Turbine blade for aircraft, has air passage holes with impact distance along directing line, where distance is evolutionary in radial direction of blade to adapt cooling intensity at point of impact of fresh air on leading edge

摘要

The blade (1) has a cooling cavity (12) partially delimited by a leading edge (2), and a fresh air circulation cavity (10). The cavities are separated by a separation wall (14) pierced of air passage holes (16). Each hole has an outlet (18) defining a directing line (19) for ejecting air within the cavity (12) and an impact distance (Di) along the line between the outlet and a point of impact (20) of fresh air on the edge, where holes are distributed along a radial direction of the blade. The distance is evolutionary in the direction to adapt cooling intensity at the point of impact.