Radiation shield and methods for manufacturing a radiation shield are provided herein, the method includes identifying a substrate for the radiation shield; identifying at least one material for cold spraying on the substrate; applying by cold spray a coating of the at least one material on the substrate thereby obtaining a radiation shield. The radiation shield is lighter, thinner, and more efficient compared to conventional radiation shields.

A method may include cold spraying a masking material on selected locations of a component to form a masking layer, wherein the masking material comprises a metal or alloy; additively manufacturing an additively manufactured portion of the component at locations at which the masking layer is not present; and removing the masking layer from the component. The masking layer may be configured to protect portions of the component by covering or otherwise providing a physical barrier that reduces or prevents material from adhering to unwanted portions of the component during a subsequent manufacturing and/or repair technique. Additionally, the masking layer may be reflective to infrared radiation and/or intimately contact the component and function as a heat sink or thermally conductive layer to transfer heat from the component.

A method for manufacturing a planet gear or a sun gear of a gearbox of a wind turbine includes forming a base of the planet gear via at least one of casting or forging. The base of the planet gear includes an inner circumferential surface and an outer circumferential surface. Therefore, at least one of the inner circumferential surface or the outer circumferential surface of the planet gear includes a plurality of net or near-net gear teeth. The method also includes applying a coating material to at least a portion of the base of the gear and at least a portion of the plurality of gear teeth of the gear via an additive manufacturing process so as to increase a hardness of the portions of the base and the plurality of gear teeth that includes the coating material.

A method for manufacturing a grain-oriented electrical steel sheet according to an aspect of the present invention includes a step of obtaining a hot-rolled steel sheet by carrying out hot rolling on a slab containing a predetermined component composition with a remainder including Fe and impurities, a step of obtaining a hot-rolled annealed sheet by carrying out hot-rolled sheet annealing as necessary, a step of carrying out pickling to obtain a pickled sheet, a step of carrying out cold rolling to obtain a cold-rolled steel sheet, a step of carrying out primary recrystallization annealing, a step of applying an annealing separating agent including MgO to a surface and then carrying out final annealing to obtain a final-annealed sheet, and a step of applying an insulating coating and then carrying out flattening annealing.

A method for joining two or more metallic components. The method includes operating a cold-spray apparatus to deposit a feedstock comprising nickel-based alloy particles on a braze region of a first metallic component to form a nickel-containing coating on the braze region. The method also includes brazing the first metallic component and a second metallic component by exposing the braze region to a braze material to form a braze joint that bonds the first metallic component to the second metallic component.

The invention relates to a method of forming a 3-dimensional solid object, comprising the steps: a) cold spraying one or more metallic powder to form a solid three dimensional item; b) thermally sintering the item such that a portion of the sprayed powder liquefies and reduces spaces between, and/or non-adhesion of, one or more solid portions of the item; and c) causing or allowing the portion of the sprayed powder that liquefied on heating, to become solid.

An electrical connecting structure (10) for use as a means for transmitting electrical energy between a first electrical component and a second electrical component, wherein the connecting structure (10) is formed from a number of layers (20, 30, 40, 50) arranged serially with one another, a first outer layer (20) consisting of aluminum or an aluminum alloy and a second outer layer (50) preferably consisting of aluminum or an aluminum alloy, and a third and preferably fourth layer (30, 40), specifically one or two inner layers, being provided between the outer layers (20, 50), the inner layer or inner layers (30, 40) being respectively produced by cold gas spraying.

A coated steel substrate has a steel substrate having a surface. A coating layer is atop the surface. The coating layer includes: aluminum activated by indium; and a ceramic binder. The coating also may comprise of multiple layers with different properties to facilitate the galvanic protection capability.

A method for inspecting and repairing a surface of a component of a gas turbine engine, the method including: inserting an inspection and repair tool into an interior of the gas turbine engine; inspecting the surface of the component with the inspection and repair tool; performing a repair of the surface of the component with the inspection and repair tool from within the interior of the gas turbine engine, the inspection and repair tool remaining within the interior of the gas turbine engine between inspecting the component and performing the repair of the surface of the component.

Methods of forming a desired geometry at a location on a superalloy part are disclosed. The method may include directing particles of a powder mixture including a low melt temperature superalloy powder and a high melt temperature superalloy powder to the location on the superalloy part at a velocity sufficient to cause the superalloy powders to deform and to form a mechanical bond but not a metallurgical bond to the superalloy part. The directing of particles continues until the desired geometry is formed. Heat is applied to the powder mixture on the repair location. The heat causes the low melt temperature superalloy powder to melt, creating the metallurgical bonding at the location. Another method uses the same directing to form a preform for repairing the location on the part. The low melt temperature superalloy powder melts at less than 1287° C., and the high melt temperature superalloy powder melts at greater than 1287° C.