Safran Aircraft Engines

Etienne Gérard Joseph Canelle

Jacques Marcel Arthur Bunel

Alexandre Corsaut

Bruno Giardini

Pierrick Bernard Jean

Faouzi Aliouat

Emeric Christian Amaury D'Herbigny

Rémi-Paul Honoré Godier

The present document relates to an annular assembly for a turbomachine turbine, in particular of an aircraft, said annular assembly extending about a longitudinal axis X and comprising: a distributor fixed to an external casing; a bladed disc mounted so as to rotate inside the external casing; said bladed disc being surrounded by a circumferentially segmented ring carried by the external casing and formed by a crown arranged radially on the outside of the bladed disc and by an annular deflector that is carried by an upstream edge of the crown and extends radially towards the inside from said upstream edge of the crown; characterized in that it comprises sealing members () between two circumferentially adjacent ring segments, these sealing members () comprising first circumferential sealing means () between two circumferentially consecutive deflector segments.

Annular assembly for a turbomachine turbine

A turbomachine sealing ring has an axis of revolution and includes an annular support, an annular coating made of abradable material which is carried by the support, and an annular thermal protection plate which is carried by the support. The ring is divided into sectors and has a plurality of ring sectors disposed circumferentially next to one another about the axis. Each ring sector has a support sector, a coating sector, and a plate sector. Each plate sector ling includes a flat tab that is pressed against a face of the corresponding support sector and is fixed to this face by brazing. The tab is inserted into a through-slot in the support sector in order to improve its integrity in operation.

Turbomachine sealing ring

The thermal shrinkage of a casing () to regulate as best as possible the internal play between the rotor and the stator is carried out by a ring () fixed onto the skin () rather than by a circular ramp at a distance therefrom. The ring () comprises, between a collection box () and the skin (), a foraminous plate (), placed on an opening of the box () parallel to the skin () and at a short distance, in order to impose invariable and known ventilation conditions.

Device for cooling a turbomachine casing

A part for a turbine engine, the part having a general annular shape about an axis of revolution, this part including a first annular shrink-fitted mounting flange and comprising an annular row of orifices for the passage of screws, this part being made by casting and including protruding pads required for the control and the manufacture of the part by casting, wherein the pads are located on the flange and in that each comprises a thread configured to engage with an extraction screw of the flange.

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Moissy-Cramayel, France

Etienne Gérard Joseph Canelle