Process for manufacturing a gas turbine engine blade

A part comprising:

• a gas turbine engine blade comprising a base, a root and an air stream area extending between the base and the root, and
• at least one protuberance protruding from a main face of the air stream area,
• wherein the at least one protuberance further comprises a plurality of protuberances, and wherein:
• the plurality of protuberances comprises at least two transverse ribs, each transverse rib of the at least two transverse ribs extending from a first longitudinal edge of the air stream area to a second longitudinal edge of the air stream area, at least one transverse rib of the at least two transverse ribs being curved, or
• the plurality of protuberances comprising at least two radial ribs, each radial rib of the at least two radial ribs being located in an alignment of a same midpoint of the air stream area.

A method for manufacturing a blade of a gas turbine engine, the method comprising:

• manufacturing a part, the part comprising a base, a root and an air stream area extending between the base and the root, the air stream area comprising at least one protuberance protruding from a main face of the air stream area, the manufacturing being carried out by injecting a mixture, the mixture comprising a binder and a powder, and the powder comprising at least one metal or at least one ceramic;
• debinding the part so as to eliminate a major part of the binder from the part;
• heat treating the part;
• and
• eliminating the at least one protuberance of the air stream area,
• wherein the at least one protuberance further comprises a plurality of protuberances, the plurality of protuberances comprising at least two radial ribs, each radial rib of the at least two radial ribs being located in an alignment of a same midpoint of the air stream area.