Method for producing a turbine engine part

A method for repairing a turbine engine part, characterized in that it comprises the steps of:

• producing a preform, layer by layer, by selectively melting a powder containing a base material identical or similar to that of the part, the preform having an assembly surface intended to be brazed to the part to be repaired and containing for this purpose a brazing material mixed with the base material, the brazing material being an alloy based on nickel, cobalt:
• 18 to 22%, silicon:
• 4 to 5%, boron:
• 2.7 to 3.15%, and carbon:
• 0 to 0.06%, all in percent by weight, said powder containing the mixture, upon heating to fusion generating heat fluxes, having a main transformation peak of the brazing material, with the greatest amplitude of heat flux, and secondary transformation peaks of the brazing material, with a lesser amplitude of heat flux;
• assembling the preform to the turbine engine part by diffusion brazing,
• wherein the amplitude of the heat flux of said main transformation peak of the brazing material used to make the preform is at least twice the amplitudes of the respective heat fluxes of the secondary transformation peaks of the brazing material, the brazing material further comprising chromium so as to limit the cracking of the parts when they are cooled.