| タイトル | Composite grid and finite-volume LU implicit scheme for turbine flow analysis |
| 著者（英） | Choo, Yung K.; Yoon, Seokkwan; Civinskas, Kestutis C. |
| 著者所属（英） | NASA Lewis Research Center|Sverdrup Technology, Inc.|Army Propulsion Lab. |
| 発行日 | 1987-01-01 |
| 言語 | eng |
| 内容記述 | A composite grid was generated in an attempt to improve grid quality for a typical turbine blade with large camber in terms of mesh control, smoothness, and orthogonality. This composite grid consists of the C grid (or O grid) in the immediate vicinity of the blade and the H grid in the upstream region and in the middle of the blade passage between the C grids. It provides a good boundary layer resolution around the leading edge region for viscous calculation, has orthogonality at the blade surface and slope continuity at the C-H (or O-H) interface, and has flexibility in controlling the mesh distribution in the upstream region without using excessive grid points. This composite grid eliminates the undesirable qualities of a single grid when generated for a typical turbine geometry. A finite-volume lower-upper (LU) implicit schemes can be used in solving for the turbine flows on the composite grid. This grid has a special grid node that is connected to more than four neighboring nodes in two dimensions and to more than six nodes in three dimensions. But the finite-volume approach poses no problem at the special point because each interior cell has only four neighboring cells in two dimensions and only six cells in three dimensions. The finite-volume LU implicit scheme was demonstrated to be robust and efficient for both external and internal flows in a broad flow regime. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 87A42078
AIAA PAPER 87-1129 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/377396 |
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