Abstract: A method of repairing a case for a gas turbine engine includes identifying areas of damage on its internal holding structures in a gas turbine case, and utilizing cold metal transfer to deposit weld material to the internal holding structures.

Abstract: A method for peening a component of a gas turbine engine, or a module of a gas turbine engine, without removing the component from the assembled gas turbine engine or module includes blending the damaged area of the component, determining parameters for peening the damaged component, and peening the damaged component without removing it from the engine.

Abstract: A shot peening operation is performed on a localized area. A conformable material contains the shot peening elements. The conformable material can conform to the multiple complex shapes of the component to be shot peened.

Abstract: A method of repairing a turbine engine component, such as an airfoil platform, is provided. The platform includes a surface having a worn or damaged area penetrating the surface, the worn area may result from galling, for example. An electrospark deposition process (ESD) is used to deposit material to the worn or damaged area. The ESD process transfers material from an electrode associated with the ESD machine through a pulsating current that deposits the material onto the worn or damaged area. The material can then be machined to restore the surface to a desired specification. The ESD process is used to repair worn compressor and/or turbine blades and vanes that would otherwise be scrapped.

Abstract: Methods for repairing gas turbine components damaged by corrosion that not only restores the components back to their original dimensions to ensure proper engine operations, but also have the added benefit of mitigating future corrosion attacks thereby extending the useful life of the components.