| タイトル | Turbomachine Sealing and Secondary Flows - Part 3 |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040086723 |
| 著者（英） | Steinetz, B. M.; Athavale, M. M.; Przekwas, A. J.; Hendricks, R. C.; Zaretsky, E. V. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2004-07-01 |
| 言語 | eng |
| 内容記述 | The issues and components supporting the engine power stream are reviewed. It is essential that companies pay close attention to engine sealing issues, particularly on the high-pressure spool or high-pressure pumps. Small changes in these systems are reflected throughout the entire engine. Although cavity, platform, and tip sealing are complex and have a significant effect on component and engine performance, computational tools (e.g., NASA-developed INDSEAL, SCISEAL, and ADPAC) are available to help guide the designer and the experimenter. Gas turbine engine and rocket engine externals must all function efficiently with a high degree of reliability in order for the engine to run but often receive little attention until they malfunction. Within the open literature statistically significant data for critical engine components are virtually nonexistent; the classic approach is deterministic. Studies show that variations with loading can have a significant effect on component performance and life. Without validation data they are just studies. These variations and deficits in statistical databases require immediate attention. |
| NASA分類 | Aeronautics (General) |
| レポートNO | E-13662-3/PT3
NASA/TM-2004-211991/PT3 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/63889 |
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