Safran Aircraft Engines

Snecma

Didier Noël Durand

Nicolas Daniel Delaporte

Florence Irène Noëlle Leutard

Eric Herzer

Thierry Michel Breugnot

Anthony Pierre Beguin

Thibault Jamon

Marina Wilma Bilioniere

Gaël Evain

Patrick Jacques Rossi

Arnaud Martin

Olivier Jean Daniel Baumas

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

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 ().

Rotor vane with active clearance control, rotary assembly and operating method thereof

A device for suspending a turbojet casing, the device including a shouldered pin extending through aligned orifices of two lugs of a clevis secured to the casing. A protection piece for providing protection against wear is mounted on each lug of the clevis and has the shouldered pin passing therethrough, the protection piece being prevented from moving in rotation on the lug by co-operating shapes.

Growing community of inventors

Moissy-Cramayel, France

Didier Noël Durand