| タイトル | Analysis of experimental shaft seal data for high-performance turbomachines, as for Space Shuttle main engines |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850013259 |
| 著者（英） | Diamond, W. A.; Burcham, R. E.; Mullen, R. L.; Hendricks, R. C.; Braun, M. J. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1985-01-01 |
| 言語 | eng |
| 内容記述 | High-pressure, high-temperature seal flow (leakage) data for nonrotating and rotating Raleigh-step and convergent-tapered-bore seals were characterized in terms of a normalized flow coefficient. The data for normalized Rayleigh-steip and nonrotating tapered-bore seals were in reasonable agreement with theory, but data for the rotating tapered-bore seals were not. The tapered-bore-seal operational clearances estimated from the flow data were significantly larger than calculated. Although clearances are influenced by wear from conical to cylindrical geometry and errors in clearance corrections, the problem was isolated to the shaft temperature - rotational speed clearance correction. The geometric changes support the use of some conical convergence in any seal. Under these conditions rotation reduced the normalized flow coefficiently by nearly 10 percent. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 85N21569
NASA-TM-86928
E-2430
NAS 1.15:86928 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/156929 |
