Turbomachine blade with airfoil designed to improve aerodynamic and mechanical properties

摘要

The present invention provides a turbomachine blade having a plurality of blade cross-sections stacked along a radial axis (Z-Z), each blade cross-section having a longitudinal axis (X--) between a leading edge and a trailing edge. X), extending along the tangential axis (Y-Y) between the pressure surface and the suction surface, the blade cross section depending on the height of the blade extending from the root to the top of the blade, Turbomachine blades arranged according to a longitudinal Xg distribution law and a tangential direction Yg distribution rule that define the positioning of the respective center of gravity of the blade cross-section with respect to the longitudinal axis (XX) and the tangential axis (YY) Each of the longitudinal Xg distribution law and the tangential direction Xg distribution law relates to a turbomachine blade including a change in inclination direction in a range of 90% to 100% of the blade height.