Patent ID: 6634863
Filing Date: 2003-10-21
Classification: F01D,Y02T

Abstract:
A gas turbine engine rotor assembly comprising:a disk having 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 circular arc 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, web channels disposed axially between said webs and radially between said rim and said hubs, said web channels having maximum widths extending axially between said webs and channel lengths extending radially between said rim and said hubs wherein said maximum widths and said channel lengths are on the same order of magnitude, a plurality of fan blades having circular arc dovetail roots disposed in said circular arc dovetail slots, rounded web channels having radially inner and outer fillets extending axially between said webs and radially between said rim and said hubs, circumferentially extending annular burst slots extending radially through said rim into said dovetail slots between each adjacent pair of said webs, and 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.