| タイトル | Dual output variable pitch turbofan actuation system |
| 本文（外部サイト） | http://hdl.handle.net/2060/19770007082 |
| 著者（英） | Broman, C. L.; Griswold, R. H., Jr. |
| 著者所属（英） | General Electric Co.|NASA Lewis Research Center |
| 発行日 | 1976-11-30 |
| 言語 | eng |
| 内容記述 | An improved actuating mechanism was provided for a gas turbine engine incorporating fan blades of the variable pitch variety, the actuator adapted to rotate the individual fan blades within apertures in an associated fan disc. The actuator included means such as a pair of synchronizing ring gears, one on each side of the blade shanks, and adapted to engage pinions disposed thereon. Means were provided to impart rotation to the ring gears in opposite directions to effect rotation of the blade shanks in response to a predetermined input signal. In the event of system failure, a run-away actuator was prevented by an improved braking device which arrests the mechanism. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 77N14025 |
| 権利 | No Copyright |
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