Abstract: A process for repairing cracks in a workpiece, such as a turbine engine component, comprises the steps of: providing a workpiece having a crack to be repaired; applying a nickel or cobalt base alloy material to a root of the crack in an amount sufficient to fill a portion of the crack; subjecting the workpiece with the nickel or cobalt base alloy material to a first heat treatment at a temperature in the range of from about 1950 to 2300° F. for a time period in the range of from about 5.0 to 30 minutes; applying a weld material to the crack; and subjecting the workpiece with the weld material to a second heat treatment.

Abstract: Methods for inspecting gas turbine component parts for possible distress after hydrogen fluoride cleaning are disclosed. The methods selectively remove a small amount of material for IGA inspection and restore the material using the same procedures as when the parts were manufactured.

Abstract: Methods for inspecting gas turbine component parts for possible distress after hydrogen fluoride cleaning are disclosed. The methods selectively remove a small amount of material for IGA inspection and restore the material using the same procedures as when the parts were manufactured.

Abstract: A process for repairing cracks in a workpiece, such as a turbine engine component, comprises the steps of: providing a workpiece having a crack to be repaired; applying a nickel or cobalt base alloy material to a root of the crack in an amount sufficient to fill a portion of the crack; subjecting the workpiece with the nickel or cobalt base alloy material to a first heat treatment at a temperature in the range of from about 1950 to 2300° F. for a time period in the range of from about 5.0 to 30 minutes; applying a weld material to the crack; and subjecting the workpiece with the weld material to a second heat treatment.

Abstract: Novel materials and methods for repairing/reclassifying superalloy components are described herein. These materials are non-traditional blends of materials having a much higher base material content than traditional repair/reclassification materials. In embodiments used to repair/reclassify nickel-based components, these materials may comprise about 5-18.9 weight percent of a low melting point alloy and about 81.1-95 weight percent of a base material. In embodiments used to repair/reclassify cobalt-based components, these materials may comprise about 15-30 weight percent of a low melting point alloy and about 70-85 weight percent of a base material. These materials can be used to repair surface defects and/or build up worn or eroded areas of a component to meet precise dimensional and metallurgical requirements. These materials create robust repaired components having a dense, isothermally solidified structure having minimal borides and a high re-melt temperature.