| 摘要 |
The turbojet according to the invention comprises a fixed structure, a fan rotor fixed to a drive shaft ( 5 ) supported by a first bearing ( 6 ) and a second bearing ( 7 ), mounted on the said structure fixed through a bearing support part ( 11, 19 ), the first bearing ( 6 ) being mounted on the fixed structure of the turbojet through a device ( 13 ) enabling it to be decoupled ( 13 ) from the fixed structure, characterised by the fact that the second bearing ( 7 ) is mounted on the bearing support part ( 19 ) through a link acting as a ball joint ( 23, 24 ) and in that the turbojet also comprises means enabling axial displacements of the second bearing ( 7 ) with respect to the fixed structure of the turbojet if the first bearing ( 6 ) should be decoupled. The centring function of the second bearing ( 7 ) after decoupling of the first bearing ( 6 ) is thus provided without introducing excessive stresses in the bearing ( 7 ).
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