Patent ID: 9657746
Date: 2017-05-23
CPC Classifications: F01D,F02C,F04D

Claim:
1. A compressor rotor of a gas turbine engine, the compressor rotor comprising: a rotor body having a face adapted to face an adjacent rotor, the rotor body extending radially between an outer peripheral rim surface and an inner rim surface, the inner rim surface defining a bore of the rotor body; a plurality of blades extending radially outwardly from the outer peripheral rim surface; a plurality of anti-vortex fins extending axially from the face of the rotor body facing the adjacent rotor, the plurality of anti-vortex fins forming a plurality of open radial passageways, the plurality of anti-vortex fins extending 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 axially closes the radial passageways; and an intermediate rim surface disposed on the face facing the adjacent rotor, the intermediate rim surface being disposed between the outer peripheral rim surface and the inner rim surface and connecting the plurality of anti-vortex fins, the intermediate rim surface defining a plurality of inlets connected in flow communication with respective ones of the plurality of radial passageways, the inlets receiving bleed air and directing it radially inwardly to the associated radial passageways.