Abstract: An extraction device of a platform for holding a blade fitted with an upstream flange, out of a turbomachine rotor disc, and extraction method using the device. The device includes a handle fitted with a radial annular shoulder extended by a threaded pin, a proximal ring and a distal ring having a tube extended by a radial collar and a sleeve. The proximal ring is arranged around the pin, the tapped distal ring being screwed onto the other end of the pin and the sleeve being arranged around the two rings between their respective collars. Screwing of the handle results in moving the distal ring towards the proximal ring, radial deformation of the distal part of the sleeve against the flared part of the cylindrical orifice of the flange and its being joined to the latter. It is possible to conjointly extract the platform and the device from the disc.

Abstract: An intermediate casing for a turbine engine, comprising at least one central hub and one shroud (12) which are positioned concentrically, and mutually mechanically connected by structural arms (11), with such casing comprising at least one sealing part (13) attached between the shroud (12) and a structural arm (11), with the sealing part (13) including at least one metal core and one seal.

Abstract: A stator of an aircraft turbine engine, comprising an annular row of fixed vanes and an annular row of arms, wherein the trailing edges of the fixed vanes are positioned substantially in a first transverse plane that is positioned downstream of a second transverse plane that passes substantially through the leading edges of the arms.

Abstract: An intermediate casing for a turbine engine, comprising at least one central hub and one shroud (12) which are positioned concentrically, and mutually mechanically connected by structural arms (11), with such casing comprising at least one sealing part (13) attached between the shroud (12) and a structural arm (11), with the sealing part (13) including at least one metal core and one seal.

Abstract: An extraction device of a platform for holding a blade fitted with an upstream flange, out of a turbomachine rotor disc which includes a handle fitted with a radial annular shoulder extended by a threaded pin, a proximal ring and a distal ring which include a tube extended by a radial collar, and a sleeve, the proximal ring being arranged around the pin, the tapped distal ring being screwed onto the other end of the pin and the sleeve being arranged around the two rings between their respective collars, such that screwing of the handle results in moving the distal ring towards the proximal ring, radial deformation of the distal part of the sleeve against the flared part of the cylindrical orifice of the flange and its being joined to the latter, and that it is possible to conjointly extract said platform and the device from the disc.

Abstract: An attachment system intended to equip a wall, the system including a nut intended to receive a screw of which the orientation is normal to the wall, the screw passing through an element such as an outer panel in order to attach the element to the wall. The attachment system comprises a socket having a threaded cylindrical outer face intended to be screwed into a hole passing through the wall and having dimensions greater than the dimensions of the fastener that the repair socket replaces, the socket carrying, in the central region of same, a nut receiving the screw.

Abstract: An attachment system intended to equip a wall (17), the system including a nut intended to receive a screw (31) of which the orientation is normal to the wall (17), the screw (31) passing through an element such as an outer panel (32) in order to attach the element to the wall (17). The attachment system comprises a socket (26) having a threaded cylindrical outer face (34) intended to be screwed into a hole (29) passing through the wall (17) and having dimensions greater than the dimensions of the fastener that the repair socket (26) replaces, the socket (26) carrying, in the central region of same, a nut (28) receiving the attachment screw (32).

Abstract: A stator of an aircraft turbine engine, comprising an annular row of fixed vanes and an annular row of arms, wherein the trailing edges of the fixed vanes are positioned substantially in a first transverse plane that is positioned downstream of a second transverse plane that passes substantially through the leading edges of the arms.