Abstract: An assembly (110) comprising a core (113) and at least a first sheet (111) held on one side of the core by a rivet (120), the rivet having two ends (121, 122). At least a first one of these ends (121, 122) is flared in shape and extends at least through the entire thickness of the first sheet (111, 112). A method of fabricating such an assembly, in which: a core (113) and a first sheet (111) are provided; the first sheet (111) is placed on one side of the core (113); and the core (113) and the first sheet (111) are riveted together.

Abstract: An assembly (110) comprising a core (113) and at least a first sheet (111) held on one side of the core by a rivet (120), the rivet having two ends (121, 122). At least a first one of these ends (121, 122) is flared in shape and extends at least through the entire thickness of the first sheet (111, 112). A method of fabricating such an assembly, in which: a core (113) and a first sheet (111) are provided; the first sheet (111) is placed on one side of the core (113); and the core (113) and the first sheet (111) are riveted together.

Abstract: A device for lubricating a component in an assembly of parts comprises a lubricant distribution chamber arranged in the vicinity of the component and formed by an annular setback in a ring mounted on a part of the assembly, said setback being closed automatically when the ring is mounted by means of a corresponding surface of the part into which there open out channels or ducts formed in the part and feeding the setback with lubricant and/or connecting the setback to means for taking lubricant to the component.

Abstract: The turbomachine of the invention extends longitudinally along an axis, and includes a rotor attached to drive shaft, arranged to rotate around an axis, supported by at least a first bearing, mounted on the fixed structure of the turbomachine by a bearing support element. The turbomachine is characterised by the fact that it includes a stop ring, mounted on the fixed structure of the turbomachine, to cooperate with the support element of the first bearing and, in the event of displacement of the rotor in relation to the fixed structure, to perform a function of axial retention of the rotor in an even manner, with no angle effect between the axis of the turbomachine and the axis of the drive shaft.

Abstract: A turbo-jet engine including a fixed structure and a fan rotor mounted on a drive shaft supported by a first bearing and a second bearing. The engine further comprises an axial retaining device configured to form an emergency bearing and to cooperate with the fixed structure and mounted rigidly to the drive shaft. The engine includes a structural flange on which the second bearing is fixed, and the axial retaining device comprises a retaining disk mounted on the drive shaft and configured to cooperate with a stop disk of the flange to axially retain the fan and form an emergency bearing.

Abstract: The turbojet includes a fixed structure, a fan rotor fixed to a drive shaft supported by a first bearing and a second bearing. The second bearing is mounted on the fixed structure through a bearing support part. The first bearing is mounted on the fixed structure of the turbojet through a device enabling it to be decoupled from the fixed structure. The second bearing is mounted on the bearing support part through a link acting as a ball joint. The turbojet also allows axial displacements of the second bearing with respect to the fixed structure of the turbojet if the first bearing should be decoupled. The centering function of the second bearing after decoupling of the first bearing is thus provided without introducing excessive stresses in the bearing.

Abstract: The turbine engine of the invention includes a rotor with at least one bearing, mounted on a bearing supporting part, said part being connected to the fixed structure by an uncoupling device, including at least one fusible screw passing through at least one bore, said screw comprising a head and a threaded portion, a fusible portion forming a preferential failure area, located between the head of the screw and its threaded portion. The screw comprises, between its threaded portion and its fusible portion, a portion for blocking the screw in rotation, cooperating with a complementary blocking portion provided in the bore. By means of the invention, the torsional torque related to the tightening of the screw is not transmitted to its fusible portion.

Abstract: The turbomachine of the invention extends longitudinally along an axis, and includes a rotor attached to drive shaft, arranged to rotate around an axis, supported by at least a first bearing, mounted on the fixed structure of the turbomachine by a bearing support element. The turbomachine is characterised by the fact that it includes a stop ring, mounted on the fixed structure of the turbomachine, to cooperate with the support element of the first bearing and, in the event of displacement of the rotor in relation to the fixed structure, to perform a function of axial retention of the rotor in an even manner, with no angle effect between the axis of the turbomachine and the axis of the drive shaft.

Abstract: A device for lubricating a component in an assembly of parts comprises a lubricant distribution chamber arranged in the vicinity of the component and formed by an annular setback in a ring mounted on a part of the assembly, said setback being closed automatically when the ring is mounted by means of a corresponding surface of the part into which there open out channels or ducts formed in the part and feeding the setback with lubricant and/or connecting the setback to means for taking lubricant to the component.

Abstract: 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).

Abstract: The present invention pertains to a turbo-jet engine comprising a fixed structure, a fan rotor integral with a drive shaft supported by a first bearing and a second bearing. It is characterized in that it comprises means forming axial retaining means for the fan rotor and/or forming an emergency bearing, cooperating with means of the fixed structure and mounted integral with the drive shaft. In particular it comprises a structural flange on which the second bearing is fixed, and the means forming axial retaining means for the fan and/or forming an emergency bearing comprise a retaining disk mounted on the drive shaft and cooperating with a stop disk of flange for axially retaining fan and with a longitudinal sleeve of flange to form an emergency bearing.