METHOD FOR PRODUCING A METAL BLADED ELEMENT OF AN AIRCRAFT TURBINE ENGINE

A method for producing a metal bladed element of a turbine engine, in particular of an aircraft, includes steps of producing the bladed element, depositing a coating made of wear-proof material on at least one portion of the bladed element and verifying, preferably visually, the conformity of the bl...

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Bibliographische Detailangaben
Hauptverfasser:	Loisel, Bruno Marc-Etienne, Nguyen, Alexandre Thanh Nhan, Pragassam, Carine Thuy-Huong, Evrard, Guillaume Sylvain Frédéric
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIRCHEMICAL OR PHYSICAL PROPERTIES LIGHTING MACHINES OR ENGINES IN GENERAL MEASURING MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PHYSICS STEAM ENGINES TESTING WEAPONS
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Beschreibung
Zusammenfassung:	A method for producing a metal bladed element of a turbine engine, in particular of an aircraft, includes steps of producing the bladed element, depositing a coating made of wear-proof material on at least one portion of the bladed element and verifying, preferably visually, the conformity of the bladed element. Verifying the conformity of the bladed element includes implementing a verification element on the bladed element. The bladed element is configured according to a conformity threshold value to conceal a non-conformity of the coating, if the non-conformity has at least one dimension less than the threshold value, and to show at least one portion of this non-conformity if the at least one dimension is greater than the threshold value.