BLADE COMPRISING A BLADE WITH PERFORATIONS EQUIPPED WITH INSERTED ELEMENTS TO DELIMIT AN INTERNAL CIRCUIT

摘要

The invention relates to a blade (17) for an aircraft turbomachine, comprising a blade (18) extending along an axis of span (AX) and including a plurality of holes (31, 34) forming a network of communicating holes therein, this blade being fitted with rods (38) attached in all or part of the holes (31, 34) to delimit, jointly with the holes (31, 34), an internal fluidic propagation circuit (X), the holes fitted with at least one rod (38) being formed opening onto the outside of the blade, each rod (38) comprising an alternation of portions (41, 42) provided to selectively allow or block a fluid passage: - along from a part of the hole in which the portion is housed, and / or - to another hole crossing the hole equipped with the portion, at their intersection. Figure for the abstract: Figure 5