Stress reducing method for gas turbine engine's disk and blade, involves optimizing start point and cut angle based on blade and disk geometry, and positioning datum line at fixed distance from face of dovetail along centerline of axis

摘要

The method involves determining a start point for a dovetail backcut relative to a datum line, where the start point of the backcut is 1.645 inches in an aft direction from the datum line. A material is removed from a blade dovetail (16) or a disk dovetail slot (14) based on the point and a cut angle of about 0.7-3 degrees to form the backcut. The start point and the cut angle are optimized according to geometry of a gas turbine blade (12) and gas turbine disk (10). The datum line is positioned at a fixed distance from a forward face of the dovetail along a centerline of a dovetail axis. An independent claim is also included for a turbine blade comprising an airfoil and a blade dovetail.