The present disclosure belongs to the field of preparation technology and provides an ultralimit alloy and a preparation method therefor. The ultralimit alloy comprises an alloy matrix. A bonding layer and a ceramic layer are successively deposited on a surface of the alloy matrix. The alloy matrix includes one of a magnesium alloy matrix, an aluminium alloy matrix, a titanium alloy matrix, an iron alloy matrix, a nickel alloy matrix, a copper alloy matrix, a zirconium alloy, and a tin alloy. For an ultralimit magnesium alloy, an ultralimit aluminium alloy, an ultralimit nickel alloy, an ultralimit titanium alloy, an ultralimit iron alloy and an ultralimit copper alloy, the bonding layer is a composite bonding layer, the ceramic layer is a composite ceramic layer, and the outside of the composite ceramic layer is further successively deposited with a reflecting layer, a catadioptric layer, an insulating layer and a carbon foam layer.

The present disclosure belongs to the field of preparation technology and provides an ultralimit alloy and a preparation method therefor. The ultralimit alloy comprises an alloy matrix. A bonding layer and a ceramic layer are successively deposited on a surface of the alloy matrix. The alloy matrix includes one of a magnesium alloy matrix, an aluminium alloy matrix, a titanium alloy matrix, an iron alloy matrix, a nickel alloy matrix, a copper alloy matrix, a zirconium alloy, and a tin alloy. For an ultralimit magnesium alloy, an ultralimit aluminium alloy, an ultralimit nickel alloy, an ultralimit titanium alloy, an ultralimit iron alloy and an ultralimit copper alloy, the bonding layer is a composite bonding layer, the ceramic layer is a composite ceramic layer, and the outside of the composite ceramic layer is further successively deposited with a reflecting layer, a catadioptric layer, an insulating layer and a carbon foam layer.

A Nickel-based alloy includes (in wt %): 25.7%-27.3% Cobalt (Co), 15.0%-16.0% Chromium (Cr), 12.2%-13.2% Aluminum (Al), 0.3%-0.5% Yttrium (Y), 2.5%-3.5% Ruthenium (Ru), 0.4%-0.8% Silicon (Si), 0.4%-0.6% Tantalum (Ta), and 0.4%-0.6% Molybdenum (Mo).

A Nickel-based alloy includes (in wt %): 25.7%-27.3% Cobalt (Co), 15.0%-16.0% Chromium (Cr), 12.2%-13.2% Aluminum (Al), 0.3%-0.5% Yttrium (Y), 2.5%-3.5% Ruthenium (Ru), 0.4%-0.8% Silicon (Si), 0.4%-0.6% Tantalum (Ta), and 0.4%-0.6% Molybdenum (Mo).

A method of coating a component includes attaching the component to a support that is configured to hold a plurality of components and placing a base of the support in a holder that is attached to rotatable member of a fixture, wherein an axis of the holder is parallel to an axis of rotation of the rotatable member. The method also includes transporting the fixture into a coating chamber wherein a direction of an exit stream of a coater in oriented perpendicularly to the axis of rotation, exposing the fixture and the component to a reverse transfer arc cleaning/pre-heating procedure, and exposing the fixture and the component to a coating procedure during which a coating is directed at the component in a direction perpendicular to the axis of rotation while the rotatable member is rotating. The method further includes transporting the fixture and removing the component from the support fixture.

A method of coating a component includes attaching the component to a support that is configured to hold a plurality of components and placing a base of the support in a holder that is attached to rotatable member of a fixture, wherein an axis of the holder is parallel to an axis of rotation of the rotatable member. The method also includes transporting the fixture into a coating chamber wherein a direction of an exit stream of a coater in oriented perpendicularly to the axis of rotation, exposing the fixture and the component to a reverse transfer arc cleaning/pre-heating procedure, and exposing the fixture and the component to a coating procedure during which a coating is directed at the component in a direction perpendicular to the axis of rotation while the rotatable member is rotating. The method further includes transporting the fixture and removing the component from the support fixture.

A method for fabricating a substrate provided with a plurality of layers, includes: providing a steel substrate with an oxide layer including metal oxides on the steel substrate; providing a metal coating layer directly on the oxide layer, the metal coating layer including: at least 8% by weight nickel; at least 10% by weight chromium; and a remainder being iron and impurities from a fabrication process; and providing an anti-corrosion coating layer directly on the metal coating layer.

A method for fabricating a substrate provided with a plurality of layers, includes: providing a steel substrate with an oxide layer including metal oxides on the steel substrate; providing a metal coating layer directly on the oxide layer, the metal coating layer including: at least 8% by weight nickel; at least 10% by weight chromium; and a remainder being iron and impurities from a fabrication process; and providing an anti-corrosion coating layer directly on the metal coating layer.

An abradable coating for a turbomachine part, includes a matrix made of a first metal material and particles made of a second metal material that are dispersed in the matrix, the first metal material having a melting temperature greater than 900° C., the second metal material having a melting temperature at least 50° C. lower than the melting temperature of the first metal material.

A method may include removing a portion of a base component adjacent to a damaged portion of the base component to define a repair portion of the base component. The base component may include a cobalt- or nickel-based superalloy, and the repair portion of the base component may include a through-hole extending from a first surface of the base component to a second surface of the base component. The method also may include forming a braze sintered preform to substantially reproduce a shape of the through-hole. The braze sintered preform may include a Ni- or Co-based alloy. The method additionally may include placing the braze sintered preform in the through-hole and heating at least the braze sintered preform to cause the braze sintered preform to join to the repair portion of the base component and change a microstructure of the braze sintered preform to a brazed and diffused microstructure.