Patent ID: 7328496
Filing Date: 2008-02-12
Classification: B23P,B23Q,B24B,F01D,F05D,Y10T

Abstract:
1. An apparatus for aligning a gas turbine engine blade including an airfoil and a dovetail, said apparatus comprising: at least one locator pin configured to engage a serration formed on the blade dovetail; a stationary locator block supporting said locator pin, said locator block comprising at least one groove sized to receive said locator pin therein; a slide block assembly for engaging a dovetail surface opposite the serration, said slide block assembly configured to position the blade dovetail against said locator pin; and a base member comprising a platform comprising an end plate, a bottom surface, and an opposite upper surface for supporting said slide block assembly and said locator block, said slide block assembly is slidably coupled to said platform upper surface, said locator block fixedly coupled to said platform upper surface, said platform upper surface defining a slotted opening extending through said bottom surface, said opening configured to receive the blade airfoil.