BLADED DISK FIXING UNDERCUT

摘要

An undercut (50) is provided in a gas turbine engine disk (30) to smooth out an uneven axial distribution of radial stress in the disk (30). The undercut (50) is defined radially inwardly of the blade attachment slots (46) provided at the periphery of the disk (30). A preferred embodiment is described herein the rotor is a swept fan with blades that are asymmetric, thereby causing an uneven axial distribution of radial stress along blade roots and corresponding blade attachment slots. A corresponding method of smoothing out an uneven axial distribution of radial stress in gas turbine engine rotor disk is also disclosed.