Safran Aircraft Engines

Mireya Sanchez Gomez

Vijeay Patel

Jean-Philippe Mallat-Desmortiers

Cyril Leo Benoit

Romain Noselli

Jean Cahen

Clément Marchand

Paul Grandin

Alice Marie Clement

Cyril Léo Benoit

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 turbine nozzle for a turbine engine, including two annular walls extending about the same axis, the walls being connected to each other by blades having an aerodynamic profile, the nozzle being divided into sectors and including several nozzle sectors arranged circumferentially end-to-end about a longitudinal axis. The blades include first blades made from a first metal alloy, and second blades made from a second metal alloy different from the first alloy, each nozzle sector including first blades and second blades. The invention also relates to a turbine engine, in particular of an aircraft, including at least one such nozzle. The invention also relates to a method for manufacturing such a nozzle in which each of the sectors is produced, for example, by additive manufacturing.

Bladed turbine stator for a turbine engine

Growing community of inventors

Moissy-Cramayel, France

Mireya Sanchez Gomez