Safran Aircraft Engines

Pascal Cédric Tabarin

Clément Jarrossay

Clément Emile André Cazin

Aurélien Gaillard

Sébastien Serge Francis Congratel

Nicolas Paul Tableau

Damien Bonneau

Nicolas Contini

Francesco Salvatori

Arthur Paul Gabriel Nimhauser

A high-pressure gas turbine for a turbomachine includes a nozzle guide vane assembly, an annular array of movable blades mounted downstream of the nozzle guide vane assembly, a bleed cavity, an upstream sealing element mounted on the nozzle guide vane assembly and a downstream sealing element mounted on the annular array of movable blades, a double baffle being formed by said upstream and downstream sealing elements, an external upstream cavity being formed in the upstream sealing element.

High-pressure gas turbine for turbomachine and turbomachine

A high-pressure gas turbine for a turbomachine includes a nozzle guide vane assembly, an annular array of movable blades mounted downstream of the nozzle guide vane assembly, a first recirculation cavity, a second recirculation cavity, and a bleed cavity. An upstream sealing element is mounted on the nozzle guide vane assembly and a downstream sealing element is mounted on the annular array of movable blades.

High-pressure gas turbine for a turbine engine and turbine engine

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 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 turbine ring assembly extending around a longitudinal axis and comprises:

Turbine ring assembly

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.

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Moissy-cramayel, France

Pascal Cédric Tabarin