| 摘要 |
In a propulsion system for an aircraft first and second aero engines (22,23) are mounted within the fuselage at the rear end and are arranged to drive through separate drive trains coaxial first and second propellers (20,21) rotatably mounted on the fuselage at the rear end. Each drive train includes reduction gearing (54,61) which is segregated from the reduction gearing (54,61) of the other drive train. One of the propellers (20) is mounted on an inner drive shaft (58) and the other propeller (21) on a hollow outer drive shaft (65) through which the inner drive shaft (58) passes concentrically. A protective sleeve (72) extends between the two shafts (58,65) to protect each shaft from damage in the event of failure of the other shaft. |
