Fan disk configuration

摘要

A gas turbine engine rotor disk (16) has a number of annular hubs (64) circumscribed about a centerline and each of the hubs is connected to a disk rim by a web (68). A plurality of circumferentially spaced apart dovetail slots are disposed through the rim (62), extending circumferentially between disk posts (50), extending axially from a forward end (65) to an aft end (67) of the rim, and extending radially inwardly from a disk outer surface (63) of the rim. Circumferentially extending annular burst slots (70) extend radially through the rim (62) into the dovetail slots between each adjacent pair (72) of the webs (68). In the exemplary embodiment of the invention illustrated herein, the dovetail slots are circular arc dovetail slots. An axially forwardly extending overhang (69) is located radially outwardly on each of the disk posts (50) and a chamfer (39) is on a radially outer corner (45) of the each of the disk posts (50) on a portion of the overhangs (69). A plurality of post holes extending axially aftwardly into the rim (62) wherein each of the post hole extends axially aftwardly into a corresponding one of the disk posts (50).