Abstract: A modification process and modified article are disclosed. The modification process includes locating an area in an article, removing the area by machining to form a machined region, inserting a modification material into the machined region, securing the modification material to the article, machining the modification material flush with a geometry of the article, and applying a coating over at least a portion of the article. Another modification process includes locating an area under a suction side leading edge tip shroud fillet of an airfoil, removing the area by machining to form a hole, inserting a modification material having improved material properties as compared to an original base material into the hole, securing the modification material in place, machining the modification material and the airfoil to form a new fillet contour, and applying a coating over at least a portion of the airfoil. Also disclosed is the modified article.

Abstract: A method is provided for modifying an airfoil shroud located at a tip of a blade of an 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 including a portion of a seal rail extending circumferentially from a radially outer surface of the airfoil shroud, and a fillet extending from the radially outer surface and positioned directly adjacent to the seal rail. The method further includes forming a relief cut in the seal rail and fillet without performing a weld process on the airfoil shroud to remove the reference location, and installing the airfoil shroud in a turbomachine directly following forming the relief cut, wherein modifying the airfoil shroud is complete following forming the relief cut.

Abstract: A method and system for determining creep capability of turbine components is provided. A plurality of turbine components are manufactured from a material having known creep characteristics. Each of the plurality of turbine components is subjected to at least one of tensile stress, centrifugal stress and thermal stress, until a measurable amount of creep is acquired. The turbine components so tested are compared against known creep characteristics for the material used in the components. Components exhibiting an amount of creep greater than a predefined amount of creep will be separated from the plurality of turbine components and not placed into service.

Abstract: A modification process and modified article are disclosed. The modification process includes locating an area in an article, removing the area by machining to form a machined region, inserting a modification material into the machined region, securing the modification material to the article, machining the modification material flush with a geometry of the article, and applying a coating over at least a portion of the article. Another modification process includes locating an area under a suction side leading edge tip shroud fillet of an airfoil, removing the area by machining to form a hole, inserting a modification material having improved material properties as compared to an original base material into the hole, securing the modification material in place, machining the modification material and the airfoil to form a new fillet contour, and applying a coating over at least a portion of the airfoil. Also disclosed is the modified article.

Abstract: A method and system for determining creep capability of turbine components is provided. A plurality of turbine components are manufactured from a material having known creep characteristics. Each of the plurality of turbine components is subjected to at least one of tensile stress, centrifugal stress and thermal stress, until a measurable amount of creep is acquired. The turbine components so tested are compared against known creep characteristics for the material used in the components. Components exhibiting an amount of creep greater than a predefined amount of creep will be separated from the plurality of turbine components and not placed into service.

Abstract: Support members for separable cooperating parts of a split mould are in pin-and-slot connection with one of the support members having spaced parallel projections or rollers running in a common slot in the other support member. The slot is of curvate form to determine the path of relative movement of the support members and piston and cylinder means is provided to effect this movement.