TURBINE ENGINE BLADE HAVING IMPROVED STACKING LAW

摘要

The invention relates to a turbine engine blade the airfoil of which extends radially between a blade root and an airfoil tip axially between a leading edge (2) and a trailing edge (3) and tangentially between a pressure side and a suction side (5) the profile of said blade consisting of a series of basic profiles in the form of a vane section stacked on one another along a so called stacking line connecting the centre of gravity of all the vane sections characterised in that the projection of said stacking line of the airfoil on at least one plane extending radially from the blade root comprises a double tangential inversion of the direction of the curvature thereof located in the last thirty percent of the height of the airfoil the projection plane being positioned substantially perpendicular to the chord of the blade.