Snecma

Safran Aircraft Engines

Mersen France Gennevilliers Sas

Patrick Jean-Louis Reghezza

Jean-Bernard Forgue

Michael Delapierre

Julien Tran

Thierry Nitre

Simon Pierre Claude Charbonnier

Nicolas Christian Triconnet

Carole Stochmil

Jack-Pierre Lauvergnat

Pierrick Charles Chevallier

Julien Roset

Antoine Patrice Marie Desreumaux

Yann Christophe Maurice Sarazin

Alain Timon

Jean-Hilaire Lexilus

Didier Monnet

Jérôme Paul Marceau Mace

Fabrice Marois

Eric Gvozdenovic

Richard Lavignotte

Thomas Chrzastek

Thomas Marouane Busson

Cédric Nicolas Bot

Henry Louis Paul Nicolas Loiseau

Sébastien Marc Jean-Michel Perez

Christian Manuel Planas

Laurent Bilz

Dominique Gaveau

Henry Louis Loiseau

Simon Pierre Charbonnier

Antoine Patrice Desreumaux

Yann Christophe Sarazin

Sebastien Marc Perez

Cédric Bot

Pierrick Chevallier

Jean-Bernard André Forgue

Michaël Delapierre

A method for repairing an end plate of a turbomachine rotor, the end plate including a crown having at least two collar fastening holes and at least one balancing-weight fastening hole located between the two collar fastening holes, each collar fastening hole being equipped with a crimped nut, the crown having a damaged portion between two collar fastening holes, the method including the steps of removing the two crimped nuts located on either side of the damage; removing the damaged crown portion, for example by machining; putting in place a strip in the form of a crown portion closing off the removed crown portion, the strip having at least one balancing-weight fastening hole and two mounting holes; fastening the strip to the crown with two crimped nuts, which penetrate the mounting holes, by crimping each nut in a collar fastening hole.

Method for repairing an end plate of a turbomachine rotor

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.

Extraction device of a platform for holding a blade and method using this device

A shutter is provided for repairing a turbine engine having a damaged or absent fixed rectifier blade (), this damaged or absent fixed blade () leaving free an opening () of a ferrule () intended to receive an end of this fixed blade (). The shutter () arranged to close the free opening () by being rigidly attached to this free opening ().

Shutter for turbine machine having an absent rectifier blade

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

Intermediate casing of a turbine engine, provided with a sealing part at the arm/shroud interface

A plug for preventing corrosion of an attachment opening, includes a bottom surface including an opening for receiving a head of a tightening device; a top surface; and a substantially cylindrical side wall extending between the bottom surface and the top surface. The side wall includes a first side area, wherein the plug is formed of a elastically deformable material and has a diameter at rest and resiliency enabling the plug to block, and be held in, a top portion of the attachment opening via resilient change in shape; and the top surface includes at least one first blind hole, the shape of which is such that, when the plug is subjected to an elastic deformation that causes a ridge to appear between the top surface and the first side area of the plug, the ridge is removed by elastic deformation of the blind hole.

Corrosion protection plug for filling an attachment opening, and system including said plug

In the method for carrying out work, according to the invention, in order to maintain a metal turbine engine motor, such as a drum, in an operational state:

Method for carrying out work on a rotor and associated foil

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.

System for repairing a fastener equipping a reactor wall

A method for repairing a fan casing in which the inner surface is damaged, includes attaching a reinforcement element to the fan casing, the reinforcement element being attached to the outer surface of the fan casing opposite the damage.

Method for repairing a fan casing

An axisymmetrical portion for an aircraft turbojet engine intermediate case intended to protrude downstream from an outer axisymmetrical portion of the intermediate case is provided. The axisymmetrical portion includes an annular groove radially open outwards, and at least one insert laid out inside the groove, which covers each internal face of the groove and which is radially open outwards.

Axisymmetrical intermediate case part including an insert positioned in an annular groove

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.

Method for repairing wear marks on a rotor supporting the fan of a bypass engine

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.

Wear-resistant part for the support of a blade of a turbojet fan

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.

Turbine engine fan

A turbomachine rotor including a disc including a rim and axial slots machined in the rim for the individual housing of blades, a ring being attached to one face of the rim, the ring being pierced with holes in the axial continuation of the slots, at least some of the holes in the continuation of the slots including a plug. The plug includes a first half-plug made of a first wear-resistant material and a second half-plug made of a second material, one of the two half-plugs bearing on one side of the ring and the other bearing on the other side of the ring and being connected to one another through the hole. The plug is configured to form an anti-wear device.

Turbomachine rotor comprising an anti-wear plug, and anti-wear plug

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.

Turbomachine rotor with anti-wear shim between a disk and an annulus

A vibration-damping shim configured to be interposed between a platform of a fan blade and a fan disk, including a radially external surface fitted with plates in contact with the fan blade platform, and a radially internal surface formed by an upstream surface, configured to be facing the disk, and a downstream surface separated from the upstream surface by a break in alignment. The upstream surface includes a zone protruding radially towards the interior, initiated at some distance from its upstream end.

Growing community of inventors

Vaux Le Penil, France

Patrick Jean-Louis Reghezza