Rotor disk with asymmetrical rotor blade slot, corresponding rotor disk assembly and manufacturing method

摘要

A gas turbine engine includes a disk (44) having an annular hub (46) circumscribed about a centerline (A) with an annular web (50) extending radially outward from the hub (46) to an annular rim (48). A multiple of slots (58) extend generally axially through the rim (48) and at least one of the multiple of slots (58) having an asymmetric slot root (64) for lower stress and higher service life.