FIELD: engines and pumps.
SUBSTANCE: metal part (200) for an aircraft turbojet engine comprising, in particular, the first set of elements (203) having a small thickness and a second set of elements (201; 202) having a greater thickness. The method includes forming a peripheral portion (301) of the elements (201; 202) of the second set of elements by selective melting of the powder layer by scanning the surface of the powder by a laser beam or an electron beam. Use peripheral portion (301) of the elements (201; 202) the second plurality of elements as a mould and perform the operation for filling with liquid metal inner zone (302) bounded by said peripheral portion (301). Cooled metal part (200) for imparting hardness of the inner zone (302) bounded by the peripheral part (301) filled with metal.
EFFECT: increase of reliability.
7 cl, 4 dwg
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