Abstract: A method for making a turbine airfoil includes providing a mold core and an outer shell which cooperatively define a cavity in the shape of a hollow airfoil having an outer wall, a root, and a tip. A tip portion of the core extends completely through the portion of the cavity defining the tip of the airfoil. The core is restrained to prevent movement between the core and outer shell. Molten metal is introduced into the cavity and solidified to form an airfoil having at least one outer wall which defines an open tip and a hollow interior. A metallic tip cap is formed on the outer wall which substantially closes off the open tip. The tip cap may be formed by packing the airfoil with metallic powder; and laser sintering the exposed powder so as to form a tip cap which is metallurgically bonded to the outer wall.

Abstract: A method and system for monitoring laser shock peening of a work piece. A line spectrum is obtained from radiation emitted by a plasma produced by a laser shock peening process. The shape of the line spectrum about its emission peak is compared to a defined line shape to verify proper operation of the laser shock peening process. The line shape may be a Lorentzian line shape corresponding to a desired line shape. The line shape may a Gaussian line shape corresponding to an undesired line shape. The system can also detect the failure mode that occurs when the opaque layer is broken through by detecting the plasma spectral component produced by the work piece material, along with the plasma produced by the opaque layer.

Abstract: Methods, apparatuses, devices, and/or systems for laser net shape manufacturing are described may make use of a nozzle that includes a main body with a thermal channel, a conducting channel and a gas distribution head. The thermal channel is at least partially within the main body and includes an aperture for passing thermal energy therethrough. The conducting channel includes a conducting outlet aperture that is a located adjacent to the thermal outlet aperture, and powder material can be passed through the conducting outlet aperture. The gas distribution head is capable of distributing shielding gas in a distribution path surrounding the conducting outlet aperture.

Abstract: A system and method for monitoring a laser shock peening process includes a sensor connected to a controller. The controller includes an input and a processor. The input is connected to the sensor to receive a signal indicative of a laser shock event at a workpiece. The processor is connected to the input and is configured to determine a time-of-flight of residual energy associated with the laser shock event from the workpiece to the sensor and determine peen quality from the time-of-flight of the residual energy.

Abstract: A turbine component formed from a niobium silicide-based composition is described. The component can be compositionally-graded through at least a portion of its structure. A turbine blade formed from a composition which includes a niobium silicide alloy is also described. The blade includes an airfoil; an airfoil tip region; a platform on which the airfoil is mounted; and a dovetail root attached to an underside of the platform. The niobium silicide alloy in at least one portion of the turbine blade is compositionally different from the niobium silicide alloy in another portion of the blade. Processes for fabricating a niobium silicide-based turbine article are also described, using laser cladding techniques. Repair methods are also set forth in the application.

Abstract: A method and system for monitoring laser shock peening of a work piece. A line spectrum is obtained from radiation emitted by a plasma produced by a laser shock peening process. The shape of the line spectrum about its emission peak is compared to a defined line shape to verify proper operation of the laser shock peening process. The line shape may be a Lorentzian line shape corresponding to a desired line shape. The line shape may a Gaussian line shape corresponding to an undesired line shape. The system can also detect the failure mode that occurs when the opaque layer is broken through by detecting the plasma spectral component produced by the work piece material, along with the plasma produced by the opaque layer.