Abstract: In a method for processing a turbomachine airfoil element, the airfoil element comprises a metallic substrate having: an airfoil extending from a first end to a second end; and a cooling passageway system extending through the airfoil. The method comprises: applying an external vibration to an area of the airfoil element targeting internal fouling of the cooling passageway system; flushing the cooling passageway system; and imaging the cooling passageway system.

Abstract: Aspects of the disclosure are directed to a method for processing a component that includes a substrate and a coating coupled to the substrate, the method comprising: applying a laser beam to the coating in a first stage, the first stage characterized by a first number of pulses of the laser beam and a first offset corresponding to a focal point of the laser beam coinciding with an exterior surface of the coating, and applying the laser beam to the coating in a second stage, the second stage characterized by a second number of pulses of the laser beam and a second offset corresponding to the focal point of the laser beam being located within a span of the substrate.

Abstract: In a method for processing a turbomachine airfoil element, the airfoil element comprises a metallic substrate having: an airfoil extending from a first end to a second end; and a cooling passageway system extending through the airfoil. The method comprises: applying an external vibration to an area of the airfoil element targeting internal fouling of the cooling passageway system; flushing the cooling passageway system; and imaging the cooling passageway system.

Abstract: Aspects of the disclosure are directed to a probe for servicing a turbine blade of an engine. The probe includes hardware configured to couple to a fluid source, a stem, and an opening included in the stem, where the opening is oriented at a non-zero valued angle relative to a length of the stem. In some embodiments, a system includes a turbine blade of an engine, a machine that captures an image of the turbine blade, and a probe that includes a stem with an opening formed in the stem, where the opening is oriented at a non-zero valued angle relative to a length of the stem and removes debris from the turbine blade captured in the image based on an ejection of a pressurized fluid from the opening, where the debris is located on an interior surface of the turbine blade.

Abstract: Methods for repairing gas turbine engine components are provided. In this regard, a representative method includes: applying a surface treatment to the component such that locations at an exterior surface of the component exhibiting inter-granular attack are protected from erosion during a cleaning process; and cleaning the component using hydrogen fluoride ion cleaning to clean the component.

Abstract: A method for cleaning anode media, the method comprising removing the anode media from an electroplating system, and removing scale coatings from substrates of the anode media by vibrational polishing the anode media with abrasive particles.

Abstract: A method for cleaning anode media, the method comprising removing the anode media from an electroplating system, and removing scale coatings from substrates of the anode media by vibrational polishing the anode media with abrasive particles.

Abstract: A method for cleaning a component having an undesired substance thereon includes exposing the component to a cleaning solution and irradiating the component with microwave radiation to assist in removing the undesired substance.

Abstract: Methods for repairing gas turbine engine components are provided. In this regard, a representative method includes: applying a surface treatment to the component such that locations at an exterior surface of the component exhibiting inter-granular attack are protected from erosion during a cleaning process; and cleaning the component using hydrogen fluoride ion cleaning to clean the component.

Abstract: A gas turbine engine includes alternating rows of rotary airfoils or blades and static airfoils or vanes. The vanes are made of a base metal, such as cobalt or nickel superalloy. If a crack forms in one of the vanes, a braze alloy is applied to the crack. The braze alloy is a powdered slurry. The braze alloy includes approximately 50 to 100% of a base material and approximately 0 to 50% of a braze material. The base material of the braze alloy has the same composition as the composition of the base metal of the vane. The airfoil is then exposed to microwaves which melt the braze alloy in preference to the base metal to repair the crack in the vane.