, CERFACS 및 JAXA의 솔버들과, 상용 소프트웨어로는 FLUENT, CFX, Adavance/FrontFlow/red, GASP, CRUNCH CFD, CFD-ACE+, FINE^TM/Turbo, STAR-CCM+ 의 솔버들을 정리하였다. 발사체 분석을 위한 각 소프트웨어의 계산 사례가 제시되었으며, 개발된 LVAFoam이 간략하게 소개되었다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.839-847
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• 2004

In this study, the flow characteristics within supersonic cascades are numerically investigated by using Fine Turbo, a commercial CFD code. Cascade flows are computed for three different inlet conditions. : a uniform supersonic inlet condition, a linear nozzle and a converging-diverging nozzle located in front of cascades. The effect of inlet conditions is compared and flow characteristics including shock patterns and shock-boundary layer interaction are analyzed. Also the effect of design parameters such as pitch-chord ratio, blade angle and blade surface curvature on the flow within supersonic cascades are studied.