An abradable coating includes a matrix and particles that are dispersed in the matrix, the particles being made of a material switching into a fluid phase under the effect of the increase in temperature upon contact between a tip of a blading and the abradable coating.

An abradable coating includes a matrix and particles that are dispersed in the matrix, the particles being made of a material switching into a fluid phase under the effect of the increase in temperature upon contact between a tip of a blading and the abradable coating.

An article has a metallic substrate having a plurality of recesses. A first coating is at least at the recesses and has: a splatted layer; and a columnar layer atop the splatted layer. A second coating is away from the recesses and has: a columnar layer atop the substrate without an intervening splatted layer.

An article has a metallic substrate having a plurality of recesses. A first coating is at least at the recesses and has: a splatted layer; and a columnar layer atop the splatted layer. A second coating is away from the recesses and has: a columnar layer atop the substrate without an intervening splatted layer.

A method for forming a porous barrier coating on a substrate without substantial chemical segregation includes the steps of providing or obtaining a barrier coating material in powdered form and spraying the barrier coating material onto the substrate using air plasma spraying. The air plasma spraying is performed using an average homologous surface temperature of the depositing particles in a range of about 1.25 to about 1.5 and a particle velocity in a range of about 300 m/s to about 500 m/s. The depositing particles are fully molten.

A compressor seal-ring assembly includes a seal formed of a nickel, cobalt or iron-based superalloy; a counterface positioned for sealing interaction with the seal; and a lubricant coating on the seal, the lubricant coating being formed of a CoCrAlY-containing material.

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 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.

A bond coating material providing unexpectedly high thermal cyclic fatigue resistance and sulfidation resistance, and unexpectedly prolonged thermal cycle life in high temperature environments of gas turbine engine components with and without the presence of sulfur contains: a) 10% to 30% by weight chromium, b) at least one of tantalum and molybdenum in a total amount of 3% to 15% by weight, c) 5% to 13% by weight aluminum, d) 0.1% to 1.4% by weight silicon, e) 0.1% to 0.8% by weight yttrium, f) 0% to 1.2% by weight carbon, g) 0% to 1% by weight dysprosium, h) 0% to 1% by weight cerium, i) the balance being nickel, and the percentages of a) to i) adding up to 100% by weight. The total amount of tantalum and molybdenum, and the amounts of aluminum and silicon are each critical for avoiding delamination of a top coat from a bond coat.