FIELD: powder metallurgy.
SUBSTANCE: invention relates to powder metallurgy, in particular to a method for additive manufacturing of a blade of an aircraft gas turbine engine. A blade is made, containing upper and lower circumferential walls, between which there is at least one nib containing a front edge and a rear edge located between the mentioned walls, at least partially indented relatively to the first and the second circumferential edges of the mentioned walls, respectively. By laser melting of a powder layer on a base plate, first of all, the first or the second circumferential edges are made directly on the base plate. Simultaneously with the first or the second circumferential edges, at the level of at least one nib of the blade, at least one temporary supporting element is made with at least one recess located between the base plate and front or rear edge of the nib. Removal of one supporting element by breaking its connection with front or rear edge is carried out using a tool, at least one end of which is inserted into at least one recess of the supporting element, and the mentioned tool is rotated in a plane perpendicular to the corresponding front or rear edge.
EFFECT: rigidity of the supporting element is increased and its removal is simplified.
10 cl, 5 dwg
