UNCOUPLING SYSTEM FOR AN AIRCRAFT TURBOJET ENGINE ROTARY SHAFT

摘要

The invention relates to an uncoupling system for an aircraft turbojet engine rotary shaft, comprising: a rolling bearing (22) having rolling elements (34) inserted between a first ring (38) fixed to a fixed bearing support (30) and a second ring (36) mounted in a mounting chamber (42) fixed to a rotary shaft (12); means (52, 54) of transmitting the rotational torque from the rotary shaft to the second ring; means (56) to allow relative radial movement of the second ring with respect to the mounting chamber when a static load associated with an imbalance affecting the rotary shaft exceeds a predetermined threshold; and a plurality of fluidtight flexible sacs (58) interposed between the second ring and the mounting chamber and each containing a heterogeneous structure (59) consisting of a porous capillary solid matrix and of an associated liquid with respect to which the matrix is lyophobic.