A method for producing an impeller, includes the following steps: a forming step of forming the impeller by fused deposition modeling; and a polishing step of polishing a wall that defines a channel of the impeller using particulate polishing materials. The particulate polishing materials are sprayed on the wall of the channel or the wall of the channel is rubbed with the particulate polishing materials in the polishing step.

A method of manufacturing an integrated impeller has a first shroud forming a bottom portion, a second shroud forming a lid portion, a hub formed at the center portion of the first shroud, and blades that section a flow path which is formed between the first shroud and the second shroud and through which a fluid flows. This method has the steps of: forming a flow path on the inner circumferential side of the impeller; and forming a flow path on the outer circumferential side of the impeller. The step of forming the flow path on the outer circumferential side of the impeller has the steps of: while rotating the linear electrode having a tip-end part and a base-end part about a longitudinal direction axis thereof, applying electric discharge machining to the first shroud; applying electric discharge machining to the second shroud; and applying electric discharge machining to the blade.

A method of polishing an outer surface of a ceramic coated gas turbine engine component includes applying a rotating diamond brush to the outer surface. The brush is configured to achieve a uniform finish of 150 microinches R.sub.a or less over the surface. The brush contains diamond impregnated bristles, and is affixed to a rotary head of a robotic arm. A force sensing controller limits brush forces against the component. The component disclosed is a hot section turbine vane designed for directional control of high temperature, high-pressure combustion gases, but the method may be applied to other components contained within such aerospace applications. The polished coating provides an improved thermal barrier for maintaining structural integrity of the component in environments having temperatures ranging up to 2,000 degrees Celsius. The method limits abrasive removal of ceramic material to only 0.0005 to 0.00075 inch, and saves time and expense over past practices.

A method for smoothing surface roughness within an internal passageway is disclosed. In various embodiments, the method comprises developing a first sphere progression through a length of the internal passageway, each sphere within the first sphere progression having a first sphere diameter greater than or equal to a diameter of the internal passageway; and developing a second sphere progression through the length of the internal passageway, each sphere within the second sphere progression having a second sphere diameter greater than the first sphere diameter, whereby the inner surface of the internal passageway is smoothed, first by the first sphere progression and then by the second sphere progression.

The present invention provides a method for producing a steam turbine member that is highly superior in smoothness. The present invention provides a method for producing a steam turbine member including a cladding layer forming step of forming a cladding layer from a powdered material containing a metal in a region of a base material in which corrosion easily occurs, and a surface heating step of heat-melting a surface of the cladding layer.

A turbine and a turbine-generator device for use in electricity generation. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters.

The present invention relates to a conditioning method of gas turbine engine components (e.g. compressor blades and vanes) for increasing fuel efficiency. The gas turbine engine components are plasma treated in a high vacuum environment to generally reach a surface roughness (Ra) below 150 nanometers and in some cases below 25 nanometers. Then during the same process the components are coated using either a metallic or ceramic, hard, thin coating ranging from 100 to 3000 nanometers in thickness depending on desired surface smoothness and non-fouling properties. The same treatment combined with a surface relaxation process, which is part of a smoothing process, allows applying even up to 100 micrometers of hard coating without changes to high cycle fatigue properties and overall performance. Improved surface smoothness of the components and enhanced non-adhesiveness of the contaminants advance the quality of the flow through the gas path and compressor efficiency.

A gas turbine engine blade includes a platform; an airfoil section extending from the platform in a first direction; a mount extending from the platform in a second direction opposite the first direction; a damper land on the platform, the damper land having a relatively smoother outward-facing surface than the platform; and a damper interfacing with the outward-facing surface of the damper land. A method of making a gas turbine engine blade is also disclosed.

A method for depositing a metal layer on a component includes applying an electrically conductive coating composition comprising a resin and metal particles on a coating region of the component and partially curing the resin to a gel state to form an electrically conductive coating. The method also includes applying additional metal particles to the partially cured resin in the gel state and depositing, via an electrodeposition process, a metal layer on the electrically conductive coating.

A turbine-generator device for use in electricity generation using heat from industrial processes, renewable energy sources and other sources. The generator may be cooled by introducing into the gap between the rotor and stator liquid that is vaporized or atomized prior to introduction, which liquid is condensed from gases exhausted from the turbine. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters.