Patent ID: 8192141

Claim:
A gas turbine rotor comprising: a plurality of first axial compression blades configured for compressing air in a first direction, the plurality of first axial compression blades having a first blade quantity and a first blade height; and a plurality of second axial compression blades configured for compressing the air from the first axial compression blades in a second direction, the second direction being generally opposite the first direction, the plurality of second axial compression blades having a second blade quantity that is greater than the first blade quantity and a second blade height that is less than the first blade height, wherein the plurality of second axial compression blades are discontinuous with the plurality of first axial compression blades and extend radially outward from the plurality of first axial compression blades such that the plurality of second axial compression blades are substantially coplanar with the plurality of first axial compression blades.