A compressor rotor of a gas turbine engine includes a rotor body having a face adapted to face an adjacent rotor. The rotor body extends radially between an outer peripheral rim surface and an inner rim surface. The inner rim surface defines a bore of the rotor body. A plurality of blades extends radially from the outer peripheral rim surface. A plurality of anti-vortex fins extends axially from the face of the rotor body facing the adjacent rotor. The plurality of anti-vortex fins forms a plurality of open radial passageways. The plurality of anti-vortex fins extends axially to a predetermined thickness such that, when assembled with the second rotor, axial extremities of the plurality of anti-vortex fins being in close proximity with the adjacent rotor and the adjacent rotor closes the radial passageways. A method of providing a first rotor for assembly with a second facing rotor of a compressor rotor assembly is also presented.

A gas dispersion system may include a drive mechanism, a drive shaft having a proximal end operably coupled to the drive mechanism, extending to a distal end, and configured to transfer rotational motion and torque, a mixing element arranged at or near the distal end of the drive shaft including a hub and multiple blade pairs, each blade pair including an upper blade and a lower blade secured to the hub and cantilevering freely and generally radially away from the hub.