TURBINE ENGINE BLADE HAVING IMPROVED STACKING LAW

摘要

Blade whose blade extends radially between a blade root and a blade head, axially between a leading edge and a trailing edge and tangentially between a lower surface and an upper surface, the profile of the blade being formed by a series of elementary profiles, in the form of a wing section, stacked on top of each other along a stacking line joining the center of gravity of all the sections, the projection of the stacking line of the blade on a plane extending radially from the root of the blade comprising at least one axial inversion of the direction of its curvature, this axial inversion being situated over the last thirty percent of the height of the blade, the plane of projection of this axial inversion being oriented substantially parallel to the chord of the blade, with the aim of improving the efficiency of a compressor stage, or of a turbine, of a turbomachine, the particular shape of the blade reducing the impact of the leakage flow between the intrados and the upper surface of the blade, without the need to modify the compressor housing.