Uncoupling system for an aircraft turbojet engine rotary shaft
View Patent ↗A decoupling system for a rotary shaft of an aircraft turbojet, the decoupling system including: a rolling bearing including rolling elements inserted between a first ring fastened to a stationary bearing support and a second ring mounted in a mounting chamber fastened to a rotary shaft; a transmission mechanism transmitting rotary torque from the rotary shaft to the second ring; a mechanism allowing the second ring to move radially relative to the mounting chamber when a static force associated with an unbalance affecting the rotary shaft exceeds a predetermined threshold; and a plurality of leaktight flexible bags interposed between the second ring and the mounting chamber and each including a heterogeneous structure including a porous capillary solid matrix and an associated liquid relative to which the matrix is lyophobic.
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.
2. A system according to claim 1 , wherein the second ring of the bearing includes a fuse shoulder fastened to the mounting chamber and enabling the second ring of the bearing to be centered radially relative to the mounting chamber so long as a static force associated with an unbalance affecting the rotary shaft does not exceed the predetermined threshold, and configured to break when a static force associated with an unbalance affecting the rotary shaft exceeds the predetermined threshold so as to allow the second ring of the bearing to move radially relative to the mounting chamber.
3. A system according to claim 1 , wherein the second ring of the bearing includes an axial flange fastened to a corresponding flange of the mounting chamber, the flanges forming a flexible connection allowing the second ring of the bearing to move radially relative to the mounting chamber.
4. A system according to claim 1 , wherein the second ring includes said transmission means, said transmission means includes a plurality of lugs co-operating with corresponding teeth of the mounting chamber to enable the transmission of the rotary torque from the rotary shaft to the second ring of the bearing.
5. A system according to claim 1 , wherein the mounting chamber is made up of two distinct portions.
6. A system according to claim 1 , wherein the mounting chamber is an interference fit on the rotary shaft and is held axially in position thereon by a nut.
7. A system according to claim 1 , wherein the rolling elements of the bearing are balls.
8. A system according to claim 1 , wherein the first ring of the bearing is arranged on the outside, while the second ring is arranged on the inside.
9. An aircraft turbojet, comprising at least one decoupling system according to claim 1 .