General Electric Company

Brian Dudley Dorrel

John Matthew Powers

Keith B Alexander

David J Huff

Wilbur R Weems

A method for repairing a turbine blade for a gas turbine engine is provided. The method includes securing the blade into a clamping fixture, obtaining a zero reference from a gauging surface on the clamping fixture, coupling the clamping fixture to a grinding machine, and grinding the blade based on the zero reference.

Apparatus for rebuilding gas turbine engines

An apparatus for aligning a gas turbine engine blade including an airfoil and a dovetail is provided. The apparatus includes at least one locator pin configured to engage a serration formed on the blade dovetail, a locator block supporting said locator pin where said locator block comprises at least one groove sized to receive said locator pin therein, and a slide block assembly for engaging a dovetail surface opposite the serration where said slide block assembly is configured to position the blade dovetail against said locator pin. The apparatus also includes 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 platform upper surface defining a slotted opening extending through said bottom surface, said opening configured to receive the blade airfoil.

Apparatus for rebuilding gas turbine engine blades

A fixture for holding a gas turbine engine blade having an airfoil extending outward from a shank and a dovetail extending inward from the shank for attaching the blade to a disk of the engine. The dovetail includes at least one pair of protrusions extending fore and aft along opposite sides of the blade. Each of the protrusions including a pressure face generally facing the airfoil of the blade for engaging the disk to retain the blade in the disk during operation of the engine. The fixture includes a support for receiving the dovetail and a clamp mounted adjacent the support for movement between a clamped position in which the clamp engages the dovetail to hold the dovetail against the support and a released position in which the clamp disengages the dovetail to permit removal of the blade from the fixture.

Fixture for holding a gas turbine engine blade

A mounting apparatus including a first element is slideably connected to a second element by a joint. The joint includes first and second spaced apart walls on the first element and a third wall on the second element that is slideably disposed between the first and second walls. A biasing feature, such as a spring, is disposed between the first and second elements. Preferably, a restraining feature is used for restraining slidable movement to one degree of freedom of motion between the elements. A bore is disposed in one wall of one of the elements and is generally alignable with a conical cavity in another wall of another of the elements and a rod disposed through the bore. The rod has a conical tip with a tip conical surface for engaging a cavity conical surface of the conical cavity. The conical tip is smaller than the conical cavity in diameter so as to being able to effect the biasing movement by axial movement of the rod in the bore. The restraining feature further may include a pivoting feature for restraining slidable movement between the elements to pivoting about a pivot point of the pivoting feature and in another embodiment a linear restraining feature may be used for restraining slidable movement between the elements to linear movement. The holder may be used to hold an electrode.

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Batesville, IN, United States of America

Brian Dudley Dorrel