Patent ID: 6019580
Filing Date: 2000-02-01
Classification: F01D

Abstract:
A gas turbine engine comprising:a turbine disk comprising a hub having an axial bore, a web extending radially from said hub and terminating in a rim section extending radially outward from said web, said rim section including first and second radial faces defining a first axial thickness;said rim section including a plurality of slots passing substantially axially from said first radial face to said second radial face defining a live rim radius of said disk, said slots each defining at least one disk fillet adapted to engage a corresponding blade lobe along a contact zone centered about a contact plane, for retaining a turbine blade to said disk;said rim section further including a first bulging region integral to and extending axially outward from said first radial face, said first bulging region having a maximum axial excursion proximal said contact plane; anda first inward taper, said first inward taper comprising a region tapering axially inward with decreasing radial dimension from said maximum axial excursion, said first inward taper beginning at a point radially outward of said live rim radius.