General Electric Company

Thomas F Berry

Christopher Charles Glynn

Michael James Weimer

Mark Daniel Gorman

David Edwin Budinger

Peter W Mueller

Matthew J Stewart

Robert E Allen

David John Dietz

Ronald Gustav Rajala

Larry R Samons

Harold L Mullins

A method for restoring thickness to load-bearing components of gas turbine engines, and for repairing a honeycomb structured gas turbine engine component. A surface of the component such as the backing surface of a honeycomb component after honeycomb removal is roughened and cleaned. A selected build-up material is deposited onto the substrate by high velocity oxy-fuel deposition or low pressure plasma spray. The component is heat treated to enhance the bond between the deposited material particles, and between the deposited material and the substrate by diffusion.

Restoration of thickness to load-bearing gas turbine engine components

A process for identificaiton, evaluation and removal of microshrinkage of investment cast superalloy parts and parts produced by the process. Parts free of deleterious microshrinkage capable of longer life at existing stress levels or use at higher alternating stresses are produced by first subjecting the parts to hot isostatic pressing to eliminate nonsurface connected subsurface microshrinkage. Next, in order to expose near-surface microshrinkage microscopically connected to the surface, the parts are immersed in an acid solution for a time sufficient to uniformly remove at least about 0.005 inches of the original as cast surface. The exposed microshrinkage is evaluated for acceptability or removal by standard nondestructive techniques, such as liquid penetration evaluation.

Process for identification evaluation and removal of microshrinkage

A friction welded metallic article such as a fluid directing element for turbomachinery apparatus has a cast airfoil and a wrought base joined by friction welding. One such article having a hollow interior portion is made from a hollow or cored casting and a wrought base member. There is provided a metal airfoil casting having a hollow interior portion and an enlarged foot including an interface portion. Also provided is a wrought metal base portion including an interface portion. Interface surfaces of the interface portions are placed in spaced apart opposed relationship and then the airfoil casting and the wrought base member are friction welded at their interface portions.

Friction welded metallic turbomachinery blade element

Growing community of inventors

Cincinnati, OH, United States of America

Thomas F Berry