A compressor for a gas turbine engine, comprising: a first rotor (R6) supporting a first plurality of circumferentially spaced rotor blades, a second rotor (R7) disposed axially downstream of the first rotor (R6) and supporting a second plurality of circumferentially spaced rotor blades and a third rotor (R8) disposed axially downstream of the second rotor (R7) and supporting a third plurality of circumferentially spaced rotor blades; a first bore cavity between the first rotor (R6) and the second rotor (R7) and a second bore cavity between the second rotor (R7) and the third rotor (R8); a fluid passageway configured to provide cooled air to the first bore cavity and the second bore cavity ; a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity ; a second anti-vortex component positioned proximate the second bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the second bore cavity ; and a third bore cavity located between the third rotor (R8) and an aft hub , wherein the first anti-vortex component comprises a first anti-vortex tube and the second anti-vortex component comprises a second anti-vortex tube, characterised in that the compressor further comprises: a third anti-vortex tube positioned within the third bore cavity , in fluid communication with the fluid passageway and positioned downstream of the third rotor (R8), and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the third bore cavity ; and an orifice through the aft hub configured to introduce a third cooled air flow path from the third bore cavity into a downstream rim portion of the third rotor (R8). a first rotor (R6) supporting a first plurality of circumferentially spaced rotor blades, a second rotor (R7) disposed axially downstream of the first rotor (R6) and supporting a second plurality of circumferentially spaced rotor blades and a third rotor (R8) disposed axially downstream of the second rotor (R7) and supporting a third plurality of circumferentially spaced rotor blades; a first bore cavity between the first rotor (R6) and the second rotor (R7) and a second bore cavity between the second rotor (R7) and the third rotor (R8); a fluid passageway configured to provide cooled air to the first bore cavity and the second bore cavity ; a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity ; a second anti-vortex component positioned proximate the second bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the second bore cavity ; and a third bore cavity located between the third rotor (R8) and an aft hub , wherein the first anti-vortex component comprises a first anti-vortex tube and the second anti-vortex component comprises a second anti-vortex tube, characterised in that the compressor further comprises: a third anti-vortex tube positioned within the third bore cavity , in fluid communication with the fluid passageway and positioned downstream of the third rotor (R8), and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the third bore cavity ; and an orifice through the aft hub configured to introduce a third cooled air flow path from the third bore cavity into a downstream rim portion of the third rotor (R8). <EOS>