Abstract: A method of repairing a superalloy component includes subjecting the superalloy component, including a repair area, to a phase agglomeration cycle, which includes stepped heating and controlled cooling of the component. The method further includes applying weld material to the repair area to create a weld surface; and covering the weld surface with brazing material. The component is then subjected to a braze cycle to produce a brazed component. The brazed component is cleaned, and the cleaned component is subjected to a restorative heat treatment to restore the microcrystalline structure and mechanical properties of the component.

Abstract: A method of brazing a treatment area of a load-bearing component includes applying a repair material over the treatment area of the component and positioning an induction brazing coil having a geometry corresponding to the treatment area over the repair material and the treatment area. The method further includes heating the repair material utilizing the induction brazing coil to a temperature sufficient to cause at least partial melting of the repair material, thereby effecting a brazed joint between the treatment area and the repair material.

Abstract: A method for treating a turbine diaphragm and a treated turbine diaphragm are provided. The method includes the step of removing a portion of the turbine diaphragm. The method further includes the step of forming a coupon having a geometry that corresponds to the portion of the turbine diaphragm removed. The method further includes joining the coupon to the turbine diaphragm. At least a portion of the coupon is a pre-sintered preform. The treated turbine diaphragm includes a substrate and a coupon joined to the substrate, wherein at least a portion of the coupon is a pre-sintered preform.

Abstract: A method of repairing a superalloy component includes subjecting the superalloy component, including a repair area, to a phase agglomeration cycle, which includes stepped heating and controlled cooling of the component. The method further includes applying weld material to the repair area to create a weld surface; and covering the weld surface with brazing material. The component is then subjected to a braze cycle to produce a brazed component. The brazed component is cleaned, and the cleaned component is subjected to a restorative heat treatment to restore the microcrystalline structure and mechanical properties of the component.

Abstract: A method of welding a superalloy component includes the following sequential steps. A welding step for welding a cavity using a filler metal in an inert atmosphere, where the cavity is located in the component. A covering step for covering the filler metal and a portion of the component with a weld filler layer in the inert atmosphere. The weld filler layer has a greater ductility than material comprising the component and/or material comprising the filler metal. A second covering step for covering the weld filler layer with a braze material, and subsequently performing a brazing operation. A heat treating step heat treats the component.

Abstract: A fixture and method for resistance welding of at least one pad to at least one surface of an article is disclosed. The method includes mounting the article in the fixture, placing the at least one pad on the at least one surface of the article, positioning a first electrode of a resistance welding apparatus to the at least one pad and a second electrode of the resistance welding apparatus to the article, and applying pressure and electric current across the at least one pad and the at least one surface. The fixture includes a first, second and third support element, which, respectively, include a first, second and third contact surface being adapted and disposed to support a first, second and third portion of the article. The first, second and third contact surfaces are each inelastic and electrically insulating. The fixture is arranged and disposed to non-rotatably cradle the article.

Abstract: A method to repair an opening in a metallic device including: mount the device on a positioner; while the device is mounted on the positioner, sense and record positions of a surface of an opening in the device using a probe operated by a manipulator; based on the recorded positions determine a centerline and diameter of the opening; orient a digital model of the opening with respect to the opening of the device based on the centerline and diameter of the opening, and apply an weld or cladding to the opening by a welding torch maneuvered automatically by the manipulator while the device is mounted to the positioner and based on the oriented digital model of the opening.

Abstract: The present application provides a method of repairing a turbine blade. The method may include the steps of removing an existing tip cap from the turbine blade in whole or in part, machining the turbine blade to form a machined groove, positioning an insert in the machined groove, welding the insert to the turbine blade, and brazing the turbine blade.

Abstract: A method of welding a superalloy component includes the following sequential steps. A welding step for welding a cavity using a filler metal in an inert atmosphere, where the cavity is located in the component. A covering step for covering the filler metal and a portion of the component with a weld filler layer in the inert atmosphere. The weld filler layer has a greater ductility than material comprising the component and/or material comprising the filler metal. A second covering step for covering the weld filler layer with a braze material, and subsequently performing a brazing operation. A heat treating step heat treats the component.

Abstract: A method for treating a turbine diaphragm and a treated turbine diaphragm are provided. The method includes the step of removing a portion of the turbine diaphragm. The method further includes the step of forming a coupon having a geometry that corresponds to the portion of the turbine diaphragm removed. The method further includes joining the coupon to the turbine diaphragm. At least a portion of the coupon is a pre-sintered preform. The treated turbine diaphragm includes a substrate and a coupon joined to the substrate, wherein at least a portion of the coupon is a pre-sintered preform.

Abstract: A method of brazing a treatment area of a load-bearing component includes applying a repair material over the treatment area of the component and positioning an induction brazing coil having a geometry corresponding to the treatment area over the repair material and the treatment area. The method further includes heating the repair material utilizing the induction brazing coil to a temperature sufficient to cause at least partial melting of the repair material, thereby effecting a brazed joint between the treatment area and the repair material.

Abstract: A method to repair an opening in a metallic device including: mount the device on a positioner; while the device is mounted on the positioner, sense and record positions of a surface of an opening in the device using a probe operated by a manipulator; based on the recorded positions determine a centerline and diameter of the opening; orient a digital model of the opening with respect to the opening of the device based on the centerline and diameter of the opening, and apply an weld or cladding to the opening by a welding torch maneuvered automatically by the manipulator while the device is mounted to the positioner and based on the oriented digital model of the opening.

Abstract: A braze system is disclosed, including a first surface, a second surface, a gap disposed between the first surface and the second surface, a capillary matrix disposed in the gap, and a braze material disposed in contact with the capillary matrix. The capillary matrix includes a matrix structure forming a plurality of capillaries. A brazed article is disclosed in which the braze material is disposed within the plurality of capillaries and contacts the first surface and the second surface. The braze material, the capillary matrix, the first surface, the second surface, and the gap form a brazed portion including less than about 20% voiding. A method for forming a brazed article includes disposing the capillary matrix into the gap, and infusing a braze material into the plurality of capillaries and in contact with the first surface and the second surface, forming the brazed portion.

Abstract: A method of brazing includes placing a non-foam matrix in a gap and applying a molten braze material to the gap such that the molten braze material flows into the gap and through the non-foam matrix by capillary action to fill the gap and cools to form a solid braze in the gap. A brazed article includes at least one component defining a gap, a non-foam matrix in the gap and a solid braze interspersed through the non-foam matrix. The non-foam matrix and the solid braze fill the gap.

Abstract: The present application provides a method of repairing a turbine blade. The method may include the steps of removing an existing tip cap from the turbine blade in whole or in part, machining the turbine blade to form a machined groove, positioning an insert in the machined groove, welding the insert to the turbine blade, and brazing the turbine blade.

Abstract: A fixture and method for resistance welding of at least one pad to at least one surface of an article is disclosed. The method includes mounting the article in the fixture, placing the at least one pad on the at least one surface of the article, positioning a first electrode of a resistance welding apparatus to the at least one pad and a second electrode of the resistance welding apparatus to the article, and applying pressure and electric current across the at least one pad and the at least one surface. The fixture includes a first, second and third support element, which, respectively, include a first, second and third contact surface being adapted and disposed to support a first, second and third portion of the article. The first, second and third contact surfaces are each inelastic and electrically insulating. The fixture is arranged and disposed to non-rotatably cradle the article.

Abstract: The present application provides a hole reducing tool. The hole reducing tool includes a punch with a conical tip and a pilot and a slide hammer assembly attached to the punch.

Abstract: The present application provides a hole reducing tool. The hole reducing tool includes a punch with a conical tip and a pilot and a slide hammer assembly attached to the punch.

Abstract: According to one aspect of the invention, a method for servicing a combustor cap assembly of a turbine includes determining a defect is present in a center ring of the cap assembly, the center ring being disposed within a plurality of vanes, removing the center ring from the cap assembly. The method also includes placing a replacement center ring in the cap assembly, wherein dimensions of the replacement center ring are substantially the same as the center ring that has been removed and brazing the replacement center ring to the plurality of vanes.

Abstract: A method of fabricating a component and a fabricated component are disclosed. The method includes depositing a material to a component and manipulating the material to form a boundary region and a filler region for desired properties. The component includes the boundary region and the filler region, thereby having the desired properties.