Patent ID: 7766624

Claim:
A blade of a rotor of a ninth phase of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, said blade having an aerodynamic profile which can be identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, said blade comprising: a base portion fixable to said rotor, the aerodynamic profile extending from a foot at said base portion to a free end distal from said base portion, a first thickening, substantially parallel to said base portion, said first thickening being substantially situated halfway up the blade, and a further thickening, substantially parallel to said base portion and situated close to said free end, said further thickening having a maximum thickness less than a thickness of the blade at said foot, said first thickening and said further thickening being suitable for shifting the natural resonance frequencies of the blade itself outside a functioning frequency range of said rotor.