Safran Aircraft Engines

Clément Emile André Cazin

Clément Jarrossay

Aurélien Gaillard

Pascal Cédric Tabarin

Sébastien Serge Francis Congratel

Nicolas Paul Tableau

Antoine Claude Michel Etienne Danis

Arthur Paul Gabriel Nimhauser

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.

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

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.

Growing community of inventors

Moissy-Cramayel, France

Clément Emile André Cazin