Abstract: A method for removing a coating including a rare earth silicate from a substrate including a ceramic or ceramic matrix composite may include contacting a coating comprising a rare earth silicate with a liquid comprising an active species. The active species may include at least one of a mineral acid or a base. The method also may include working the coating to cause removal of at least a portion of the coating.

Abstract: A method and apparatus for removing a coating from a gas turbine engine component enabling repair of the component, including application of a braze alloy, without fluoride ion cleaning uses electrolytic stripping of the component in an alkaline bath with the component acting as an anode and current passing to a conformal cathode.

Abstract: Haptic devices that include a transducer configured to convert digital signals representing sound into sensory stimulation and methods of representing sound through sensory stimulation. An audio signal is received and a processed signal is generated from the audio signal that is indicative of a specific frequency in the audio signal. The processed signal is converted into a vibration stream used for sensory stimulation.

Abstract: A method for removing a coating including a rare earth silicate from a substrate including a ceramic or ceramic matrix composite may include contacting a coating comprising a rare earth silicate with a liquid comprising an active species. The active species may include at least one of a mineral acid or a base. The method also may include working the coating to cause removal of at least a portion of the coating.

Abstract: A titanium electrosurgical instrument, such as a scalpel (20), and electrosurgical devices, e.g., needle (40), and Bovie tips (40), are provided with a silane coating (30) directly against the solid titanium metal (26, 43, 73) of the body tissue-contacting distal ends (24, 47, 70) thereof whereby to impart advantageous non-stick properties thereto.

Abstract: A method and apparatus for forming a coating on a surface of a superalloy substrate area of a gas turbine engine component, and the component produced by the method, includes providing a slurry with selected metal powders suspended in a silane containing solution, applying the slurry by brushing, spraying or 3D printing using a piezoelectric dot matrix printhead to the superalloy substrate, drying the applied slurry, and depending on the aluminum content desired in the coating, including a sufficient amount of aluminum in the slurry or aluminiding the coated component. The method and apparatus can be used to obtain components having different superalloy coating thicknesses or compositions in different areas of the component based on the particular operating environment for each area with a single heat treatment and/or aluminiding cycle for obtaining the different coatings.

Abstract: Methods and systems for forming modified metal coatings on a gas turbine engine component. The gas turbine engine component is placed inside a container having a known volume, along with a source material containing a secondary element. The container, gas turbine engine component, and the source material inside the container are placed into an oxygen-depleted space inside a reaction chamber. At least one temperature for the source material is determined based upon the known volume of the container and an amount of the source material. While in the oxygen-depleted space, the source material is heated to the at least one temperature sufficient to release a vapor phase reactant containing the secondary element. The vapor phase reactant is confined inside the container at an approximately constant pressure and the secondary element is deposited from the vapor phase reactant as a layer on the gas turbine engine component.

Abstract: Metal components with a protective coating containing silicon and a process for forming such protective coatings. The protective coating is formed by applying a silicon-containing fluid composition to the metal component as a silicon-containing layer and then heating the silicon-containing layer to a temperature exceeding 400° F.

Abstract: A method of forming a metallic wetting layer on the surface of a metal component is provided, including the steps of placing the component into a chemical vapor deposition furnace, placing a metal-containing salt in the furnace, and heating the component and the metal-containing salt in the furnace to cause the metal from the metal-containing salt to deposit in a coating on the surface of the component forming a metallic wetting layer that improves the metallic bond of a subsequently applied brazing material. The process can be practiced with the addition of a cleaning reagent to both clean and coat in one operation.

Abstract: A turbine engine component (10) with a non-aluminide protective coating (14) containing silicon and chromium and a process for forming such non-aluminide protective coatings (14). The non-aluminide protective coating (14) is formed by applying a silicon-containing fluid composition to the turbine engine component (10) as a silicon-containing layer (20) and heating the silicon-containing layer (20) to a temperature effective to form the non-aluminide protective coating (14).

Abstract: A chemical vapor deposition (CVD) system and method for applying an aluminide coating constituted by two or more extrinsic metal components on a jet engine component. The aluminide coating is capable of forming a protective complex oxide upon subsequent heating in an oxidizing environment. At least one of the extrinsic metals in the aluminide coating is provided as a first vapor phase reactant from a receptacle coupled by a closed communication path with the reaction chamber of the CVD system and free of a carrier gas. The aluminide coating is formed by the chemical combination of the first vapor phase reactant with a second vapor phase reactant either created in situ in the reaction chamber or supplied by a carrier gas to the reaction chamber from a precursor source.

Abstract: Methods and systems for forming modified metal coatings on a gas turbine engine component (20). The gas turbine engine component (20) is placed inside a container (50) having a known volume, along with a source material (32) containing a secondary element. The container (50), gas turbine engine component (20), and the source material (32) inside the container are placed into an oxygen-depleted space (18) inside a reaction chamber (12). At least one temperature for the source material (32) is determined based upon the known volume of the container (50) and an amount of the source material (32). While in the oxygen-depleted space (18), the source material (32) is heated to the at least one temperature sufficient to release a vapor phase reactant (35) containing the secondary element.

Abstract: Metal components with a protective coating containing silicon and a process for forming such protective coatings. The protective coating is formed by applying a silicon-containing fluid composition to the metal component as a silicon-containing layer and then heating the silicon-containing layer to a temperature exceeding 400° F.

Abstract: A metal component (10) with a protective coating (16) containing silicon and a process for forming such protective coatings (14). The protective coating (16) is formed by applying a silicon-containing fluid composition to the metal component (10) as a silicon-containing layer (12) and heating the silicon-containing layer (12) to a temperature exceeding 400° F.

Abstract: A method of forming a metallic wetting layer on the surface of a metal component is provided, including the steps of placing the component into a chemical vapor deposition furnace, placing a metal-containing salt in the furnace, and heating the component and the metal-containing salt in the furnace to cause the metal from the metal-containing salt to deposit in a coating on the surface of the component forming a metallic wetting layer that improves the metallic bond of a subsequently applied brazing material. The process can be practiced with the addition of a cleaning reagent to both clean and coat in one operation.

Abstract: Methods for removing coatings from metal components, such as metal components used in aircraft and other aerospace vehicles and the oil industry. The method may include removing an outer layer of a coating with a first stripping operation, removing an inner layer of the coating with a second stripping operation, and specifying an aqueous bath for either the first stripping process based upon an element in the outer layer or the second stripping process based upon an element in the inner layer.

Abstract: Apparatus and methods for removing coatings from metal components, such as metal components used in aircraft and other aerospace vehicles and the oil industry, as well as aqueous bath compositions. The metal component may be DC coupled with a counter electrode and immersed in an aqueous bath that includes an active oxygen source and a ligand in a composition effective to remove the coating. The aqueous bath may include hydrogen peroxide as the active oxygen source and may be maintained in a specific pH range if the temperature of the aqueous bath is controlled. In an alternative embodiment, the composition of the aqueous bath may include a non-peroxide active oxygen source, such as sodium perborate, and be maintained in a different specific pH range. An oxygen sensor may be provided to periodically monitor the concentration of active oxygen in the aqueous bath.

Abstract: A gas turbine engine component with an aluminide coating on at least a portion of an airflow surface that includes a roughening agent effective to provide a desired surface roughness and a deposition process for forming such aluminide coatings. A layer including a binder and the roughening agent may be applied to the superalloy substrate of the component and the aluminide coating formed on the airflow surface portion by exposing the component and layer to an appropriate deposition environment. Suitable roughening agents include metal and ceramic particles that are dispersed on the airflow surface portion before exposure to the deposition environment. The particles, which are substantially intact after the aluminide coating is formed, are dispersed in an effective number to supply the desired surface roughness.

Abstract: A gas turbine engine component (10) with an aluminide coating (42) on at least a portion of an airflow surface (18) that includes a roughening agent (44) effective to provide a desired surface roughness and a deposition process for forming such aluminide coatings (42). A layer (40) including a binder (38) and the roughening agent (44) maybe applied to the superalloy substrate (46) of the component (10) and the aluminide coating (42) formed on the airflow surface portion by exposing the component (10) and layer (40) to an appropriate deposition environment. Suitable roughening agents include metal and ceramic particles (44) that are dispersed on the airflow surface portion before exposure to the deposition environment. The particles (44), which are substantially intact after the aluminide coating (42) is formed, are dispersed in an effective number to supply the desired surface roughness.

Abstract: Methods and systems for forming modified metal coatings on a gas turbine engine component (20). The gas turbine engine component (20) is placed inside a container (50) having a known volume, along with a source material (32) containing a secondary element. The container (50), gas turbine engine component (20), and the source material (32) inside the container are placed into an oxygen-depleted space (18) inside a reaction chamber (12). At least one temperature for the source material (32) is determined based upon the known volume of the container (50) and an amount of the source material (32). While in the oxygen-depleted space (18), the source material (32) is heated to the at least one temperature sufficient to release a vapor phase reactant (35) containing the secondary element.