A thermal coating method for applying a functional layer to a workpiece surface, particularly for applying a running surface coating to a cylinder running surface of a crankcase of an internal-combustion engine, includes the steps of: melting a coating material by use of a melting device, applying coating material droplets to the workpiece surface by use of a gas jet aimed at the workpiece surface, which gas jet blows coating material droplets from a melting location of the melting device onto the workpiece surface, and cooling or rapidly freezing the coating material droplets during their transport from the melting location to the workpiece surface.

A method to modify the shape of a channel in a metallic substrate is described. The method includes the step of applying at least one metallic coating on selected portions of an interior surface of the channel, so as to alter the heat transfer characteristics of the channel during passage of a coolant fluid therethrough. Related articles that contain the modified channels are also described, such as gas turbine engine components.

A method to modify the shape of a channel in a metallic substrate is described. The method includes the step of applying at least one metallic coating on selected portions of an interior surface of the channel, so as to alter the heat transfer characteristics of the channel during passage of a coolant fluid therethrough. Related articles that contain the modified channels are also described, such as gas turbine engine components.

The present invention relates to a rotating blade (5), in particular for a compressor or turbine stage of a gas turbine, having a radially outer rib arrangement with at least one rib (2), onto which a coating (3) is disposed, whereby, in a meridian section, the coating (3) has an outer contour (3.1), which extends axially outwardly in the radial direction.

The present invention relates to a rotating blade (5), in particular for a compressor or turbine stage of a gas turbine, having a radially outer rib arrangement with at least one rib (2), onto which a coating (3) is disposed, whereby, in a meridian section, the coating (3) has an outer contour (3.1), which extends axially outwardly in the radial direction.

An electrostatic chuck and a manufacturing method are disclosed in which drawbacks of using an adhesive are not existent and a freedom degree of design is high. The electrostatic chuck includes a substrate part constituting a main chuck body, a first insulating layer of a spray coating formed to the surface of the substrate part, a heater part of an electric conductor formed by applying a conductive paste to the surface of the first insulating layer, a second insulating layer of a spray coating formed to the surface of the first insulating layer so as to cover the heater part, an electrode part formed by thermal spraying to the surface of the second insulating layer and a dielectric layer of a spray coating formed to the surface of the second layer so as to cover the electrode part and lowers a volume resistivity without using an adhesive.

An electrostatic chuck and a manufacturing method are disclosed in which drawbacks of using an adhesive are not existent and a freedom degree of design is high. The electrostatic chuck includes a substrate part constituting a main chuck body, a first insulating layer of a spray coating formed to the surface of the substrate part, a heater part of an electric conductor formed by applying a conductive paste to the surface of the first insulating layer, a second insulating layer of a spray coating formed to the surface of the first insulating layer so as to cover the heater part, an electrode part formed by thermal spraying to the surface of the second insulating layer and a dielectric layer of a spray coating formed to the surface of the second layer so as to cover the electrode part and lowers a volume resistivity without using an adhesive.

Methods are provided for repairing a surface of a component within a gas turbine engine. A first bladder and a second bladder can be installed (simultaneously or independently) within the gas turbine engine. The first bladder and the second bladder can then be inflated with an inflating fluid to form a first circumferential seal and a second circumferential seal to define an isolated area within the gas turbine engine. All the surfaces within the isolated area can then be coated with a masking layer. At least a portion of the masking layer can then be removed to expose a working area, and a coating can be formed on the working area.

A manufacturing method for a component in a plasma processing apparatus is provided. The method includes: performing a surface conditioning on a surface of an underlying layer on which a film is to be formed by thermal spraying, the surface of the underlying layer includes a surface of a base or a surface of a layer formed on the surface of the base; and forming the film on the surface of the underlying layer by thermally spraying yttrium fluoride. A high velocity oxygen fuel spraying method or an atmospheric plasma spraying method is used in the forming of the film.

A garment with reflective material applied to an outer surface of the garment is provided herein. The reflective material is positioned on the garment based on modeled sun exposure. A method for modeling sun exposure to determine the positioning of reflective material on a garment is also provided herein. A system for modeling sun exposure, determining the position of reflective material on a garment, and applying the reflective material to the outer surface of the garment is also provided.