Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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 Cr7C3 and Cr23C6 chromium 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° C. to 70° C.

Abstract: A method of chromating a part including an aluminum-based alloy, the method including the steps of providing the part including a layer based on aluminum oxide on at least one of its surfaces, of immersing the part in a chromating bath including chromium III, and of performing chemical conversion of the part in the chromating bath. The invention also provides a part obtained by the method.

Abstract: 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.

Abstract: 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 ?m.

Abstract: 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 Cr7C3 and Cr23C6 chromium 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° C to 70° C.

Abstract: 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.

Abstract: 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.

Abstract: 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 ?m.