Method for forming a metal alloy coating such as mcraly

C - Chemistry – Metallurgy – 23 – C

Patent

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Details

C23C 18/16 (2006.01) C23C 18/50 (2006.01) C23C 24/00 (2006.01) F01D 5/28 (2006.01)

Patent

CA 2355692

The invention concerns a method comprising the following steps: a) producing, on a powder a precursor alloy containing at least the elements Cr, Al and Y, a chemical or electrolytic deposition of at least a modifying element such as platinum, palladium, ruthenium or rhenium, from a first bath containing the ions of said element; b) producing on said substrate a simultaneous chemical deposition of nickel and/or cobalt and the resulting modified powder, from a suspension of the latter in a second autocatalytic bath containing nickel and/or cobalt ions, to obtain said coating. The modifying element enhances the capacity of the coating to form from phase beta , by exposure to oxygen at high temperature, an adhesive alumina surface barrier.he invention is useful for protecting against corrosion and oxidation at high temperatures aviation turbine blades.

Le procédé comprend les étapes suivantes: a) on réalise, sur une poudre d'un alliage précurseur contenant au moins les éléments Cr, Al et Y, un dépôt chimique ou électrolytique d'au moins un élément modificateur tel que le platine, le palladium, le ruthénium ou le rhénium, à partir d'un premier bain contenant des ions de cet élément; et b) on réalise sur ledit substrat un dépôt chimique simultané de nickel et/ou de cobalt et de la poudre ainsi modifiée, à partir d'une suspension de cette dernière dans un second bain autocatalytique contenant des ions nickel et/ou cobalt, pour obtenir ledit revêtement. L'élément modificateur renforce l'aptitude du revêtement à former à partir de la phase .beta., par exposition à l'oxygène à température élevée, une barrière superficielle adhérente d'alumine. Application à la protection contre la corrosion et l'oxydation aux températures élevées des aubes de turbines aéronautiques.

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