Safran Aircraft Engines

Vijeay Patel

Ba-Phuc Tang

Alexandre Gimel

Stéphane Knittel

Bruno Marc-Etienne Loisel

Josserand Jacques André Bassery

Pragash Douglas

Camille Maryse Martine Palomba

Mireya Sanchez Gomez

Alice Marie Clement

Paul Grandin

Clément Marchand

Etienne Léon Francois

Robert Fiarda

Pauline Namvong

Quentin Bruno Guy Andre Emile Lievoux

Quentin Bruno Guy André Emile Lievoux

Guillaume Evrard

The turbomachine subassembly including at least one low-pressure nozzle ring, the nozzle ring including a root integral with the nozzle ring, a clamp configured so as to fasten the root to a casing of the turbomachine; and at least two pads interposed between the root and the clamp. Each pad being assembled in a form-fitting manner with one of either the root or the clamp.

Turbojet engine nozzle ring for an aircraft

A method for refitting blade shrouds of a rotor wheel in an aircraft turbomachine is described. The rotor wheel has a disc bearing blades that each have an airfoil extending between a root and a shroud, the shroud of each blade having lateral edges including shapes complementary to the lateral edges of the shrouds of the adjacent blades. The lateral edges of the shrouds are interlocked in engagement with one another such that anti-wear coatings of these edges are in contact with one another in a desired interlocking engagement position, and at least one of the lateral edges of at least one of the shrouds being able to be disengaged from the lateral edge of an adjacent shroud in an undesired disengagement position. The method includes, when an undesired disengagement position is detected, a step of inserting a re-engagement device into the turbomachine.

Method for refitting blade shrouds of a rotor wheel in an aircraft turbomachine

A turbomachine rotor blade includes a radially outer end equipped with a heel, the heel being provided with at least one sealing wiper, the or each sealing wiper projecting beyond the heel along a first axis, the first axis being at &#xb1;15&#xb0; with respect to a radial direction, and extending along a second axis, substantially perpendicular to the first axis, between a first upper-surface end and a second lower-surface end, the or each sealing wiper having a first upstream side and a second downstream side as well as a radially outer surface, wherein the or each sealing wiper includes a base attached to the heel and an end piece removably interlocked with the base.

Rotor blade for a turbomachine

An assembly includes: a movable blade for a turbomachine including a tip; and a removable part including an anti-wear material, configured to be attached removably to an edge of the tip to limit wear of the tip.

Removable anti-wear part for blade tip

Growing community of inventors

Moissy Cramayel, France

Vijeay Patel