통합 검색 | Korea Science

최창호;유정열
- 대한기계학회논문집B
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- 제23권10호
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- pp.1229-1239
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- 1999
A computational study on unsteady compressible flows has been performed by adopting a low Reynolds number $k-{\omega}$ turbulence model in conjunction with dual time stepping scheme. An explicit four-stage Runge-Kutta scheme for the Navier-Stokes equations and an approximate factorization scheme for the $k-{\omega}$ turbulence model equations are used. Computational results obtained for blade surface pressure distributions in the process of rotor-stator interaction in a turbine stage are in good agreement with extant experimental data. The effects of the wake from the stator on the boundary-layer transition over the rotor blade surface are discussed by showing that high intensity turbulence of the stator wake induces an early transition.
https://doi.org/10.22634/KSME-B.1999.23.10.1229 인용 PDF

이장준;최준민;이동호
- 한국전산유체공학회:학술대회논문집
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- 한국전산유체공학회 2004년도 추계 학술대회논문집
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- pp.111-114
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- 2004
CFD code that simulates stator-rotor interactions is developed applying parallel computing method. Modified Multi-Block Grid System which enhances perpendicularity in grid and is appropriate in parallel processing is introduced and Patched Algorithm is applied in sliding interface which is caused by movement of rotor. The experimental model in the turbo-machine is composed of 11 stators and 14 rotors. Analyses on two test cases which are one stator - one rotor model and three stators - four rotors model are performed. The results of the two cases have been compared with the experimental test data.
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김동규;오재응;임동규
- 한국음향학회지
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- 제12권6호
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- pp.28-35
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- 1993
팬소음은 설계변수들과 관계가 있으므로 본 논문은 실험적 방버벵 의하여 팬소음과 설계변수의 관계를 고찰하였다. 설계변수는 팬소음에 특히 영향이 큰 날개수, 날개각도, 날개끝 간극을 선택하였으며 새로운 설계변수로서 동익과 정익간의 간극과 흡입구 길이를 고찰하였다. 본 논문은 팬소음에 대한 관련된 이론을 정리하였으며 축류형 팬의 고효율 저소음 설계를 위한 방안을 제시하였다. 흡입구 길이, 날개끝 간극, 동익과 정익간의 간극등의 설계변소를 변경하여 실험한 결과 이들 설계변수들의 조정에 m이하여 축류형 팬의 고효율 저소음화를 이룰 수 있었다.
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정영래;박원규;이상욱
- 유체기계공업학회:학술대회논문집
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- 유체기계공업학회 1999년도 유체기계 연구개발 발표회 논문집
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- pp.163-169
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- 1999
The numerical procedure has been developed for simulating incompressible viscous flow around a turbine stage with rotor-stator interaction. This study solves 2-D unsteady incompressible Navier-Stokes equations on a non-orthogonal curvilinear coordinate system. The Marker-and-Cell concept is applied to efficiently solve continuity equation. To impose an accurate boundary condition, O-H multiblocked grid system is generated. O-type grid and H-type grid is generated near and outer rotor-stator The cubic-spline interpolation is applied to handle a relative motion of a rotor to the stator. Turbulent flows have been modeled by the Baldwin- Lomax turbulent model. To validate present procedure, the time averaged pressure coefficients around the rotor and stator are compared with experiment and a good agreement obtained.
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