Appeal No. 97-2596
Application No. 08/319,345
APPENDIX
1. A dovetail assembly component of a gas turbine engine for
mounting blades around a rotor disk periphery, said dovetail
assembly component comprising:
a metallic body having at least a portion of said body
subject to a stress field due to forces generated by the engine's
operation,
at least one stress riser located in said portion that
causes stress concentration in said stress field when the rotor
is rotating,
at least one region of the component around said stress
riser having deep compressive residual stresses imparted by laser
shock peening,
said stress riser is a transition portion of the component
between an area of minimum width, in cross section, and a
pressure face of the component wherein said pressure face is a
contact surface between a complementary dovetail blade slot and
dovetail blade root formed between adjacent disk posts
circumferentially disposed around a centerline axis of the disk,
and
wherein said region extends inward from a laser shocked
surface of the component along said transition portion of the
component.
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Last modified: November 3, 2007