Abstract: A method for selective aluminide diffusion coating removal. The method includes diffusing aluminum into a substrate surface of a component to form a diffusion coating. The diffusion coating includes an aluminum-infused additive layer and an interdiffusion zone. The diffusion coating is solution heat treated at a temperature and for a time sufficient to dissolve at least a portion of the interdiffusion zone. Thereafter the aluminum-infused additive layer is selectively removed. An aluminide diffusion coated turbine component is also disclosed.

Abstract: A method for selective aluminide diffusion coating removal. The method includes diffusing aluminum into a substrate surface of a component to form a diffusion coating. The diffusion coating includes an aluminum-infused additive layer and an interdiffusion zone. The diffusion coating is solution heat treated at a temperature and for a time sufficient to dissolve at least a portion of the interdiffusion zone. Thereafter the aluminum-infused additive layer is selectively removed. An aluminide diffusion coated turbine component is also disclosed.

Abstract: An interactive device includes a housing and a finger ladder held within the housing and having a number of parallel rungs. Each rung includes at least one sensor. A display system, which may include panels attached to either side of the ladder, produce sounds and/or images when the rungs of the ladder are contacted sequentially. Alternately, the display system may be integral with the finger ladder. The sounds and/or images may produce a song or a familiar sequence, such as the alphabet. The sequential activation of the sensors results in the development of both gross and fine motor skills, for example, in children, persons with developmental differences, and persons needing physical or occupational therapy.

Abstract: A process for modifying or repairing a metallic component, such as a combustion cap effusion plate for a gas turbine, is disclosed. The method includes generating a notch or groove in the metallic component and depositing a filler material in the notch or groove. A pulsed laser is applied to the filler material. The pulsed laser has a power, frequency, and pulse width sufficient to apply heat to the metallic component and to the filler material to make at least a portion of the metallic component and the filler material melt in order to weld the filler material to the metallic component and repair or modify the metallic component. Various operating parameters of the pulsed laser can be configured to reduce undesirable heating affects.

Abstract: A process for modifying or repairing a metallic component, such as a combustion cap effusion plate for a gas turbine, is disclosed. The method includes generating a notch or groove in the metallic component and depositing a filler material in the notch or groove. A pulsed laser is applied to the filler material. The pulsed laser has a power, frequency, and pulse width sufficient to apply heat to the metallic component and to the filler material to make at least a portion of the metallic component and the filler material melt in order to weld the filler material to the metallic component and repair or modify the metallic component. Various operating parameters of the pulsed laser can be configured to reduce undesirable heating affects.

Abstract: A process and braze paste suitable for filling and closing voids in relatively thin wall sections of high temperature components, such as an impingement plate of a combustor of a gas turbine engine. The process entails applying at least a first braze paste to the crack to form a braze paste patch comprising powders of first and second alloys and an organic binder. The first alloy has a higher melting temperature than the second alloy, and the powders of the first and second alloys are present in the braze paste patch at a weight ratio of about 30:70 to about 70:30 weight percent. The braze paste patch is then heated to burn off the binder and melt at least the powder of the second alloy to form a brazement within the crack that contains particles of the first alloy dispersed in a matrix formed by the second alloy.

Abstract: A method of repairing a turbine component with one or more craze cracks therein includes the steps of: (a) routing out the one or more cracks to form one or more routed areas; (b) applying a superalloy powder/paste in the one or more routed areas; (c) heat treating the component in place to form one or more repaired areas; and (d) blending the repaired area with adjacent areas of the component.

Abstract: A method of repairing a turbine component seal land includes: (a) removing material along substantially the entire seal land to provide a preform-receiving face; (b) locating a repair preform along and engaged with said preform-receiving face; (c) brazing the preform to said preform-receiving face; (d) and finish machining an exposed face of the preform to specifications, thereby providing a repaired seal land.

Abstract: A fuel nozzle assembly for a gas turbine includes a plurality of circumferentially spaced vanes with holes for flowing fuel from plenums within the vanes through holes in the vane walls for premixing with air. To tune the nozzle assembly, the holes are resized by reforming the existing holes to a predetermined hole size, securing plugs into the holes, and forming holes through at least certain of the plugs to diameters less than the diameter of the existing holes.

Abstract: The cap assembly of a turbine combustor includes a plurality of burner tubes sealed against fuel nozzles extending in the tubes. These piston seals are coated with a high velocity oxygen fuel coating to extend their service life. The outer cap body assembly includes concentric seal rings each with cantilevered convex fingers circumferentially offset from one another to seal between the cap assembly casing and the inner liner. The cap assembly casing is provided with a plurality of holes at predetermined locations about the casing to minimize or eliminate response to combustion dynamics.

Abstract: A fuel nozzle assembly for a gas turbine includes a plurality of circumferentially spaced vanes with holes for flowing fuel from plenums within the vanes through holes in the vane walls for premixing with air. To tune the nozzle assembly, the holes are resized by reforming the existing holes to a predetermined hole size, securing plugs into the holes, and forming holes through at least certain of the plugs to diameters less than the diameter of the existing holes.