Abstract: A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.

Abstract: A bucket tip shroud measurement fixture includes a frame extending from a first end to a second end through an intermediate portion having a first surface and an opposing second surface, a first tip shroud fixing member extending from the second surface of the frame at the first end, and a second tip shroud fixing member extending from the second surface of the frame at the second end. The first and second tip shroud fixing members are configured and disposed to retain and establish an orientation of a bucket tip shroud relative the frame. A plurality of reference points are provided on the frame. The plurality of reference points are configured and disposed to receive a coordinate measuring machine (CMM) probe.

Abstract: A component identification system for identifying an industrial machine component in situ is disclosed herein. In an embodiment, a computer system is provided which is configured to implement a method of identifying a component of an industrial machine in situ. In particular, the computer system is configured to decode an image containing a data matrix code, and identify the data matrix code in the image. The computer system is further configured to associate the data matrix code in the image with an identified component in a database.

Abstract: Stripping a metallic bond coat from an article using a wet chemical process. An article removed from service and having a metallic bond coat applied over a surface of its metallic substrate is provided. The metallic bond coat is used to improve the adhesion of a TBC to the article, so grit blasting to first remove any TBC applied over the bond coat and which still remains on the article initially may be required. The bond coated article is then immersed in an acid solution of HCl/H3PO4 at a predetermined temperature for a predetermined amount of time, the HCl/H3PO4 solution reacting with the bond coat applied over the metallic substrate to form a smut on the surface. The article is then removed from the HCl/H3PO4 solution and quickly immersed in a solution of NaOH for a predetermined amount of time to at least partially desmut the surface.

Abstract: Methods for modifying a turbine buckets include removing at least an original outer edge for an entire length of the slash face of the turbine bucket and adding a new material to the slash face to build a new outer edge, wherein the new outer edge extends the entire length of the slash face.

Abstract: A component identification system for identifying an industrial machine component in situ is disclosed herein. In an embodiment, a computer system is provided which is configured to implement a method of identifying a component of an industrial machine in situ. In particular, the computer system is configured to decode an image containing a data matrix code, and identify the data matrix code in the image. The computer system is further configured to associate the data matrix code in the image with an identified component in a database.

Abstract: Various embodiments include approaches for monitoring turbomachine components. In various particular embodiments, a system for monitoring a component within a turbomachine includes: a borescope probe sized to pass through an opening in the turbomachine, the borescope probe for detecting a symbolic data array on the component within the turbomachine; and at least one computing device operably coupled to the borescope probe, the at least one computing device configured to: obtain image data about the symbolic data array from the borescope probe; evaluate the image data to determine whether the image data is compatible with a symbolic data array analysis program; and analyze the image data using the symbolic data array analysis program in response to determining the image data is compatible with the symbolic data array analysis program.

Abstract: Extendable moment weight tools include an extendable base adapted to extend between at least a first distance and a second distance, wherein the extendable base supports a pair of weight scales at the first distance and the second distance, and, a first platform having an upper side provided with a pair of transverse component-supporting posts, and a lower side provided with a pair of transverse foot rails adapted to engage the respective pair of weight scales.

Abstract: A method of locally inspecting and repairing a coated component is provided. The method includes determining an area of interest on the coated component, wherein the area of interest has little to no visible damage. The method also includes removing a coating proximate the area of interest to expose a base material of the coated component. The method further includes inspecting the area of interest for damage to the base material.

Abstract: According to one aspect, a fixture for an airfoil shroud having a first end edge, a second end edge, a leading edge, a trailing edge, a radially outer side and a radially inner side with respect to a rotor axis of a bucket having the airfoil shroud is provided. The fixture includes a base plate, a first member extending from the base plate configured to locate and abut the first end edge, a second member extending from the base plate configured to locate and abut a side of a seal rail, a third member extending from the base plate configured to locate and abut the radially outer side of the airfoil shroud and a template recess formed in the base plate proximate the first end edge to define a geometry of a relief cut in the trailing edge of the airfoil shroud.

Abstract: A turbine engine, bucket and method for modifying an airfoil shroud of turbine bucket is disclosed. A reference location is located in a second end edge of the airfoil shroud proximate a seal rail of the airfoil shroud. A relief cut is formed in the airfoil shroud to remove the reference location. Additionally, another reference location may be located in a first end edge of the airfoil shroud proximate the seal rail. Another relief cut may be formed in the airfoil shroud to remove the other reference location.

Abstract: According to one aspect of the invention, a method is provided for modifying an airfoil shroud located at a tip of an airfoil of a airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge and a trailing edge. The method includes locating a reference location in the first end edge of the airfoil shroud, the reference location being proximate a seal rail extending circumferentially from the substantially horizontal surface and forming a relief cut in the airfoil shroud to remove the reference location, wherein a modifying of the airfoil shroud is complete following forming of the relief cut.

Abstract: A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.

Abstract: A method for preparing to refurbish a turbo-machine component includes virtually refurbishing the turbo-machine component, actually refurbishing the turbo-machine component, and comparing the virtually refurbished turbo-machine component to the actually refurbished turbo-machine component.

Abstract: Disclosed is a method for measuring deformation of a turbine blade, the method including identifying at least one measuring point disposed on the turbine blade, retaining information pertaining to a first position of the at least one measuring point, operating the turbine blade over a period of time, measuring a spatial distance traveled by the at least one measuring point after the operating of the turbine blade over the period of time, the spatial distance being measured relative to the first position of the at least one measuring point; and determining an amount of deformation in the blade based on the measuring of the spatial distance.