Abstract: A coated article has: a metallic substrate; a bondcoat; and a thermal barrier coating (TBC). The bondcoat has an MCrAlY first layer and an MCrAlY second layer, the second layer having a lower Cr content than the first layer.

Abstract: A method for coating a turbine engine component comprises the steps of: providing a turbine engine component having at least one sacrificial attachment on a first side; grasping the turbine engine component via the at least one sacrificial attachment to position a first surface of the turbine engine component relative to a source of coating material; and applying a coating to said first side.

Abstract: The present disclosure relates to an improved low-cost metallic coating to be deposited on gas turbine engine components. The metallic coating consists of 1.0 to 18 wt % cobalt, 3.0 to 18 wt % chromium, 5.0 to 15 wt % aluminum, 0.01 to 1.0 wt % yttrium, 0.01 to 0.6 wt % hafnium, 0.0 to 0.3 wt % silicon, 0.0 to 1.0 wt % zirconium, 0.0 to 10 wt % tantalum, 0.0 to 9.0 wt % tungsten, 0.0 to 10 wt % molybdenum, 0.0 to 43.0 wt % platinum, and the balance nickel.

Abstract: A turbine engine apparatus includes a structural component made of a superalloy material. A protective coating is disposed on the structural component and has a composition that consists essentially of up to 30 wt % cobalt, 5-40 wt % chromium, 7.5-35 wt % aluminum, up to 6 wt % tantalum, up to 1.7 wt % molybdenum, up to 3 wt % rhenium, up to 5 wt % tungsten, up to 2 wt % yttrium, 0.05-2 wt % hafnium, 0.05-7 wt % silicon, 0.01-0.1 wt % zirconium, and a balance of nickel.

Abstract: The present disclosure relates to an improved low-cost metallic coating to be deposited on gas turbine engine components. The metallic coating consists of 1.0 to 18 wt % cobalt, 3.0 to 18 wt % chromium, 5.0 to 15 wt % aluminum, 0.01 to wt % yttrium, 0.01 to 0.6 wt % hafnium, 0.0 to 0.3 wt % silicon, 0.0 to 1.0 wt % zirconium, 0.0 to 10 wt % tantalum, 0.0 to 9.0 wt % tungsten, 0.0 to 10 wt % molybdenum, 0.0 to 43.0 wt % platinum, and the balance nickel.

Abstract: Different thermal barrier coatings are deposited on different regions of the surface of a component. A first thermal barrier coating comprising an erosion resistant yttria stabilized zirconia material is deposited on a first region of the surface of the component. A second thermal barrier coating comprising an oxidation and corrosion resistant gadolinia stabilized zirconia is deposited on a second region of the surface of the component.

Abstract: A process for improving the adherence of a thermal barrier coating to a substrate includes the steps of providing a substrate, depositing a masking layer of aluminum, an aluminum alloy, or titanium alloy, or titanium on a surface of the substrate, depositing a non-thermally grown oxide layer of alumina or titania on the masking layer, and depositing a thermal barrier coating on the oxide layer.

Abstract: The thermal barrier coating system comprises a matrix of a first chemistry with multiple embedded second phases of a second chemistry. The matrix comprises a stabilized zirconia. The second regions comprise at least 40 mole percent of oxides having the formula Ln2O3, where Ln is selected from the lanthanides La through Lu, Y, Sc, In, Ca, and Mg with the balance zirconia (ZrO2), hafnia (HfO2), titania (TiO2), or mixtures thereof. The second phases have a characteristic thickness (T6) of less than 2.0 micrometers (?m). The spacing between second phases has a characteristic thickness (T5) of less than 8.0 micrometers (?m).

Abstract: A coating system for a turbine engine component has a substrate, a masking layer on a surface of the substrate, which masking layer comprises a homogeneous layer of a single metal, a non-thermally grown oxide layer deposited on the masking layer, and a thermal barrier coating deposited on the oxide layer.

Abstract: A method of repairing a damaged coated vane from a turbine module without removing the vane from the module is taught. The method includes locally removing the coating in the vicinity of the damage as well as any underlying damage in the superalloy substrate. A diffusible coating precursor is then applied to the damage site. A heat treating fixture is then mounted on the vane and repair site is heated to up to 2000° F. in an inert environment to interdiffuse the coating precursor and the substrate. After the diffusion anneal, the vane is cleaned and the module is returned to service.

Abstract: A coating system for a turbine engine component having a substrate includes a multi-layer bond coat applied to the substrate. The multi-layer bond coat has an oxidation resistant layer and a spallation resistant layer deposited over the oxidation resistant layer. Processes for forming the coating system are described.

Abstract: A method of stripping gamma/gamma prime polycrystalline alloy bond coats from single crystal gamma/gamma prime nickel based superalloys, including the steps of grit blasting followed by the use of hydrochloric acid solutions, followed by rinsing. The cycle may be repeated several times, with visual inspection between cycles.

Abstract: A method of repairing a damaged coated vane from a turbine module without removing the vane from the module is taught. The method includes locally removing the coating in the vicinity of the damage as well as any underlying damage in the superalloy substrate. A diffusible coating precursor is then applied to the damage site. A heat treating fixture is then mounted on the vane and repair site is heated to up to 2000° F. in an inert environment to interdiffuse the coating precursor and the substrate. After the diffusion anneal, the vane is cleaned and the module is returned to service.

Abstract: A metallic coating for protecting a substrate from high temperature oxidation and hot corrosion environments comprising about 2.5 to about 13.5 wt. % cobalt, about 12 to about 27 wt. % chromium, about 5 to about 7 wt. % aluminum, about 0.0 to about 1.0 wt. % yttrium, about 0.0 to about 1.0 wt. % hafnium, about 1.0 to about 3.0 wt. % silicon, about 0.0 to about 4.5 wt. % tantalum, about 0.0 to about 6.5 wt. % tungsten, about 0.0 to about 2.0 wt. % rhenium, about 0.0 to about 1.0 wt. % molybdenum and the balance nickel.

Abstract: A magnet array for a steered arc physical vapor deposition system has multiple magnets sandwiched between two pole plates.

Abstract: A physical vapor deposition system includes a segmented post cathode having multiple post segments.

Abstract: A process for repairing a workpiece includes the steps of: providing a workpiece having at least one interior surface requiring restoration; providing a source of repair material; and depositing the repair material onto the at least one interior surface using a technique which is a near non-line of sight technique.

Abstract: A turbine engine apparatus includes a structural component made of a superalloy material. A protective coating is disposed on the structural component and has a composition that consists essentially of up to 30 wt % cobalt, 5-40 wt % chromium, 7.5-35 wt % aluminum, up to 6 wt % tantalum, up to 1.7 wt % molybdenum, up to 3 wt % rhenium, up to 5 wt % tungsten, up to 2 wt % yttrium, 0.05-2 wt % hafnium, 0.05-7 wt % silicon, 0.01-0.1 wt % zirconium, and a balance of nickel.

Abstract: A puck for providing a coating material in a cathodic arc coating system has a generally uniform depression formed at the outer periphery. The depression ensures that an arc from the coating apparatus will move uniformly about the outer periphery of the puck, such that a coating cloud will also be uniformly applied to parts to be coated.

Abstract: A puck for providing a coating material in a cathodic arc coating system has a generally uniform depression formed at the outer periphery. The depression ensures that an arc from the coating apparatus will move uniformly about the outer periphery of the puck, such that a coating cloud will also be uniformly applied to parts to be coated.