| タイトル | Small High-Speed Self-Acting Shaft Seals for Liquid Rocket Engines |
| 本文（外部サイト） | http://hdl.handle.net/2060/19770024556 |
| 著者（英） | Burcham, R. E.; Boynton, J. L. |
| 著者所属（英） | Rockwell International Corp. |
| 発行日 | 1977-07-01 |
| 言語 | eng |
| 内容記述 | Design analysis, fabrication, and experimental evaluation were performed on three self-acting facetype LOX seal designs and one circumferential-type helium deal design. The LOX seals featured Rayleigh step lift pad and spiral groove geometry for lift augmentation. Machined metal bellows and piston ring secondary seal designs were tested. The helium purge seal featured floating rings with Rayleigh step lift pads. The Rayleigh step pad piston ring and the spiral groove LOX seals were successfully tested for approximately 10 hours in liquid oxygen. The helium seal was successfully tested for 24 hours. The shrouded Rayleigh step hydrodynamic lift pad LOX seal is feasible for advanced, small, high-speed oxygen turbopumps. |
| NASA分類 | MECHANICAL ENGINEERING |
| レポートNO | 77N31500
RI/RD77-195
NASA-CR-135167 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/181298 |
