Abstract: A rotor blade is disclosed herein. The rotor blade comprises a nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1. Wherein X and Y are distances in millimeters which, when connected by smooth, continuing arcs, define airfoil profile sections at each distance Z in millimeters. The airfoil profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: A rotor blade is disclosed herein. The rotor blade comprises a nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1. Wherein X and Y are distances in millimeters which, when connected by smooth, continuing arcs, define airfoil profile sections at each distance Z in millimeters. The airfoil profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: A blade of a rotor of a second stage of a compressor can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), where the axis (Z) is a radial axis intersecting the central axis of the compressor. The blade has a profile which can be identified by a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis. The blade also has a non-linearly variable trend of decreasing maximum thickness defined by the closed curves, substantially parallel to a base portion of the blade itself, fixable to the rotor. The variable trend of maximum thickness is substantially situated midway up the blade and is suitable for shifting the natural resonance frequencies of the blade itself outside a functioning velocity range of the rotor.

Abstract: The invention relates to 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, the blade having a profile which can be identified by having a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, the blade also comprising a thickening, substantially parallel to a base portion of the blade itself, fixable to said rotor, said thickening being substantially situated half-way up the blade and being suitable for shifting the natural resonance frequencies of the blade itself outside a functioning frequency range of said rotor.

Abstract: The invention relates to a blade (10) of a rotor of a second 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 (10) having a 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 (10) also comprising a thickening (30), substantially parallel to a base portion (12) of the blade (10) itself, fixable to said rotor, said thickening (30) being substantially situated midway up the blade (10) and being suitable for shifting the natural resonance frequencies of the blade (10) itself outside a functioning velocity range of said rotor.

Abstract: The invention relates to a blade (10) 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 (10) having a 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 (10) also comprising a thickening (30), substantially parallel to a base portion (12) of the blade (10) itself, fixable to said rotor, said thickening (30) being substantially situated half-way up the blade (10) and being suitable for shifting the natural resonance frequencies of the blade (10) itself outside a functioning frequency range of said rotor.