AN AIRFOIL FOR A ROTOR DISK OF A MULTISTAGE AXIAL FLOW COMPRESSOR ,IN PARTICULAR FOR A GAS TURBINE ENGINE

摘要

The invention relates to an airfoil (12) for a rotor disk (14) of a multistage axial flow compressor, in particular for a gas turbine engine, the rotor disk (14) having axial, tangential, and radial orthogonal axes, comprising: pressure and suction sides (18, 20) extending radially from root (22) to tip (24) and axially between leading and trailing edges (26, 28); transverse sections constituting the airfoil (12) having respective chords (30) and camber lines (32) extending between said leading and trailing edges, and centers of gravity (34) aligned in a bowed stacking axis (36); and said suction side (20) being bowed in tangential axis along said trailing edge (28) adjacent said root (22) for reducing flow separation thereat.