Safran Aircraft Engines

Safran Ceramics

Aurélien Gaillard

Clément Jarrossay

Sébastien Serge Francis Congratel

Nicolas Paul Tableau

Clément Emile André Cazin

Antoine Claude Michel Etienne Danis

Pascal Cédric Tabarin

Matthieu Arnaud Gimat

David René Pierre Le Cair

Gilles Gérard Claude Lepretre

Pascal Grégory Casaliggi

Francis Gabriel Michel

Pascal Cedric Tabarin

Arthur Paul Gabriel Nimhauser

Yann Richard

Turbine shroud assembly comprising sections () made from CMC and forming a shroud () and a support structure (), each section having a base () with a radially internal face () and a radially external face (), from which there extend in a projecting manner an upstream attachment lug () and a downstream attachment lug (), the support structure comprising a collar (), from which there radially extend in a projecting manner towards the shroud an upstream radial flange () and a downstream radial flange (), by which the lugs of each section of the shroud are retained, the shroud () being retained by axial pins () which cooperate, on the one hand, with the upstream radial flange, via first and second annular end plates (), and directly with the downstream radial flange and, on the other hand, with the upstream and downstream attachment lugs, respectively.

Turbine shroud assembly

An abradable coating includes a tubular cell structure, wherein the the tubular cell structure includes a fibrous reinforcement of discontinuous short fibers which is densified by a ceramic matrix.

Abradable coating having a honeycomb structure made of composite material having a ceramic matrix made of short fibers

A turbine ring assembly having ring segments made of ceramic matrix composite material and each having first and second attachment tabs and a cavity for the circulation of air flow, a metal support having a first bracket and a second bracket bearing axially upstream against the second tab, a first metal flange arranged upstream of the first bracket and having an inner periphery bearing axially downstream against the first tab and an outer periphery fastened to the first bracket, and air passage orifices formed in the inner periphery of the first flange and/or in the second bracket, the orifices configured to ensure that the air flow passes from the cavity to the outside of the assembly.

Turbine ring assembly for a turbomachine

A turbine engine nozzle extending about an axis and including a vane assembly mounted between an outer shroud and an inner shroud; and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress on the vane assembly towards the outer shroud. The contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device.

Guide vanes assembly with position-maintaining device

A turbine including a casing and a nozzle including an outer metallic shroud secured to the casing, an inner metallic shroud, and a plurality of nozzle segments made of CMC forming a crown extending between the outer shroud and the inner shroud, each segment including a strut, an inner platform, an outer platform and at least one airfoil having a hollow profile traversed by the strut, wherein for

Turbomachine turbine having a CMC nozzle with load absorption and positional adjustment

A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.

Turbomachine stator assembly comprising an inner shroud having upstream and downstream portions assembled by axial translation

Turbine comprising a casing and a nozzle including a metal outer shroud integral with the casing, a metal inner shroud, and a plurality of nozzle sectors of CMC forming a ring extending between the metal outer shroud and the metal inner shroud, each sector including a mast, an inner platform, an outer platform and at least one airfoil having a hollow profile defining an inner recess, each of the inner and outer platforms having an opening communicating with said inner recess, and the mast passing through said openings and the inner recess and being attached to said casing and connected with said nozzle sector. The mast comprises at least one fastening projection having at least one portion extending from a radially outer end of the mast in a direction opposite to the center of the mast and in a plane orthogonal to the radial direction.

Turbomachine turbine having CMC nozzle with load spreading

A turbine assembly () comprising: —a plurality of turbine ring sectors () made of ceramic-matrix composite material, —a ring support structure (), comprising an annular shroud (), and in addition —a plurality of angular spacer sectors () together forming an annular spacer (), said annular spacer () being, on the one hand, fixed to the turbine ring () and, on the other hand, fixed to said annular shroud (), characterized in that said turbine assembly () comprises at least one air diffuser (), which is configured to diffuse cooling air onto the radially outer face () of at least one of said turbine ring sectors (), and in that said at least one air diffuser () is mounted by being nested on one of said angular spacer sectors (), in a nested position.

Turbine assembly, and gas turbine engine provided with such an assembly

A nozzle for a turbomachine turbine. The nozzle includes blades made of ceramic matrix composite material, and at least one metal liner passing through a respective blade. The liner is connected in a sealed manner to a metal internal shroud so as to guide a ventilation fluid through the blade. The nozzle can be configured to maintain effective sealing in spite of the different thermal expansions of the blade and of the internal shroud.

Turbine nozzle having blading made of ceramic matrix composite through which a metal ventilation circuit passes

The invention relates to a turbine assembly comprising: a plurality of ring sectors forming a ring; a support structure comprising a shroud from which there project radial flanges which serve to hold latching tabs of each ring sector; a stator positioned downstream of said ring and comprising a blade provided with a radially outer platform and extending axially opposite said ring; an annular space being defined between the ring, the support structure and the platform, this annular space having passing through it a leakage air current, the assembly comprising a hollow ring which occupies said annular space and which is shaped so as to collect, channel and expel said leakage air current, more specifically to channel and expel it into the radially inner region of said annular space.

Assembly of a turbomachine turbine ring and stator

A turbomachine blade includes a root intended to be mounted in a recessed pocket of a turbomachine rotor disc, the root having two side faces extending radially and longitudinally, each of the side faces including at least one seating intended to be inserted against a side wall of the recessed pocket, along an axis of longitudinal direction and to be in contact with the side walls of the recessed pocket, a radially inner face intended to face the bottom of the recessed pocket when the root is mounted in the recessed pocket, the radially inner face connecting the two side faces, the radially inner face including at least one curved concave surface and two curved convex surfaces, the curved concave surface extending from one end of each of the two curved convex surfaces.

Growing community of inventors

Moissy-Cramayel, France

Aurélien Gaillard