Abstract: A rotor stage assembly 20 of the type adapted for use in an axial flow gas turbine engine is disclosed. The assembly includes a rotor disk 36 having blade attachment slots 42 configured to receive a plurality of rotor blades 40. Each rotor blade is insertable into the disk in a generally axial direction. Each rotor blade is retained against fore and aft movement by a lock pin 52. The disk is adapted by a groove 44 and the blade is adapted by a groove 48 to receive the lock pin. During assembly the lock pin is slidable in the grooves 44,48 to bring the lock pin into engagement with the corresponding groove in a rotor blade in a corresponding groove in the disk.

Abstract: A lightweight, rotor assembly for a gas turbine engine having a critical speed characteristic well above the operating speed is disclosed. Various construction details which enhance the axial stiffness of the rotor assembly and which shield a portion of the disk from working medium gases are developed. The rotor assembly employs a frustoconical member to connect a shaft to the disk.