Safran Helicopter Engines

Safran

Messier-bugatti-dowty

Safran Landing Systems

Turbomeca

Julien Gurt Santanach

Fabrice Crabos

Alain Viola

Yann Danis

Julien Esteban

A process for manufacturing a turbomachine part coated with a thermal barrier, includes manufacturing the part by additive manufacture; electrophoretic depositing the part of a layer including particles of a ceramic material; consolidating the layer by heat treatment to obtain a ceramic coating.

Method for producing a thermal barrier on a part of a turbomachine

Subjecting an aluminum or aluminum alloy substrate to anti-corrosion and anti-wear treatment that is applicable in particular in the field of aviation for protecting certain mechanical parts of airplanes or helicopters that are subjected simultaneously to corrosion and to wear, including applying to the substrate, a sol-gel treatment step forming a sol-gel layer; and after the sol-gel treatment step, a hard oxidation step forming a hard oxide layer.

Method of treatment against corrosion and against wear

An aircraft engine-part including at least a metal substrate and a protective coating for protection against erosion that is present on the substrate, the coating including at least one phase including at least chromium at an atom content greater than or equal to 45% and carbon at an atom content lying in the range 5% to 20%, the phase including CrCand CrCchromium carbides. A method of fabricating such a part in which electroplating is used to deposit a coating composition on the part and the part is subjected to heat treatment at a temperature lying in the range 250&#xb0; C. to 70&#xb0; C.

Aircraft engine part including a coating for protection against erosion, and a method of fabricating such a part

A device for performing anodizing treatment on a part, the device including a treatment chamber including a part for anodizing together with a counter-electrode situated facing the part to be treated, the part to be treated constituting a first wall of the treatment chamber; a generator, a first terminal of the generator being electrically connected to the part to be treated and a second terminal of the generator being electrically connected to the counter-electrode; and a system for storing and circulating an electrolyte, the system including a storage vessel, different from the treatment chamber, for containing the electrolyte; and a circuit for circulating the electrolyte in order to enable the electrolyte to flow between the storage vessel and the treatment chamber.

Device intended for implementing an anodization treatment and anodization treatment

A rotor-stator assembly for a gas turbine engine, the assembly including a rotor having a layer of ceramic material forming an abrasive coating deposited on its tip, the layer being constituted mainly by zirconia and possessing a void ratio less than or equal to 15%, and a stator arranged around the rotor and provided facing the tip of the rotor with a layer of ceramic material forming an abradable coating, the layer being constituted mainly by zirconia possessing a void ratio lying in the range 20% to 50% with pores having size less than or equal to 50 &#x3bc;m.

Growing community of inventors

Saint Vincent de Tyrosse, France

Julien Gurt Santanach