| 摘要 |
A gas turbine engine has a shaft 16 normally co-axial with the longitudinal axis 15 of the engine which shaft is supported by a bearing 18 which is in turn supported by the fixed structure 25 of the engine through a frangible connection 26, two limiting means 30, 36 being provided at different radial distances from the longitudinal axis of the engine to limit the radial movement of the shaft in the vicinity of the bearing following fracture of the frangible connecting means. The shaft may be the fan shaft of a ducted fan gas turbine engine and the fracture may be caused by imbalance in the fan following blade loss, the limiting means altering the natural frequency of the vibration of the fan. The radial movement may be limited by the limiting means radially furthest from the axis at first and subsequently by the other limiting means. A radially outward surface 29 of the outer race 20 of the bearing may engage with the movement limiting means. The two limiting means may be axially spaced and at last part of the bearing may be axially translatable, moved by load means 33. |
