Safran Aircraft Engines

Axel Sylvain Loïc Thomas

Maurice Guy Judet

Gabrijel Radeljak

Fabrice Marcel Noel Garin

Franck Davy Boisnault

Alexandre Xavier Bossaert

Florent Pierre Antoine Luneau

Fabrice Marcel Noël Garin

Cecile Marie Emilienne Alirot

Christian Michel Jacques Gosselin

Cécile Marie Emilienne Alirot

The turbine () for a turbine engine () extends around a major axis (X-X) and comprises: —a casing () comprising an annular hook (), —a movably mounted impeller (), —a ring () extending opposite the impeller in a direction radial to the major axis (XX), —a distributor () comprising a blade provided with a platform (), the platform being extended radially outwards by a spoiler (), the spoiler () being radially mounted on the hook (), and —foils () each having a profiled trough shape in a direction circumferential to the axis, the foils extending in succession in the circumferential direction, each foil () extending between the spoiler () and the hook (). The turbine comprises stops () to prevent the foils () from moving in the circumferential direction. Each foil () comprises a protrusion () arranged so as to extend circumferentially opposite another protrusion () of another adjacent foil ().

Turbine for a turbine engine comprising heat-shielding foils

Assembly () comprising an annular turbine distributor () for turbomachinery (), an annular structural element () of the turbomachinery (), coaxial with the distributor () and at least one device () for attaching the annular distributor () with the annular structural element (), characterised in that: &#x2014;the annular distributor () is crossed by at least two axial passages, and &#x2014;the or each attachment device () comprises: at least two pins (), rigidly connected to the annular structural element () and passing through one of said passages of the distributor (), a first transverse stop () for stopping the distributor () axially and passing through two consecutive pins (), and two second stops () rigidly connected to the structural element () to retain, in the pins (), the first transverse stop () for stopping the distributor () radially.

Assembly for a turbomachine comprising a distributor, a structural element of the turbomachine, and an attachment device

The present invention relates to an assembly () comprising:

Assembly for attaching a nozzle to a structural element of a turbine engine

The turbine () has a rotor () with blades () arranged on a periphery of disks () in radial planes (), and a tie rod () extending along slots () in the disks. An annular spacer (') fixes a position of the tie rod relative to a center line (M) of the disks, and is arranged in a channel (). The spacer has through-openings, which are arranged radially relative to the tie rod or to its center line, and extend coaxially. The channel carries a cooling medium and is limited by a separating pipe () radially outwards. The through-openings serve for flow of the medium.

Turbomachine comprising a shaft sleeve and associated sleeve tube

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Moissy-Cramayel, France

Axel Sylvain Loïc Thomas