Abstract: The invention relates to an outside ring of a rotary shaft bearing of a turbomachine, comprising a first guiding edge of at least one rolling element, the first guiding edge comprising an inside surface of the first guiding edge, an outside surface of the first guiding edge opposite the inside surface and at least one through-hole passing through the inside surface and the outside surface. Moreover, the inside surface of the first guiding edge forms a shoulder for guiding the rolling element, the through-hole defining a lubricant drainage orifice.

Abstract: A lubrication system for a device located between an internal shaft and an external shaft of an aircraft turbine, that are free to rotate, concentric and arranged at least partially one around the other, is provided. The lubrication system includes an annular element provided with an external groove and being mounted integral with the external shaft, the external groove being supplied with lubricant from a fixed part of the turbine; and a grooved element mounted integral with the internal shaft, the grooved element having a relief which directs a lubricant in contact with its external surface along a longitudinal direction when the internal shaft is rotating. The external groove is in fluid communication with an external surface of the grooved element through at least two conduits arranged through the external shaft.

Abstract: A device for centring and guiding the rotation of a turbine engine shaft, in which the outer race of a bearing is retained axially upstream and downstream by a retaining mechanism cooperating with a bearing bracket and with a coupling mechanism including elastically deformable mechanism connecting the outer race to the bearing bracket, the retaining mechanism being separate from a protecting ring of the device. A method of assembling such a device is also described. The retaining mechanism is pre-assembled with the coupling mechanism prior to the final assembly of the coupling mechanism with the bearing bracket. The device and the method have the combined advantages of axially retaining the outer race in two opposing directions and having a particularly straightforward assembly.

Abstract: A device for centring and guiding the rotation of a turbine engine shaft, in which the outer race of a bearing is retained axially upstream and downstream by a retaining mechanism cooperating with a bearing bracket and with a coupling mechanism including elastically deformable mechanism connecting the outer race to the bearing bracket, the retaining mechanism being separate from a protecting ring of the device. A method of assembling such a device is also described. The retaining mechanism is pre-assembled with the coupling mechanism prior to the final assembly of the coupling mechanism with the bearing bracket. The device and the method have the combined advantages of axially retaining the outer race in two opposing directions and having a particularly straightforward assembly.

Abstract: A structure for an aircraft turbojet including a rolling bearing including an outer ring, a bearing bracket, a retaining ring interposed between the ring and the bracket, a mechanism to connect the ring onto the bracket incorporating an attaching flange installed on the bearing bracket, a flexible connection attached to the ring and to the flange, and a mechanism enabling axial retention of the ring, in event the flexible connection fractures. The mechanism enabling axial retention includes a first stop securely attached to the retaining ring and capable of axially retaining this retaining ring relative to the bracket, and a second stop securely attached to the retaining ring, and capable of axially retaining the ring relative to the retaining ring.

Abstract: The invention relates to an outside ring of a rotary shaft bearing of a turbomachine, comprising a first guiding edge of at least one rolling element, the first guiding edge comprising an inside surface of the first guiding edge, an outside surface of the first guiding edge opposite the inside surface and at least one through-hole passing through the inside surface and the outside surface. Moreover, the inside surface of the first guiding edge forms a shoulder for guiding the rolling element, the through-hole defining a lubricant drainage orifice.

Abstract: A cooled turbine vane for a turbine engine, that includes a blade mounted on a platform carried by a base, the blade including one or more cavities formed therein for cooling air circulation, the cavity extending along the trailing edge and being supplied with cooling air by a supply duct connecting an air intake located in a lower portion of the base and the cavity of the trailing edge by defining a bend within the base. The duct includes, on an axis substantially radial relative to the air intake a bell-shaped niche located under the platform, the niche being open at a top thereof via a dusting hole extending through the platform and being defined at a foot of the base by walls extending substantially radially from the platform to close the platform laterally.

Abstract: Lubrication system for a device (13) located between an internal shaft (12a) and an external shaft (12b) of an aircraft turbine (10), that are free to rotate, concentric and arranged at least partially one (12b) around the other (12b), comprising an annular element (30) provided with an external groove (31) and being configured so that it can be mounted integral with the external shaft (12b), the external groove (31) being designed to be supplied with lubricant from a fixed part of the turbine (10), a grooved element (25) configured to be mounted integral with the internal shaft (12a), the grooved element (25) having relief (70) designed to direct a lubricant in contact with its external surface along a longitudinal direction (A) when the internal shaft (12a) is rotating, the external groove (31) being in fluid communication with an external surface (70) of the grooved element (25) through at least two conduits (22) arranged through the external shaft (12b).

Abstract: A connecting module interposed between a drive shaft of an aircraft engine fan and a rolling-element bearing, wherein the module includes an inner structure attached to the shaft and including a bonnet, and an outer structure attached to the bearing, which is radially supported on a mechanism installed on the inner structure and delimiting a raceway which is complementary to the bonnet so as to form a ball-joint connection kept in a blocked state by a blocking device installed on the inner structure and protruding radially from the bonnet, wherein a mechanism forming a mechanical fuse provides a junction between the device and the bonnet, such that the ball-joint connection is released following fracture of this mechanism forming a mechanical fuse. The radial support mechanism is added to the device.

Abstract: A connecting module interposed between a drive shaft of an aircraft engine fan and a rolling-element bearing, wherein the module includes an inner structure attached to the shaft and including a bonnet, and an outer structure attached to the bearing, which is radially supported on a mechanism installed on the inner structure and delimiting a raceway which is complementary to the bonnet so as to form a ball-joint connection kept in a blocked state by a blocking device installed on the inner structure and protruding radially from the bonnet, wherein a mechanism forming a mechanical fuse provides a junction between the device and the bonnet, such that the ball-joint connection is released following fracture of this mechanism forming a mechanical fuse. The radial support mechanism is added to the device.

Abstract: A structure for an aircraft turbojet including a rolling bearing including an outer ring, a bearing bracket, a retaining ring interposed between the ring and the bracket, a mechanism to connect the ring onto the bracket incorporating an attaching flange installed on the bearing bracket, a flexible connection attached to the ring and to the flange, and a mechanism enabling axial retention of the ring, in event the flexible connection fractures. The mechanism enabling axial retention includes a first stop securely attached to the retaining ring and capable of axially retaining this retaining ring relative to the bracket, and a second stop securely attached to the retaining ring, and capable of axially retaining the ring relative to the retaining ring.

Abstract: A locking member for a device for fastening ring sectors to an aircraft turbine engine casing is disclosed. The member has first and second clamping branches, which are connected together by curving joining portions, via a connecting branch. The joining portion of center thickness E1 has an inside surface of mean radius Rm1, and the joining portion of center thickness E2 has an inside surface of mean radius Rm2. Thickness E1 is strictly smaller than thickness E2, and mean radius Rm1 is strictly smaller than mean radius Rm2.

Abstract: A cooled turbine vane for a turbine engine, that includes a blade mounted on a platform carried by a base, the blade including one or more cavities formed therein for cooling air circulation, the cavity extending along the trailing edge and being supplied with cooling air by a supply duct connecting an air intake located in a lower portion of the base and the cavity of the trailing edge by defining a bend within the base. The duct includes, on an axis substantially radial relative to the air intake a bell-shaped niche located under the platform, the niche being open at a top thereof via a dusting hole extending through the platform and being defined at a foot of the base by walls extending substantially radially from the platform to close the platform laterally.

Abstract: This invention relates to a locking member (24) for a device for fastening ring sectors to an aircraft turbine engine casing. The member has first and second clamping branches (28, 30), which are connected together by means of curving joining portions (36a, 36b), via a connecting branch (32), the joining portion (36a) of centre thickness E1 having an inside surface (36a?) of mean radius Rm1, and the joining portion (36b) of centre thickness E2 having an inside surface (36b?) of mean radius Rm2. According to the invention, thickness E1 is strictly smaller than thickness E2, and mean radius Rm1 is strictly smaller than mean radius Rm2.

Abstract: The invention provides a device for holding strip sealing gaskets on a turbomachine nozzle, the nozzle being constituted by a plurality of sectors having guide vanes which extend between inner and outer platforms elements, at least one of said platform elements having a sealing strip (30) disposed radially in a space between said platform element and an adjacent structural element in order to provide fluid tightness between said elements, the corresponding strips of two adjacent sectors touching, and their joint being covered by a joint cover (31) disposed between said strips, and by a holding member for holding said strips in the sealing position.

Abstract: The invention provides a device for holding strip sealing gaskets on a turbomachine nozzle, the nozzle being constituted by a plurality of sectors having guide vanes which extend between inner and outer platforms elements, at least one of said platform elements having a sealing strip (30) disposed radially in a space between said platform element and an adjacent structural element in order to provide fluid tightness between said elements, the corresponding strips of two adjacent sectors touching, and their joint being covered by a joint cover (31) disposed between said strips, and by a holding member for holding said strips in the sealing position.

Abstract: A sheet metal sealing sleeve placed under a pair of juxtaposed blade platforms in a turbomachine so as to cover the gap between them is provided with apertures to allow the flow of a ventilating gas to the platforms. The apertures are provided in bosses formed on the sleeve to define chambers between the sleeve and the platforms which provide for greater heat exchange by virtue of the forcible impact of the gas blown through the apertures under the platforms. The sleeve also aids in damping platform vibration.