| タイトル | Numerical simulation of flow path in the oxidizer side hot gas manifold of the Space Shuttle main engine |
| 著者（英） | Yang, R. J.; Chang, James L. C.; Lin, S. J.; Kwak, D. |
| 著者所属（英） | NASA Ames Research Center; Rockwell International Corp. |
| 発行日 | 1987-06-01 |
| 言語 | eng |
| 内容記述 | The purpose of this study is to examine in detail incompressible laminar and turbulent flows inside the oxidizer side Hot Gas Manifold of the Space Shuttle Main Engine. To perform this study, an implicit finite difference code cast in general curvilinear coordinates is further developed. The code is based on the method of pseudo-compressibility and utilize ADI or implicit approximate factorization algorithm to achieve computational efficiency. A multiple-zone method is developed to overcome the complexity of the geometry. In the present study, the laminar and turbulent flows in the oxidizer side Hot Gas Manifold have been computed. The study reveals that: (1) there exists large recirculation zones inside the bowl if no vanes are present; (2) strong secondary flows are observed in the transfer tube; and (3) properly shaped and positioned guide vanes are effective in eliminating flow separation. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 87A45212
AIAA PAPER 87-1800 |
| 権利 | Copyright |
