Device for guiding a shaft of an aircraft turbine engine

A device for guiding a shaft of an aircraft turbine engine, the device comprising:

• a rolling bearing, comprising two rings, a first ring and a second ring respectively, between which rolling elements are mounted,
• an annular bearing support extending around the bearing, and
• an oil film compression damping system mounted between the bearing support and the second ring, this damping system comprising:
• an annular shrink ring interposed between the bearing support and the second ring,
• two annular sealing segments upstream and downstream respectively, which are housed in annular grooves formed in an external cylindrical surface of the second ring and which are able to bear radially on an internal cylindrical surface of the shrink ring these external and internal surfaces defining between them an annular space for the formation of an oil film which is delimited axially by the sealing segments, each of these segments being slit by a straight cut to allow the evacuation of the oil from this space, and
• a first oil supply circuit this first circuit being connected to an annular supply channel which extends around the space and is connected to this space by orifices formed in the shrink ring,
• characterised in that the damping system further comprises:
• a second oil supply circuit this second circuit being connected to at least one annular heating channel which is independent of said supply channel and which extends around the space and in line with one of the sealing segments.