Abstract: A method of joining a first component and a second component includes providing the first component including a first surface; providing the second component including a second surface; creating a braze joint between the first and second surfaces using a sinker electrical discharge machining (EDM) device, where the first component is used as an electrode of the sinker EDM device and a voltage is generated between the first and second components such that the braze joint is created by spark erosion of at least one of the first component and the second component; and coupling the first and second components securely together along the braze joint.

Abstract: A system for manufacturing an airfoil includes an outer surface of the airfoil, a cavity inside the airfoil, and a collimator outside of the airfoil. The system further includes a fluid column flowing from the collimator toward the outer surface of the airfoil, and a laser beam inside the fluid column creates a confined laser beam directed at the outer surface of the airfoil. A method for manufacturing an airfoil includes confining a laser beam inside a fluid column to create a confined laser beam, directing the confined laser beam at an outer surface of the airfoil, and creating a passage through the outer surface of the airfoil with the confined laser beam.

Abstract: A method for inspecting a turbine nozzle segment includes positioning the turbine nozzle segment on a base of a tool, with the outer forward face and the inner forward face of the turbine nozzle segment contacting a surface of the base. The outer wall is positioned between a first pedestal outer stand and a second pedestal outer stand of the tool, and the inner wall is positioned between a first pedestal inner stand and a second pedestal inner stand of the tool. At least one of a position, a depth and a width of a seal slot formed in a side edge of the outer wall and/or the inner wall is measured. At least one axial dimension of the turbine nozzle segment and at least one radial dimension of the turbine nozzle segment are measured.

Abstract: The trailing edge of a turbine bucket is cut back from a root portion of the bucket to a location 50-75% of the span of the bucket. The cutback portion is tapered, forming an obtuse angle between it and the remaining original portion of the trailing edge outwardly of the cutback portion. A new conical section is thus created of a slightly larger conical and, hence, transverse configuration. The crack is removed upon removal of the material forming the cutback. With the edges of the recreated conical section surrounded, the cutback portion assumes a scalloped configuration with the exit openings of the cooling holes as seen from opposite sides of the bucket.

Abstract: The trailing edge of a turbine bucket is cut back from a root portion of the bucket to a location 50-75% of the span of the bucket. The cutback portion is tapered, forming an obtuse angle between it and the remaining original portion of the trailing edge outwardly of the cutback portion. A new conical section is thus created of a slightly larger conical and, hence, transverse configuration. The crack is removed upon removal of the material forming the cutback. With the edges of the recreated conical section surrounded, the cutback portion assumes a scalloped configuration with the exit openings of the cooling holes as seen from opposite sides of the bucket.