Patent ID: 9650896
Date: 2017-05-16
CPC Classifications: F01D,F04D,F05D,Y02T

Claim:
1. A turbomachine blade, comprising: an airfoil which extends radially between a blade root and an airfoil tip, axially between a leading edge and a trailing edge, and tangentially between a pressure face and a suction face, a profile of the blade including a series of elementary profiles, in a form of vane sections, stacked on one another along a stacking line joining centers of gravity of all of the sections, wherein a projection of the stacking line of the airfoil onto a plane extending radially from the blade root comprises an axial inversion of curvature, wherein the axial inversion is situated in a last 30 percent of height of the airfoil, the plane of projection of the axial inversion being oriented substantially parallel to a chord of the blade, wherein directions of curvatures of the leading edge and the trailing edge change at a radial position of the axial inversion, and the leading edge and the trailing edge are both axially offset at a same amount and in a same direction from the stacking line at the radial position of the axial inversion, and wherein the axial inversion is situated over a last 10 percent of the height of the airfoil.