BLADE DOVETAIL BACKCUT FOR STRESS REDUCTION IN THE BLADE

The present application thus provides a method for reducing stress on at least one of a turbine disk 55 and a turbine blade 100. The method may include the steps of (a) determining a starting line 150 for a dovetail backcut 130 relative to a datum line (M), (b) determining a cut angle 170 for the do...

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Bibliographische Detailangaben
Hauptverfasser:	ZEMITIS, William Scott, GUNNING, Sean Patrick Douglas, NEVILLE, Jason Adam, MERRILL, Mitchell
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The present application thus provides a method for reducing stress on at least one of a turbine disk 55 and a turbine blade 100. The method may include the steps of (a) determining a starting line 150 for a dovetail backcut 130 relative to a datum line (M), (b) determining a cut angle 170 for the dovetail backcut, and (c) removing material from at least one of a blade dovetail 110 or a disk dovetail slot 65 according to the starting line and the cut angle to form the dovetail backcut. The datum line may be positioned about 2.866 inches (about 72.796 millimeters) from a forward face 145 of the blade dovetail and wherein step (a) is practiced such that for the pressure side of the dovetail, the starting line of the dovetail backcut is at least about 2.566 inches (about 65.176 millimeters) in a forward direction from the datum line.