METHOD AND APPARATUS FOR REDUCING ROTOR ASSEMBLY CIRCUMFERENTIAL RIM STRESS

摘要

A rotor assembly (14) for a gas turbine engine (10) operates with reduced circumferential rim stress. The rotor assembly includes a rotor (16) including a plurality of rotor blades (18) and a radially outer platform (48). The rotor blades extend radially outward from the platform. A root fillet (80) extends circumferentially around each blade between the blades and platforms. The platforms include an outer surface (50) including a plurality of indentations (64) extending between adjacent rotor blades. Each indentation extends from a leading edge (60) of the platform to a trailing edge (62) of the platform with a depth (72) that tapers to an approximate zero depth at the trailing edge.