Patent ID: 6520742
Filing Date: 2003-02-18
Classification: F01D,F05D,Y02T

Abstract:
A gas turbine engine rotor disk comprising:a number of annular hubs circumscribed about a centerline, said hubs connected to a disk rim by respective webs, a plurality of circumferentially spaced apart dovetail slots disposed through said rim, extending circumferentially between disk posts, extending axially from a forward end to an aft end of said rim, and extending radially inwardly from a disk outer surface of said rim, circumferentially extending annular burst slots extending radially through said rim into said dovetail slots between each adjacent pair of said webs, each of said burst slots having a cross-section in a shape of an ogive with a radially outer ogive radius and a radially inner ogive radius and said radially inner ogive radius is substantially larger than said radially outer ogive radius, and rounded web channels having radially inner and outer fillets extend axially between said webs and radially between said rim and said hubs.