Abstract: An assembly for a turbine engine includes at least a first part and a second part, and at least one bolt including a screw engaging with a nut. The screw extends through respective openings in the first part and in the second part. A bearing element of the bolt has an annular flange mounted between the screw or the nut and the first part. The flange has a bearing surface bearing that is tapered and forms an angle (?) with an additional bearing surface of the first part such that only an outer peripheral area of the flange bearing surface comes into contact with the additional bearing surface of the first part, in a non-tightened state of the bolt, the flange deformable such that when the nut is tightened on the screw, a larger area of the flange bearing surface bears on the additional bearing surface of the first part.

Abstract: The invention relates to the production of a composite material of a lobed structure (10) of a flow mixer which comprises a portion having a plurality of lobes (17, 19). For this purpose, a fibrous preform containing a resin will be produced in a simple geometric configuration of developable revolution. This is an intermediate state. By exploiting the thermoformable or thermosetting nature of the resin, the geometry of this intermediate preform is modified to deform it with limited offsets towards the final geometry.

Abstract: The invention relates to the production of a composite material of a lobed structure (10) of a flow mixer which comprises a portion having a plurality of lobes (17, 19). For this purpose, a fibrous preform containing a resin will be produced in a simple geometric configuration of developable revolution. This is an intermediate state. By exploiting the thermoformable or thermosetting nature of the resin, the geometry of this intermediate preform is modified to deform it with limited offsets towards the final geometry.

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: A tension decoupler includes first rupture members, arranged in parallel to each other, and second rupture members, arranged in parallel to each other and parallel to the first rupture members. The first rupture members and the second rupture members are designed to break only when the load applied to the decoupler device reaches or exceeds a predetermined load value, and the second rupture members are designed to have sufficient fatigue strength as long as the applied load does not reach the predetermined load value.

Abstract: An arrangement of bearing supports for a rotating shaft mounted on bearings connected to an engine stator structure by bearing supports of which at least one is made up of N>1 elements effectively acting in parallel to simultaneously connect the bearing to the structure, of which N?1 of the N elements form this connection by fusible links, is made up of a first bearing supported by a first bearing support and a second bearing supported by a second bearing support, that of the two bearing supports which makes up the N>1 elements being the second bearing support.

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: 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: 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: A tension decoupler includes first frangible rupture members, arranged in parallel to each other, and second structural rupture members, arranged in parallel to each other and parallel to the first rupture members. The frangible rupture members and the structural rupture members are designed to break only when the load applied to the decoupler device reaches or exceeds a predetermined load value, and the structural rupture members are designed to have sufficient fatigue strength as long as the applied load does not reach the predetermined load value.

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 invention relates to a rotary shaft arrangement carrying equipment at one end and extending rearwards from the equipment, the shaft (1) being supported by a first bearing (2) behind the equipment, and by a second bearing (3) behind the first bearing (2), the first bearing (2) being carried by a casing (4) surrounding the shaft (1) and extending rearwards from the first bearing (2) to a stator structure (5) to which the casing (4) is fastened by screws (6) that extend parallel to the shaft (1) and that are fusible in traction, the arrangement being characterized by the fact that the second bearing (3) is disposed with radial clearance (J) in a bore (7) of an annular support (8) secured to the stator structure (5), and is fastened to said annular support (8) by screws (9) that are parallel to the shaft (1) and that are fusible in shear, whereby the second bearing (3) can bear against said support (8) in the event of said screws (9) rupturing.

Abstract: A tension decoupler includes first rupture members, arranged in parallel to each other, and second rupture members, arranged in parallel to each other and parallel to the first rupture members. The first rupture members and the second rupture members are designed to break only when the load applied to the decoupler device reaches or exceeds a predetermined load value, and the second rupture members are designed to have sufficient fatigue strength as long as the applied load does not reach the predetermined load value.

Abstract: The invention relates to a turbomachine comprising a rotor with a drive shaft centered on the axis of the turbomachine by a first bearing and a second bearing which bearings are supported respectively by a first-bearing-support piece and a second-bearing-support piece which are secured to one another and connected to the turbomachine fixed structure by a decoupling device. This turbomachine comprises means designed to collaborate with at least one element of the turbomachine fixed structure in order to perform a dual function, that of preventing the bearing supports, from rotating and that of radially retaining the drive shaft in the event of the bearings becoming decoupled.

Abstract: The invention relates to a turbomachine comprising a rotor with a drive shaft centered on the axis of the turbomachine by a first bearing and a second bearing which bearings are supported respectively by a first-bearing-support piece and a second-bearing-support piece which are secured to one another and connected to the turbomachine fixed structure by a decoupling device. This turbomachine comprises means designed to collaborate with at least one element of the turbomachine fixed structure in order to perform a dual function, that of preventing the bearing supports, from rotating and that of radially retaining the drive shaft in the event of the bearings becoming decoupled.

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.