| タイトル | Self-acting seals for helicopter engines |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760011035 |
| 著者（英） | Lynwander, P. |
| 著者所属（英） | Avco Lycoming Div. |
| 発行日 | 1975-10-01 |
| 言語 | eng |
| 内容記述 | An experimental evaluation was conducted with NASA-designed self-acting face and circumferential seals for use in the main shaft positions of advanced gas turbine engines. The seals featured Rayleigh step pads (self-acting geometry) for lift augmentation. The tested seals incorporated design improvements over previous self-acting configurations. Self-acting face seals were tested to speeds of 214 m/s (700 ft/sec, 63700 rpm), air pressures of 216.8 N/sq cm abs (314.7 psia), and air temperatures of 688K (778 F). Self-acting circumferential seals were tested to speeds of 183 m/s (600 ft/sec, 47700 rpm), air pressures of 61.8 N/sq cm abs (89.7 psia), and air temperatures of 711 K (820 F). Self-acting face-seals are capable of operating at conditions exceeding conventional seal capability. The limit on speed capability was found to be the flatness of the seal-seat. The self-acting circumferential seal design tested requires further development for use in advanced engines. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 76N18123
NASA-CR-134940
LYC-75-78 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/187009 |
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