Safran Aircraft Engines

Snecma

Marion France Chambre

Sebastien Congratel

Bruno Richard

Romain Roullet

Franck Davy Boisnault

Jérôme Claude George Lemonnier

Nicolas Marc Florent

Bruno Marc-Etienne Loisel

Carine Thuy-Huong Pragassam

Kévin Claude Luc Baudy

Sébastien Congratel

Denis Aydin

Thomas Marchyllie

Florian Armand Gabriel Gaudry

A turbine ring assembly extending around an axis, including a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure held by a turbine casing, each ring sector including a base from which an upstream tab and a downstream tab extend radially outward, spaced axially from one another,

Turbine ring assembly mounted on a cross-member

A rotor blade for a rotor disk of a turbine of an aeronautical turbomachine includes, in a radial direction from inside to outside, a blade foot root, a support, a platform and a rotor vane, where the root is connected to the support by a neck. The neck has a curvilinear profile defining, in a section in a plane perpendicular to the radial direction, a curved shape. The neck section overlaps at least 75% of the section of the rotor vane, as a projection of the sections of the neck and of the rotor vane in a plane perpendicular to the radial direction, where the section of the rotor vane joins with the platform.

Turbine rotor disk blade having a foot of curvilinear shape

The invention concerns a fixed flow distribution blading () in a turbomachine, comprising two coaxial annular platforms that are internal () and external respectively, linked to each other by a plurality of radial blades (), in which the internal annular platform () comprises an annular radial partition () and a blade support ring () extending to each side of an outer radial end of said partition (), the blading () further comprising an annular sealing plate () mounted on the internal annular platform (), on the upstream side of the radial partition relative to an airflow in the blading, the blading () being characterized in that the sealing plate () is mounted on the blade support ring (), and in that it comprises a circumferential groove. The invention also concerns a method for producing such a blading and a turbomachine comprising such a blading.

Flow distribution blading comprising an improved sealing plate

The invention relates to a fixed diffuser vanes assembly () for guiding flow through a turbomachine, comprising an internal annular platform () and a plurality of fixed vanes () which are mounted on this platform, the internal platform comprising a support plate () forming the base of said vanes, a radial annular partition () extending from the support plate toward an axis of the vanes assembly, and an internal ring () attached to the radial annular partition and having an internal surface on which an abradable material () is arranged, the vanes assembly being characterized in that the internal ring comprises at least one cut-out () delimiting a tongue (), the tongue being bent to press against the radial annular partition (). The invention also relates to a method of manufacturing such a vanes assembly and to a turbomachine incorporating such vanes.

Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production method

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Moissy-Cramayel, France

Marion France Chambre