General Electric Company

Marek M Steplewski

Bhupendra Kumar Gupta

Thomas Joseph Kelly

David Edwin Budinger

Wayne Ray Grady

Glenn Herbert Nichols

Edward John Emilianowicz

Robert Ingram Ackerman

Matthew Nicklus Miller

Cary Michael Kinder

Luciana De Fatima Lira Dederichs

Ian Craig Linscott

Glenn H Nichols

A turbine nozzle may be repaired by severing the inner band from the vanes and outer band, which may then be discarded. A replacement nozzle is cast to include replacement vanes extending between a replacement outer band and an inner web, with the replacement outer band and vanes conforming with the original outer band and vanes. The new web is configured differently than the old inner band and includes a tie bar. The inner band is machined to form vane seats. The web is machined to form plinths atop the tie bar at each of the replacement vanes. The plinths and tie bar are assembled through the vane seats and bonded to the machined inner band to collectively form the repaired turbine nozzle.

Turbine nozzle biform repair

A gas turbine engine plenum cover is repaired using a prefabricated repair cover SPAD. The SPAD repair cover has a spoolie boss that is aligned and attached to the body of the repair plenum cover prior to attachment to a plenum casting to form a repaired plenum chamber. Preattachment of the spoolie boss by brazing methods, as well as optional machining of a borescope hole prior to or after attachment of the repair cover, greatly simplifies the repair process, thereby reducing the time required and cost of repair.

Repair method for plenum cover in a gas turbine engine

A process for refurbishing a worn surface of a shroud support component of a turbomachine, as well as a shroud support component refurbished with the process. The process generally entails removing a surface region of the worn surface so as to define a repair surface on the component. A braze tape formed from a slurry to comprise a braze material and a wear-resistant alloy is then applied to the repair surface, followed by a heat treatment to cause the braze tape to diffusion bond to the repair surface so as to define a built-up surface. The built-up surface is then machined to define a wear-resistant coating on the component.

Method for refurbishing surfaces subjected to high compression contact

A method facilitates replacing a portion of a gas turbine engine turbine support. The turbine support includes a body including a forward leg, an aft leg, and a mounting flange that each extend radially outwardly from the body. The forward leg is axially upstream from the aft leg and the mounting flange. The mounting flange is substantially axially aligned with respect to the aft leg. The method comprises cutting through at least one of the body, the aft leg, and the mounting flange, removing the forward leg and at least a portion of the body that is upstream from the cut from the engine, and coupling a replacement spad to the portion of the turbine support that is downstream from the cut.

Methods for replacing portions of turbine shroud supports

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Mission, TX, United States of America

Marek M Steplewski