Safran Aircraft Engines

Snecma

Patrick Sultana

Olivier Renon

Guillaume Sevi

Benoit Argémiro Matthieu Debray

Guy Vieillefond

Yannick Durand

Boucif Bensalah

Dominique Michel Fouquet

Grégory Ghosarossian-Prillieux

Sébastien Jean Laurent Prestel

Laurent Cédric Zamai

Florence Irène Noëlle Leutard

Clément Charles Jérémy Coiffier

Pierrick Raphael Americo Bauduin

Florence Irene Leutard

Pierrick Raphael Bauduin

A turbine includes a first rotor and a second rotor that can rotate in opposite directions and are interleaved. The turbine further includes a ring to which abradable material is secured, the ring, unsegmented, extending between the first impellers of the first rotor and the second rotor, over a sector of between 350 and 360°, and, axially between an upstream end and a downstream end of the ring, the ring is held with the second rotor.

Gas turbine for twin-rotor aircraft

A method for manufacturing a casing, for example, an exhaust casing, for a turbomachine. The method generally includes: (a) producing casing sectors, each casing sector having a hub sector, a ferrule sector, and at least one arm linking the hub and ferrule sectors, (b) arranging the casing sectors adjacently and circumferentially, such that each hub sector has longitudinal edges facing longitudinal edges of adjacent hub sectors, (c) welding the longitudinal edges facing the hub sectors, and (d) adding and welding at least a second part of the ferrule to the casing sectors.

Method for manufacturing a turbomachine exhaust casing from segments welded together

A casing is provided, for example, an exhaust casing for a turbomachine. The casing generally includes an inner hub having an axis of rotation and an outer annular ferrule extending around the hub, the ferrule configured to define, with the hub, an annular flow path for a gas stream. In some examples, the ferrule is rigidly connected to the hub by arms. The hub generally includes, at one longitudinal end, a scalloped annular flange comprising solid portions distributed at regular intervals about said axis and spaced apart from each other by hollow portions. The hub is produced by assembling several angular hub sectors arranged circumferentially end to end around the axis, each hub sector connected to an adjacent hub sector by a longitudinal weld bead that extends over substantially the entire axial extent of the hub and that is substantially aligned axially with a hollow portion of said flange.

Turbomachine exhaust casing and method for manufacturing same

A support system () for a structural casing of a turbomachine (), which comprises:

Handling fitting with movable jaws for a turbomachine casing

An extraction sleeve for extracting two rotationally symmetrical parts that are joined together by interference fit, the extraction sleeve including: a head having a conical part; a cylindrical body, the internal part of the cylindrical body having a screw thread suitable for the screwing of an extraction screw; the conical part of the head of the extraction sleeve forming a friction component suitable for coming into contact with one of the rotationally symmetrical parts, the friction component being designed so as to determine a limit slipping torque greater than the friction torque generated at the screw thread of the sleeve by screwing of the extraction screw.

Extraction sleeve

A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins extending outwards in a radial plane from the annular portion, each fin forming an angle relative to the radial direction. The fins have fastener zones at their outer peripheries, the fastener zones being inclined in the axial direction of the support so as to be suitable for fastening to an exhaust cone of the turbine engine.

Air exhaust tube holder in a turbomachine

A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins that are inclined relative to the axial direction of the annular portion and relative to the radial plane, the radially outer periphery of each fin being for fastening to an exhaust cone of the turbine engine.

Growing community of inventors

Moissy-Cramayel, France

Patrick Sultana