Safran Aircraft Engines

Nicolas Daniel Delaporte

Didier Noël Durand

Anthony Pierre Beguin

Arnaud Martine

Antoine Giguet

Thierry Michel Breugnot

Marina Wilma Bilioniere

Vincent Goyon

Pierre Marie Mulheim

Alain Dominique Gendraud

Didier Noel Durand

Yannick Durand

Emmanuel Bernard Marie Charrier

Olivier Jean Daniel Baumas

Mostafa Benbouda

Adeline Isabelle Anne-Marie Houssaye

Olivier Jean-Daniel Baumas

A foil for a turbomachine rotor blade, configured to be mounted on a root of the rotor blade and including an embossment located in a lower surface of the foil and forming, in the lower surface of the foil, a convex protrusion capable of being inserted into a housing formed in a lower face of the blade root.

Foil, assembly for a turbomachine rotor and turbomachine

A foil and a root of a blade of a turbomachine rotor and includes a base, two side limbs that are connected to each other by the base, at least the first limb includes at least one recess including at least two folds in two different directions, the recess being capable of engaging with a notch provided in the root of the blade to ensure the foil is longitudinally retained relative to the root of the blade at least in a longitudinal direction.

Foil, rotor blade, assembly for a turbomachine rotor and rotor

A method for checking the tightening tension of at least one fastening bolt for fastening at least two aeronautical parts, wherein it includes the steps of mounting a centering device on a head of a screw of the bolt, the centering device including an aperture aligned with an axis of the screw; engaging one end of a sensor in the aperture of the device until this end is in contact with the head of the screw; checking at least one physical parameter of the bolt by the sensor, this parameter being representative of the tightening tension of the bolt; then removing the centering device.

Method and device for checking the tightening tension of a fastening bolt for fastening aeronautical parts

An assembly for a turbomachine of longitudinal axis includes a nozzle carried by an annular part which is fixed to an outer casing. The nozzle has an outer annular platform from which extends, radially outwards, a radial annular wall which carries an annular attachment tab extending longitudinally upstream from the radial annular wall. The assembly has a cooling circuit with an inner annular chamber delimited radially by the outer annular platform and the annular part and delimited downstream by the radial annular wall. An intermediate annular chamber is formed radially externally to the annular attachment tab and in fluid communication with the outer casing. Means of fluid communication between the inner annular chamber and the intermediate annular chamber is formed in the annular attachment tab of the nozzle.

Turbine for turbomachine

An aircraft turbomachine module having two tubular casings equipped with first and second annular flanges assembled by studs received in the first flange and receiving nuts on the back of the second flange, each stud having an intermediate stretch of hexagonal shape cooperating with a locking plate. The locking plate can have a first orifice received on the intermediate stretch by at least two opposite walls, and a transverse body which is immobilized to prevent the rotation of the plate and that of the stud. Each plate can be fitted on two immediately adjacent studs and the body can have, for this purpose, a second orifice opposite the first orifice and which is received on an intermediate stretch of an immediately adjacent stud and cooperates with the intermediate stretch of hexagonal shape of the stud.

Turbomachine module comprising stud pair locking plates

An upstream rail of a turbine engine turbine casing, which includes a casing body extending along a longitudinal axis, includes a base including a radial face, extending substantially radially from the casing body, a plate including an upper face, extending substantially along the longitudinal axis, a connection portion between the base and the plate, including a concave face connecting the radial and upper faces, the concave and radial faces extending on either side of an edge. The upstream rail is repaired through a method including covering a surface with a solder, the surface including the upper and concave faces such that the solder extends until the edge, and machining the covered surface, in a single action, in a direction toward the radial face, so as to reshape the surface, wherein the machining of the covered surface is performed on a portion of the radial face.

Method for repairing an upstream rail of a turbine engine turbine casing

The present disclosure relates to a holding system for the dismantling of a blade wheel, the blade wheel comprising: a disc, a plurality of blades configured to be mounted circumferentially around the disc, the plurality of blades defining a plurality of inter-blade spaces, each of the inter-blade spaces being defined circumferentially between two adjacent blades of the plurality of blades, the holding system comprising a plurality of inserts, each of the inserts being configured to be inserted into each of the inter-blade spaces in a holding position so as to hold the relative position of the blades when the plurality of blades is dismantled from the disc.

Holding system for the dismantling of a blade wheel

The invention relates to a retaining device for disassembling a bladed wheel of a turbine engine. The invention is characterized in that the retaining device () includes:

Retaining device for disassembling a bladed wheel of a turbine engine and method employing it

A retention device for at least one cooling tube of a cooling system of a turbomachine casing, the casing extending around an axial direction of the turbomachine, the retention device includes a fixing plate suited to being made integral with the casing and a retention element for the cooling tube. The retention device includes an adjustment system configured to adjust the relative position of the retention element with respect to the fixing plate and to absorb a relative movement between the retention element and the fixing plate.

Retention device for a cooling tube for a turbomachine casing

The invention relates to a sealing assembly for a turbine engine, comprising a wheel mounted inside a sectorised ring carrying an abradable material, having at an axial end an annular groove () in which a circumferential rail of the casing is engaged, sealing members being partly engaged in a recess () of a circumferential edge of a ring sector and another part thereof being engaged in a recess of a circumferential edge circumferentially opposite a circumferentially adjacent ring sector, characterised in that each sealing member comprises an axial end portion () arranged radially between the circumferential rail and two adjacent ring sectors.

Turbine sealing assembly for turbomachinery

A method for repairing an upstream rail of a turbine engine turbine casing, the casing including a casing body extending along a longitudinal axis, the upstream rail including: a base including a radial surface, extending substantially radially from the casing body; a plate including an upper surface, extending substantially along the longitudinal axis; and a connection portion between the base and the plate, including a concave surface connecting the radial surface and the upper surface, the concave surface and the radial surface extending on either side of an edge, the method including: covering a surface with a solder, the surface including the upper surface and the concave surface, such that the solder extends substantially until the edge; and a step of machining the covered surface, in a single action, in the direction of the radial surface, and at least until the edge, so as to reshape the surface.

The invention relates to a motor vane for a turbine engine, comprising a body () locally defining a blade provided at the radially outer end with a root (), characterised in that it also comprises at least one sealing element () extending beyond the radially outer end of the root and connected to an area of the root by means of a movable mechanical link ().

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Chaumes en Brie, France

Nicolas Daniel Delaporte