A method for remotely stopping a crack in a component of a gas turbine engine is provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface on the component; supplying a new material to the area to fill the defect; and heating the new material to fuse the new material to the component within the defect.

A non-weldable workpiece may be affixed to a weldable workpiece by friction stirring the weldable workpiece to plasticize and extrude at least a portion thereof into a recess in the non-weldable workpiece. The weldable workpiece may then be welded to a body of a downhole tool to enable the welding of a non-weldable workpiece onto a body to increase the wear-resistance of the body.

A hybrid article is disclosed including a coating circumscribing the lateral surface of a hollow core having a core material and a channel disposed within the lateral surface. The coating includes about 35% to about 95% of a first metallic material, and about 5% to about 65% of a second metallic material with a lower melting point than the first metallic material. A method for forming the hybrid article is disclosed including disposing the hollow core in a die, forming a gap between the lateral surface and the die, introducing a slurry having the metallic materials into the gap, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture, and brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or a combination thereof.

A structure of assembly grasp for palladium-alloy tubes and the manufacturing method thereof are described. The structure of assembly grasp for palladium-alloy tubes includes a grasp with a plurality of holes, a plurality of palladium-alloy tubes inserted into the plurality of holes, and an intermetallic compound layer between the palladium-alloy tubes and the inner sidewalls of the plurality of holes.

The present disclosure is directed to a system and method for preventing damage to one or more components of the gas turbine engine during a repair procedure. The method includes locating one or more gaps of one or more components of the gas turbine engine in the vicinity of the defect. Further, the method includes filling the one or more gaps with a filler material so as to prevent arcing over the gaps during repair. Thus, the method also includes applying an electrical discharge to the defect.

A tool for forming a shaped product has a support body that is fabricated from a first material, such as for instance cast iron. The first material defines a first portion of a forming surface of the tool and has a feature supported thereon. The feature has a layer of a second material that is supported on the first material of the support body, a layer of a third material that is supported on the layer of the second material and a layer of a fourth material that is supported on the layer of the third material. The layer of the fourth material, such as for instance a tool steel alloy, defines a second portion of the forming surface of the tool. During use the first portion of the forming surface and the second portion of the forming surface cooperate to form a desired shape of the shaped product.

Irradiation with a laser beam is started at a welding start position of two members that are stacked together, and the output of the laser beam is set so that spatter is not generated. After the start of the irradiation, the output of the laser beam is gradually increased so that a penetration depth from an irradiated edge to a deeper location between abutting surfaces of the two members falls within a predetermined penetration depth range while the laser beam is not moved. After the output of the laser beam is gradually increased, the laser beam is moved toward a welding end position so that the penetration depth is maintained within the penetration depth range.

Provided are a machining device and a machining method in which machining of higher precision can be performed with a simple configuration. The machining device has an irradiation head (16) and a controller; and the irradiation head (16) can be divided into a collimate optical system, a laser revolving unit (35), and a light collection optical system (37). The laser revolving unit (35) has a first prism (51), a second prism (52), a first rotation mechanism (53), and a second rotation mechanism (54). The controller controls the rotational speeds and the difference in phase angles of the first prism (51) and the second prism (52), on the basis of at least the relationship between a heat affected layer of a member to be machined and the revolving speed of the laser.

A method for brazing is provided, in which an amorphous or partially amorphous brazing foil, having a composition with a metalloid content of 10 to 30 at. %, is arranged at a joining point of two or more parts. The brazing foil is in the form of a wound ring-shaped strip which has a short-circuited current path between at least two layers lying one on top of the other. The brazing foil inductively heated, melted and a brazed connection of the parts is produced.

A braze composition, brazing process, and brazed article are disclosed. The braze composition includes a MCrAlY alloy at a concentration, by weight, of between 50% and 70%, where M is selected from the group consisting of nickel, cobalt, iron, alloys thereof, and combinations thereof, and a nickel-based alloy at a concentration, by weight, of between 30% and 50%. The brazing process includes forming a braze paste, brazing the braze paste to a portion of a component, and shaping the braze paste to form a brazed article. The brazed article includes a component and a braze composition brazed to the component, the braze composition including a MCrAlY alloy at a concentration, by weight, of between 50% and 70%, where M is selected from the group consisting of nickel, cobalt, iron, alloys thereof, and combinations thereof, and a nickel-based alloy at a concentration, by weight, of between 30% and 50%.