Safran Aircraft Engines

Safran Ceramics

Gaël Frédéric Claude Cyrille Evain

Olivier Arnaud Fabien Lambert

Jean-Baptiste Vincent Desforges

Lucien Henri Jacques Quennehen

Thierry Guy Xavier Tesson

Patrick Jean Laurent Sultana

David Marsal

Cyrille Telman

Mathieu Charles Jean Verdiere

Mathieu Louis Jean Leduc

Pierre-Louis Alexandre Carlos

Franck Robert Drouet

David Mathieu Paul Marsal

Paul Georges Rodrigues

Claire Charlotte Groleau

The invention relates to a device () for maintaining at least one cooling tube (T) outside a turbomachine casing (), comprising:

Device for maintaining at least one cooling tube on a turbomachine casing and the mounting method thereof

A gas turbine engine includes a device for providing sealing between one rotor section and one stator section. The device includes a coating made of an abradable material attached to the stator section. The device further includes a lip on a portion of the rotor section. The lip is configured to form a seal with the abradable material. The gas turbine engine further includes passages for a gaseous fluid and means for blowing such gaseous fluid. The passages open into the rotor section provided with the lip, so that blown gaseous fluid can be present in a zone radially located between the coating and the lip.

Turbine engine and air-blowing sealing method

A casing of a turbine of a turbine engine includes an internal shroud, an external shroud extending around the internal shroud, and hollow arms connecting the external shroud to the internal shroud and each intended to receive a tubular auxiliary element, each hollow arm defining an inner housing connecting a first passage orifice passing through the internal shroud in the radial direction to a second passage orifice passing through the external shroud in the radial direction, and including an inner wall facing the inner housing. Each arm includes at least one protrusion on the inner wall of the arm protruding from the inner wall towards the inner housing and defining a constriction of the inner housing in a section plane orthogonal to the direction in which the arm extends.

Turbine engine casing

A method of assembling a turbine for a turbine engine that includes mounting annular sectors around the blades to form an abradable ring that includes a groove in a sector of the annular sectors. The method also includes engaging a first wiper of a particular blade of the blades with the groove of the sector. The method further includes axially engaging an assembly comprising the blades and the annular sectors in a casing of a turbine, so that fixing members of the annular sectors cooperate with flanges of the casing to fix the annular sectors in the casing, around the blades. The fixing members comprise at least one upstream fixing member fixed on a radially internal facing side of an upstream end of the annular sectors and at least one downstream fixing member arranged at a downstream end of the annular sectors.

Turbine for a turbine engine and method of assembling same

The invention relates to a turbine for a turbine engine, having a stator and a rotor comprising a rotor wheel having vanes the radially external periphery of which comprises at least one lip which radially extends outwards, with sealing means radially extending about the vanes and comprising a ring. The radially external end of the lip cooperates with said ring so as to form a seal of the labyrinth type.

Turbine for a turbine engine

A turbine for a turbine engine, the turbine comprising a rotor including blades the radially external periphery of which includes at least one first wiper radially extending outwards, sealing means radially extending about the blades and including a ring made of abradable material, with the radially external ends of the wipers cooperating with said ring made of abradable material so as to form a labyrinth-type seal, wherein said ring includes at least one first portion axially extending upstream of the first wiper and a second portion, different from the first portion, axially extending downstream of the first wiper, with the first portion and/or the second portion including a groove, wherein the first wiper has been inserted, with said groove being defined by the first portion and by the second portion.

A turbine ring assembly includes ring sectors made as a single piece of ceramic matrix composite material and being for mounting on a metal ring support structure, the ring support structure having two tabs extending radially towards a gas flow passage, each ring sector having a first portion forming an annular base with a radially inside face defining the inside face of the turbine ring and an outside face from which there extend two tab-forming portions, the ring sectors having a section that is substantially &#x3c0; shaped. The tabs of each ring sector fit axially over the tabs of the ring support structure with contact between the tabs of the ring support structure and the tabs of each ring sector when cold. The tabs of each ring sector are held to the ring support structure by pegs passing through holes formed in the tabs of each ring sector.

Growing community of inventors

Moissy-Cramayel, France

Gaël Frédéric Claude Cyrille Evain