BLADE/DISK DOVETAIL BACKCUT FOR BLADE DISK STRESS REDUCTION

摘要

PROBLEM TO BE SOLVED: To provide a blade disk capable of reducing stress on at least one of a turbine disk and a turbine blade.;SOLUTION: A method comprises: determining a starting line 150 for a dovetail backcut 130 relative to a datum line; determining a cut angle for the dovetail backcut 130; and removing material from at least one of the blade dovetail 110 and the disk dovetail slot according to the starting line 150 and the cut angle to form the dovetail backcut 130. The datum line may be positioned about 2.866 inches from a forward face of the blade dovetail. The determination of the starting line 150 for the dovetail backcut 130 relative to the datum line is practiced such that, for the positive pressure side of the dovetail, the starting line 150 of the dovetail backcut 130 is at least about 2.566 inches in a forward direction from the datum line.;SELECTED DRAWING: Figure 5;COPYRIGHT: (C)2017,JPO&INPIT