Patent ID: 8602738

Claim:
A rotor disk for a gas turbine, comprising: a base and a plurality of dovetail slots, wherein each of the plurality of dovetail slots is between a pair of dovetail walls; an array of rotor blades, wherein each rotor blade of the array of rotor blades comprises a dovetail and wherein the dovetail of each rotor blade of the array of rotor blades is axially inserted into at least one dovetail slot of the plurality of dovetail slots; one or more fillets provided on a forward or aft side of the base of the rotor disk, wherein the one or more fillets were formed at a prior location of one or more cracks in the base; and one or more conic cuts provided on the base of the rotor disk between the pair of dovetail walls of each of the plurality of dovetail slots, wherein the base is provided at a radially inner surface of each of the plurality of dovetail slots.