General Electric Company

Gregory Matthew Ford

Timothy Lee Siebert

David Edwin Budinger

Joshua L Miller

Glenn Herbert Nichols

Michael Philip Hagle

Jeffrey J Reverman

Paul D Dasilva

Paul A Dasilva

Eric Keith

Dana Leigh Ferguson

Jeffrey John Reverman

A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or welding. The first vane assembly member includes the outer band, the airfoil, an inner flange, and a first segment of the inner band with a first edge, spaced from the flange and extending between and through inner band circumferential edge portions. The second vane assembly member includes a second segment of the inner band including a second edge of shape and size matched with the first edge and extending through the inner band circumferential edge portions.

Method for repairing a turbine engine vane assembly and repaired assembly

Methods and apparatus of fabricating a gas turbine engine component are provided. The method includes selecting a surface of a component to apply a wear-resistant material, applying a formed wear pad fabricated from a wear-resistant alloy and a braze material, and vacuum brazing the component and applied wear pad wherein the wear-resistant alloy is bonded to the component surface using the braze material.

Methods and apparatus for fabricating gas turbine engines

A method is provided for making a repaired turbine engine stationary vane assembly including at least one airfoil bonded between spaced apart first and second platforms. The method comprises providing a first vane assembly member including at least a portion of the first platform, the airfoil, and a first segment of the second platform bonded with the airfoil. Also provided is a second vane assembly member including a second segment of the second platform with a recess of a shape and size sufficient to receive the first segment of the second platform. The first segment is placed in the recess after which the first and second segments are bonded, for example by brazing or welding. Provided is a more structurally sound repaired turbine engine stationary vane assembly including the first and second vane assembly members bonded together.

Method for making a repaired turbine engine stationary vane assembly and repaired assembly

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Cincinnati, OH, United States of America

Gregory Matthew Ford