Gas turbine engine rotor sections held together by tie shaft, and rotor having a blade rim undercut

摘要

A section for use in a gas turbine engine and comprising a plurality of adjacent stages (40,42), each of said stages including an integrally bladed rotor, and a plurality of blades extending from each of said rotors, and said blades having airfoils (50). At least one of said rotors having blades with an undercut (64) at a downstream edge of said airfoil in an area where said airfoil merges with a platform (52), and a tie shaft (30) for transmitting a force into said one of said rotors (40), which is then passed to said adjacent rotors.