FIELD: aircraft.
SUBSTANCE: blade (102) of an aircraft gas turbine engine, wherein the blade comprises at least one internal cavity (100) for circulation of the ventilation air flow, whereas the cavity has a wall (104) that comprises the first protruding elements (106) oriented in the first direction and forming elements of perturbation of the air flow, and this wall additionally comprises at least one second protruding element (108), oriented at least in a second direction different from the first direction, and this second element and at least one of the first elements overlap each other in one zone, characterized in that the first element or each first element that overlaps the second element has a height (H2, H4') greater than the height (H1) of the second element in said zone and which exceeds the height (H3) of the other first wall elements, to maintain its function as an element of perturbation throughout its length.
EFFECT: efficiency of blade cooling.
9 cl, 8 dwg
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