Patent ID: 8646978
Filing Date: 2014-02-11
Classification: F01D,F05D,F16C,Y02T

Abstract:
1. A decoupling system for a rotary shaft of an aircraft turbojet, the system comprising: a rolling bearing including a plurality of rolling elements inserted between first and second rings, the first ring being fastened to a stationary bearing support of the turbojet and the second ring being mounted in an annular mounting chamber fastened to a rotary shaft of the turbojet; transmission means for transmitting rotary torque from the rotary shaft to the second ring of the bearing; means for radially centering the second ring of the bearing relative to the mounting chamber so long as a static force associated with an unbalance affecting the rotary shaft does not exceed a predetermined threshold, and for allowing the second ring of the bearing to move radially relative to the mounting chamber when a static force associated with an unbalance affecting the rotary shaft exceeds the predetermined threshold; and a plurality of leaktight flexible bags interposed between the second ring of the bearing and the mounting chamber around the entire circumference thereof, each bag including a heterogeneous structure including a porous capillary solid matrix and an associated liquid relative to which the matrix is lyophobic.