General Electric Company

Daniel Padraic O'Reilly

Thomas Carl Mesing

William Terence Dingwell

Ronald Lance Galley

Henry Ng

A tool for in-situ airfoil contouring is provided. The tool has a pathway for an airfoil edge wherein the edge movement is limited and further wherein the edge is exposed to a grinding structure having a preselected profile shape therein. The tool makes this contouring process available for airfoils without the necessity of removing the airfoils from, for example, an aircraft engine.

In-situ airfoil contouring tool

A gas turbine engine compressor including a stator assembly and a method of assembling the same are provided. The method includes providing a compressor casing including at least two stator vane casing rails extending from the casing, coupling a rail liner within each respective casing rail, and coupling a stator vane assembly including two dovetails, and at least two stator vanes coupled together within the casing rails within the liner such that a first dovetail is received within a first casing rail and a first rail liner, and a second dovetail is received within a second casing rail and a second rail liner.

Methods and apparatus for assembling gas turbine engines

A method enables a variable vane assembly for a gas turbine engine including a casing to be assembled. The variable vane assembly includes a seal assembly and at least one variable vane that includes a platform and a trunnion, wherein the platform extends outwardly from the trunnion. The method comprises coupling a seal assembly journal bushing to the variable vane such that the journal bushing is against the trunnion and between the trunnion and the engine casing, and wherein the journal bushing has a substantially constant diameter extending between a first and a second end of the journal bushing, and positioning a substantially flat first washer on the variable vane ledge to prevent contact between the variable vane assembly and the engine casing.

Methods and apparatus for sealing gas turbine engine variable vane assemblies

A variable stator vane assembly for a gas turbine engine including a bushing that facilitates extending a useful life of the stator vane assembly is described. The stator vane assembly includes a spacer and a vane secured to an engine casing. The bushing is between the spacer and vane, and prevents the spacer and the vane from contacting the engine casing. The bushing is fabricated from several materials formed in a matrix, such that at least a portion of the bushing is electrically conductive. During engine operation, a conductive path is realized through the bushing that discharges electrical charges.

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Hamilton, OH, United States of America

Daniel Padraic O'Reilly