Abstract: A method for repairing a flange of a rotor, to a transverse surface of which a disk of a fan in an upstream turbo-fan engine is attached. The flange includes, in a form of a ring, openings for connecting to the disk and intermediate discharge openings. Wear marks are formed by friction of the fan blades on the flange. The method includes machining spot facings onto the flange, in areas with wear marks; placing anti-wear slugs in the discharge openings that can be covered by the blades during friction; and the spot facings extend between the connection openings and are circumferentially limited by clamping surfaces of the connection between the disk and the flange.

Abstract: An aircraft turbojet fan including multiple fan blades including a support that includes a rear portion including a first surface located on an intrados side and a second surface located on an extrados side. A fan disk includes, between recesses, attaching flanges radially protruding towards the outside such that the first surface and the second surface are located respectively opposite two attaching flanges. The fan further includes a wear-resistant part installed on the blade to form a protective shell on each of the first and second surfaces of the support, preventing contact between each surface and the attaching flange located opposite it.

Abstract: A turbine engine air blower including a rotor disk that includes, on an outer periphery thereof, longitudinal ribs, each including a radial lug for attaching the disk onto a downstream compressor rotor. The flanks of the lugs form abutments for holding vanes that are mounted onto the disk. A mechanism protecting flanks of the lugs is circumferentially inserted between the lugs and the vanes.

Abstract: The fan comprises a fan disk able to be rotationally driven about a longitudinal axis and provided at the periphery with radial blades each comprising a root slideably engaged in a groove of the disk and, on the outside thereof, a vane, platforms surrounding the disk being interposed between the radial blades. Advantageously, the fan additionally comprises shock-absorbing wedges which are arranged tangentially at the exterior periphery of said disk underneath the platforms and between two roots of adjacent radial blades, each wedge being in tangential contact with the two adjacent blades.

Abstract: A method for repairing a flange of a rotor, to a transverse surface of which a disk of a fan in an upstream turbo-fan engine is attached. The flange includes, in a form of a ring, openings for connecting to the disk and intermediate discharge openings. Wear marks are formed by friction of the fan blades on the flange. The method includes machining spot facings onto the flange, in areas with wear marks; placing anti-wear slugs in the discharge openings that can be covered by the blades during friction; and the spot facings extend between the connection openings and are circumferentially limited by clamping surfaces of the connection between the disk and the flange.

Abstract: A turbomachine rotor including a disk with a rim and axial cavities machined into the rim to individually house blades; and an annulus attached to one side of the rim and pierced with stress-relief holes, in which part of the stress-relief holes are situated in the axial continuation of the cavities, is disclosed. An annular shim is attached and interposed between the disk and the annulus, the shim forming a removable device for closing off the holes and an axial bearing surface against which the blades housed in the cavities can bear.

Abstract: An anti-wear device of a turbomachine rotor including a disk with a rim and axial recesses machined on the rim for the individual housing of blades; and a ring being fitted to one face of the rim, the ring being pierced with holes in the axial extension of the recesses, is disclosed. At least one of the holes in the extension of the recesses is closed by a plug including a metal head forming a bearing surface for the blades. The plug includes a stud in the extension of the metal head, an insert made of deformable material surrounding at least partly the stud, and a clamping device. The insert is made of deformable material being deformed by the clamping device so as to immobilize the plug in the hole.

Abstract: An aircraft turbojet fan including multiple fan blades including a support that includes a rear portion including a first surface located on an intrados side and a second surface located on an extrados side. A fan disk includes, between recesses, attaching flanges radially protruding towards the outside such that the first surface and the second surface are located respectively opposite two attaching flanges. The fan further includes a wear-resistant part installed on the blade to form a protective shell on each of the first and second surfaces of the support, preventing contact between each surface and the attaching flange located opposite it.

Abstract: A turbine engine air blower including a rotor disk that includes, on an outer periphery thereof, longitudinal ribs, each including a radial lug for attaching the disk onto a downstream compressor rotor. The flanks of the lugs form abutments for holding vanes that are mounted onto the disk. A mechanism protecting flanks of the lugs is circumferentially inserted between the lugs and the vanes.

Abstract: The present invention relates to a turbomachine rotor comprising a disk with a rim and axial cavities machined into the rim to individually house blades, an annulus pierced with stress-relief holes, part of the stress-relief holes being situated in the axial continuation of the cavities, being attached to one side of the rim. The rotor is characterized in that an annular shim is attached and interposed between the disk and the annulus, the shim forming a removable means of closing off the said holes and an axial bearing surface against which the blades housed in the cavities can bear. The invention applies to a turbojet engine with a fan at the front and to the interface between the fan disk and the upstream flange of the drum of the boost compressor.

Abstract: The present invention relates to an anti-wear device of a turbomachine rotor comprising a disk (20) with a rim and axial recesses (21) machined on the rim for the individual housing of blades, a ring (43) being fitted to one face of the rim, the ring being pierced with holes (44) in the axial extension of the recesses, at least one portion of said holes (44) in the extension of the recesses being closed by a plug (50) comprising a metal head (51) forming a bearing surface for said blades. The device is noteworthy in that the plug comprises a stud (52) in the extension of the metal head, an insert (53) made of deformable material surrounding at least partly the stud and a clamping means (54), the insert made of deformable material being deformed by the clamping means so as to immobilize the plug in the hole.