The preset invention has as its object the provision of a laminate free of hexavalent chromium and excellent in corrosion resistance and wear resistance, and a manufacturing process of the laminate. To solve the above-described problems, a laminate according to the present invention includes a substrate, and a laminated film portion with metal films laminated in two or more layers. The laminate has an interface layer between each two adjacent ones of the metal films. The laminated film portion contains a first metal element as a principal component, the first metal element being at least one element of Ni, Cr, Co, and W, and a second metal element that is a metal element of smaller cohesive energy than that of the first metal element. The second metal element contained in the interface layer is at a content ratio higher than that of the second metal element contained in each of the adjacent metal films.

A method for creating a chrome-plated surface having a matte finish that typically includes: controlling a resistance of a current bridge circuit; depositing a first chromium layer on a substrate positioned in a chromium bath, wherein the first chromium layer is deposited by supplying current from a power source that is electrically connected to the substrate and to anodes positioned in the chromium bath; etching the first chromium layer by engaging a current bridge that closes the current bridge circuit; depositing a first intermediate chromium layer, wherein the first intermediate chromium layer is deposited by supplying current from the power source; etching the first intermediate chromium layer, wherein the first intermediate chromium layer is etched by engaging the current bridge; and depositing a final chromium layer, wherein the final chromium layer is deposited by supplying current from the power source.

A method for creating a chrome-plated surface having a matte finish that typically includes: controlling a resistance of a current bridge circuit; depositing a first chromium layer on a substrate positioned in a chromium bath, wherein the first chromium layer is deposited by supplying current from a power source that is electrically connected to the substrate and to anodes positioned in the chromium bath; etching the first chromium layer by engaging a current bridge that closes the current bridge circuit; depositing a first intermediate chromium layer, wherein the first intermediate chromium layer is deposited by supplying current from the power source; etching the first intermediate chromium layer, wherein the first intermediate chromium layer is etched by engaging the current bridge; and depositing a final chromium layer, wherein the final chromium layer is deposited by supplying current from the power source.

The method for treatment of parts, characterized in that it comprises the stages of applying an electrolytic chromium plating layer on a part; applying a coating over the entire outer surface of the part; selective stripping of the coating in order to leave the part with at least one coated portion and at least one uncoated portion; carrying out a selective etching on the layer in at least one part of the uncoated portion; metallization of the entire surface of the part; and removal of the coating.

A magnesium alloy composite structure includes a magnesium alloy substrate, a zinc layer applied to the magnesium alloy substrate, a copper layer applied to the zinc layer, a nickel strike layer applied to the copper layer; an autocatalytic nickel layer applied to the nickel strike layer and a surface layer applied to the autocatalytic nickel layer. Various surface layers include Aluminum Titanium Nitride, Boron Nitride, Chromium Nitride, Titanium Nitride, Zirconium Nitride, Zirconium Oxide, Zirconium Oxycarbide, Titanium Carbide, Titanium Nitride and Diamond Like Carbon.

A gas turbine engine component made of a nickel-based superalloy, the gas turbine engine component comprising a protective coating. The protective coating includes an inner diffusion barrier layer including any one or any combination of elements selected from the group consisting of platinum, palladium, tantalum, tungsten, hafnium and iridium, and an outer layer of hard material formed of hard particles embedded in a matrix.

A gas turbine engine component made of a nickel-based superalloy, the gas turbine engine component comprising a protective coating. The protective coating includes an inner diffusion barrier layer including any one or any combination of elements selected from the group consisting of platinum, palladium, tantalum, tungsten, hafnium and iridium, and an outer layer of hard material formed of hard particles embedded in a matrix.

The present invention relates to a very specific electroplating bath for depositing a black chromium layer, a respective method thereof, and a respective substrate with said black chromium layer thereon. The substrate comprising said black chromium layer is excellently suited for decorative purposes.

The present invention relates to a very specific electroplating bath for depositing a black chromium layer, a respective method thereof, and a respective substrate with said black chromium layer thereon. The substrate comprising said black chromium layer is excellently suited for decorative purposes.

An object comprising a chromium-based coating on a substrate is disclosed. The chromium is electroplated from an aqueous electroplating bath comprising trivalent chromium cations, wherein the chromium-based coating comprises at least one chromium-containing layer, the chromium-based coating does not contain macrocracks, wherein a macrocrack is a crack that extends from the outer surface of the chromium-based coating, through the chromium-based coating, to the substrate, the chromium-based coating has a Vickers microhardness value of 800-1100 HV, and the chromium-based coating exhibits a critical scratch load value (L.sub.C2) of at least 80 N in the adhesion test according to ASTM C1624-05 (2015; point 11.11.4.4). Further is disclosed a method for its production.