| 摘要 |
<p>The method comprises forming a preform (1) by selective melting of powder containing a base material (60%), which is identical or similar to a turbine engine part, where the preform has a surface that contains a brazing material and is intended to brazed on the part (17) to be repaired, maintaining the preform in the part by laser pointing, degreasing and/or pickling the surface to be brazed, assembling the preform with the part by diffusion brazing, and depositing the brazing material on the surface of the preform. The method comprises forming a preform (1) by selective melting of powder containing a base material (60%), which is identical or similar to a turbine engine part, where the preform has a surface that contains a brazing material and is intended to brazed on the part (17) to be repaired, maintaining the preform in the part by laser pointing, degreasing and/or pickling the surface to be brazed, assembling the preform with the part by diffusion brazing, and depositing the brazing material on the surface of the preform. A melting temperature of the brazing material is lower than a melting temperature of the powder containing the base material. The step of deposition of brazing material is performed by laser projection or by plasma projection of brazing powder. An independent claim is included for a turbine engine part.</p> |
