Patent ID: 9739159
Date: 2017-08-22
CPC Classifications: F01D,F05D,Y10T

Claim:
1. A method for relieving stress on a dovetail of a turbine rotor blade in a gas turbine, said method comprising: coupling at least one turbine rotor blade to a turbine disk for rotation about an axis, the at least one turbine rotor blade including a dovetail extending in a radial direction and axially insertable into a correspondingly-shaped slot defined in the turbine disk, wherein the correspondingly-shaped slot includes at least one groove, the at least one groove defined by at least an axially extending, radially upper inner surface, the radially upper inner surface extending in a plane normal to the axis from a circumferentially innermost edge to a circumferentially outermost edge and defining a depth therebetween; defining at least one tang on the dovetail that extends axially along at least a portion of the dovetail, the at least one tang including a pair of axially extending end portions shaped complementary to the at least one groove and configured to contact the radially upper inner surface during rotation of the turbine disk; and defining at least one stress relief surface in the at least one tang, the at least one stress relief surface extending axially between the end portions and recessed relative to an outer surface of the end portions, such that the at least one tang along an axial extent of the at least one stress relief surface is spaced from the radially upper inner surface along an entirety of the depth during rotation of the turbine disk.