| 摘要 |
A ducted fan gas turbine engine comprises a fan 12 mounted on a first shaft 16 and a compressor 44 mounted on a second shaft 43. A first bearing 21 carries the upstream part of the first shaft 16 and the second bearing 40 carries the upstream part of the second shaft 43. Both bearings 21,40 are attached to a structure 26 which comprises an axial sleeve 28, a front frustoconical portion 30 and a rear radially stiff but axially flexible frustoconical portion 32, the structure 26 being attached to the engine casing 36. The front frustoconical portion 30 is frangibly attached to the front part of the axial sleeve 28 at abutting frustro-spherical faces 34,35. In the event of damage to the fan the frangible connection 33 breaks and the first shaft 16 is allowed to orbit about the engine longitudinal axis 15. The rear portion 32 is swashingly non-linear flexible and accommodates the out of balance radial loads transferred to it as couples during such an incident. |
